Single crystal nickel-based superalloy

BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to single crystal nickel-based superalloys and, more particularly, single crystal nickel-based superalloys and articles made therefrom for use in advanced gas turbine engines under high stress, high temperature conditions.
2. Description of the Prior Art
Advances over recent years in the metal temperature and stress capability of single crystal articles have been the result of the continuing development of single crystal superalloys, as well as improvements in casting processes and engine application technology. These single crystal superalloy articles include rotating and stationary turbine blades and vanes found in the hot sections of gas turbine engines. However, gas turbine engine design goals have remained the same during the past decades. These goals include the desire to increase engine operating temperature, rotational speed, thrust-to-weight ratio, fuel efficiency, and engine component durability and reliability.
The basic technology of alloys for the casting of single crystal components is described in U.S. Pat. Nos. 3,494,709; 4,116,723 and 4,209,348. Development work resulted in first generation nickel-based superalloys, which were materially improved over those described in the aforementioned patents. However, these first generation nickel-based superalloys contained no rhenium. Examples of such first generation nickel-based superalloys, commercially known as CMSX-2 alloy and CMSX-3 alloy produced by Cannon-Muskegon Corporation, assignee of the present application, are described in U.S. Pat. No. 4,582,548. Further development work resulted in second generation nickel-based superalloys having improved creep strength/creep rate. These second generation nickel-based superalloys have a moderate rhenium content of about 3 weight percent. An example of such a second generation nickel-based superalloy is described in U.S. Pat. No. 4,643,782. This patent discloses a superalloy, commercially known as CMSX-4 alloy, having a specific nickel-based composition including a rhenium content in the range of 2.8-3.2 weight percent. The present invention provides the next generation of nickel-based superalloys having higher total refractory element (W+Re+Mo+Ta) content and improved mechanical properties.
Single crystal articles are generally produced having the low-modulus (001) crystallographic orientation parallel to the component dendritic growth pattern or blade stacking axis. Face-centered cubic (FCC) superalloy single crystals grown in the (001) direction provide extremely good thermal fatigue resistance relative to conventionally cast articles. Since these single crystal articles have no grain boundaries, alloy design without grain boundary strengtheners, such as carbon, boron and zirconium, is possible. As these elements are alloy melting point depressants, their reduction from an alloy design provides a greater potential for high temperature mechanical strength achievement since more complete gamma prime solution and microstructural homogenization can be achieved relative to directionally solidified (DS) columnar grain and conventionally cast materials. Their reduction also makes possible a higher incipient melting temperature.
These process benefits are not necessarily realized unless a multi-faceted alloy design approach is undertaken. Alloys must be designed to avoid tendency for casting defect formation such as freckles, slivers, spurious grains and recrystallization. Additionally, the alloys must provide an adequate heat treatment window (numeric difference between an alloy's gamma prime solvus and incipient melting point) to allow for nearly complete gamma prime solutioning. At the same time, the alloy compositional balance should be designed to provide an adequate blend of engineering properties necessary for operation in gas turbine engines. Selected properties generally considered important by gas turbine engine designers include: elevated temperature creep-rupture strength, thermo-mechanical fatigue resistance, impact resistance plus hot corrosion and oxidation resistance.
An alloy designer can attempt to improve one or two of these design properties by adjusting the compositional balance of known superalloys. However, it is extremely difficult to improve more than one or two of the design properties without significantly or even severely compromising the remaining properties. The unique superalloy of the present invention provides an excellent blend of the properties necessary for use in producing single crystal articles for operation in gas turbine engine hot sections.
SUMMARY OF THE INVENTION
This invention relates to a nickel-based superalloy comprising the following elements in percent by weight: from about 5.0 to about 7.0 percent rhenium, from about 1.8 to about 4.0 percent chromium, from about 1.5 to about 9.0 percent cobalt, from about 7.0 to about 10.0 percent tantalum, from about 3.5 to about 7.5 percent tungsten, from about 5.0 to about 7.0 percent aluminum, from about 0.1 to about 1.2 percent titanium, from about 0 to about 0.5 percent columbium, from about 0.25 to about 2.0 percent molybdenum, from about 0 to about 0.15 percent hafnium, and the balance nickel plus incidental impurities, the superalloy having a phasial stability number N.sub.V3B less than about 2.10.
Advantageously, this superalloy composition may be further comprised of (percentages are in weight percent) from about 0 to about 0.04 percent carbon, from about 0 to about 0.01 percent boron, from about 0 to about 0.01 percent yttrium, from about 0 to about 0.01 percent cerium and from about 0 to about 0.01 percent lanthanum. Although incidental impurities should be kept to the least amount possible, the superalloy can also be comprised of from about 0 to about 0.04 percent manganese, from about 0 to about 0.05 percent silicon, from about 0 to about 0.01 percent zirconium, from about 0 to about 0.001 percent sulfur, and from about 0 to about 0.10 percent vanadium. In all cases, the base element is nickel. Furthermore, this superalloy can advantageously have a phasial stability number N.sub.V3B less than about 1.85, and a chromium content of from about 1.8 to about 3.0 percent, a rhenium content of from about 5.5 to about 6.5 percent, and a cobalt content of from about 2.0 to about 5.0 percent. This invention provides a superalloy having an increased resistance to creep under high stress, high temperature conditions, particularly up to about 2030.degree. F.
In one preferred embodiment, this invention relates to a single crystal casting to be used under high stress, high temperature conditions up to about 2030.degree. F. characterized by an increased resistance to creep under such conditions. In this embodiment, the casting is made from a nickel-based superalloy consisting essentially of the following elements in percent by weight: from 6.2 to 6.8 percent rhenium, from 1.8 to 2.5 percent chromium, from 1.5 to 2.5 percent cobalt, from 8.0 to 9.0 percent tantalum, from 3.5 to 6.0 percent tungsten, from 5.5 to 6.1 percent aluminum, from 0.1 to 0.5 percent titanium, from 0.01 to 0.1 percent columbium, from 0.25 to 0.60 percent molybdenum, from 0 to 0.05 percent hafnium, from 0 to 0.04 percent carbon, from 0 to 0.01 percent boron, from 0 to 0.01 percent yttrium, from 0 to 0.01 percent cerium, from 0 to 0.01 percent lanthanum, from 0 to 0.04 percent manganese, from 0 to 0.05 percent silicon, from 0 to 0.01 percent zirconium, from 0 to 0.001 percent sulfur, from 0 to 0.10 percent vanadium, and the balance nickel+incidental impurities, wherein the superalloy has a phasial stability number N.sub.V3B less than about 1.65.
Single crystal articles can be suitably made from the superalloy of this invention. The article can be a component for a turbine engine and, more particularly, the component can be a gas turbine blade or gas turbine vane.
The superalloy compositions of this invention have a critically balanced alloy chemistry which results in a unique blend of desirable properties. These properties include: excellent single crystal component castability, particularly for moderately sized blade and vane components; adequate cast component solutionability; excellent resistance to single crystal cast component recrystallization; ultra-high creep-rupture strength to about 2030.degree. F.; extremely good smooth and notched low cycle fatigue strength; extremely good high cycle fatigue strength; high impact strength; very good bare hot corrosion resistance; very good bare oxidation resistance; adequate coatability; and adequate microstructural stability, such as resistance to the undesirable, brittle phases called topologically close-packed (TCP) phases.
Accordingly, it is an object of the present invention to provide superalloy compositions and single crystal articles made therefrom having a unique blend of desirable properties. It is a further object of the present invention to provide superalloys and single crystal articles made therefrom for use in advanced gas turbine engines under high stress, high temperature conditions, such as up to about 2030.degree. F. These and other objects and advantages of the present invention will be apparent to those skilled in the art upon reference to the following description of the preferred embodiments.

BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a chart of hot corrosion test results performed to 117 hours on one embodiment of the alloy of this invention and on two prior art alloys;
FIG. 2 is a chart of hot corrosion test results performed to 144 hours on another embodiment of the alloy of this invention and on a prior art alloy;
FIG. 3 is a graphical comparison of bare alloy oxidation data from tests performed at 2012.degree. F. on two embodiments of this invention and on three other alloys;
FIG. 4 is a graphical comparison of bare alloy oxidation data from tests performed at 1886.degree. F. on two embodiments of this invention and on three other alloys;
FIG. 5 is a graphical comparison of bare alloy corrosion data from tests performed at 1742.degree. F. on two embodiments of this invention and on two other alloys; and
FIG. 6 is a graphical comparison of bare alloy corrosion data from tests performed at 1742.degree. F. on four embodiments of this invention and on two other alloys.

DESCRIPTION OF THE PREFERRED EMBODIMENTS
The nickel-based superalloy of the present invention comprises the following elements in percent by weight:
______________________________________Rhenium about 5.0-7.0Chromium about 1.8-4.0Cobalt about 1.5-9.0Tantalum about 7.0-10.0Tungsten about 3.5-7.5Aluminum about 5.0-7.0Titanium about 0.1-1.2Columbium about 0-0.5Molybdenum about 0.25-2.0Hafnium about 0-0.15Nickel + Incidental balanceImpurities______________________________________
This superalloy composition also has a phasial stability number N.sub.V3B less than about 2.10. Further, this invention has a critically balanced alloy chemistry which results in a unique blend of desirable properties. These properties include increased creep-rupture strength relative to prior art single crystal superalloys, single crystal component castability, cast component solutionability, single crystal component resistance to recrystallization, fatigue strength, impact strength, bare hot corrosion resistance, bare oxidation resistance, component coatability, and microstructural stability, including resistance to TCP phase formation under high stress, high temperature conditions. Unlike prior nickel-based superalloys known in the art, the superalloys of the present invention have a low chromium, low cobalt and high rhenium content. The chromium is about 1.8-4.0% by weight. Advantageously, the chromium content is from 1.8% to 3.0% by weight. This chromium content is significantly lower than that typically found in prior art single crystal nickel-based superalloys. In the present superalloy, chromium provides hot corrosion resistance, although it may also assist with the alloy's oxidation capability. Tantalum and rhenium also assist toward hot corrosion property attainment, and aluminum is present at sufficient levels to provide adequate oxidation resistance, so that relatively low addition of chromium is tolerable in this alloy. Besides lowering the alloy's gamma prime solvus, chromium contributes to the formation of Cr, Re, W-rich TCP phase and must be balanced accordingly in these compositions.
The cobalt content is about 1.5-9.0% by weight. Advantageously, the cobalt content is from 2.0% to 5.0% by weight. This cobalt content is lower than that typically found in prior art single crystal nickel-based superalloys. In the present superalloy, cobalt assists in providing an appropriate heat treatment window since it has the effect of lowering the alloy's gamma prime solvus while generally not affecting its incipient melting point. Rhenium-containing alloys are generally designed with much higher cobalt content than the present invention for the purpose of imparting increased solid solubility and phasial stability. However, the superalloys of the present invention unexpectedly show that much lower cobalt contents are possible and desirable toward providing optimized phasial stability, including control of TCP phase formation.
The rhenium content is about 5.0-7.0% by weight and, advantageously, rhenium is present in an amount of from 5.5% to 6.5% by weight. The amount of rhenium in the superalloy of the present invention is significantly greater than the rhenium content of prior art single crystal nickel-based superalloys. Furthermore, the superalloys of this invention are generally designed with an increased level of refractory element content, e.g., W+Re+Mo+Ta. The tungsten content is about 3.5-7.5% by weight and, advantageously, the amount of tungsten is from 3.5% to 6.5% by weight. Tungsten is added since it is an effective solid solution strengthener and it contributes to strengthening the gamma prime. Additionally, tungsten is effective in raising the alloy's incipient melting temperature. The amount of tungsten added to these superalloys is balanced with the amount of rhenium added since they both contribute to the formation of "freckle" defects during the single crystal investment casting process. They also both strongly effect the propensity for TCP phase formation.
Similar to tungsten, rhenium is effective in raising the alloy's incipient melting point. However, rhenium is a more effective strengthener than tungsten, molybdenum and tantalum in terms of elevated temperature creep-rupture and, therefore, rhenium is added appropriately. Additionally, rhenium has a positive influence on this alloy's hot corrosion resistance. Moreover, rhenium partitions primarily to the gamma matrix, and it is effective in slowing gamma prime particle growth during high temperature, high stress conditions. Besides requiring the balancing of rhenium with tungsten for castability reasons, W+Re must also be set at a level consistent with minimizing TCP phase formation. In general, the TCP phases which occur in such material are rich in chromium, tungsten, and rhenium content, with rhenium being present in the greatest proportion. Thus, careful Re/W ratio control is necessary in this alloy to control the propensity for TCP phase formation.
The molybdenum content is about 0.25-2.0% by weight. Advantageously, molybdenum is present in an amount of from 0.25% to 1.5% by weight. Molybdenum is a good solid solution strengthener, but it is not as effective as tungsten, rhenium and tantalum. However, since the alloy's density is always a design consideration, and the molybdenum atom is lighter than the other solid solution strengtheners, the addition of molybdenum is a means of assisting control of the overall alloy density in the compositions of this invention.
The tantalum content is about 7.0-10.0% by weight and, advantageously, the tantalum content is from 8.0% to 10.0% by weight. Tantalum is a significant contributor to this alloy's strength through means of solid solution strengthening and enhancement of gamma prime particle strength (tantalum also partitions to the gamma prime phase). In this alloy, tantalum is able to be utilized at relatively high concentration since it does not contribute to TCP phase formation. Additionally, tantalum is an attractive single crystal alloy additive in this composition since it assists in preventing "freckle" defect formation during the single crystal casting process. Tantalum is also beneficial in this composition since it tends to raise this alloy's gamma prime solvus, and it is effective toward promoting good alloy oxidation and hot corrosion resistance, along with aluminide coating durability.
The aluminum content is about 5.0-7.0% by weight. Furthermore, the amount of aluminum present in this composition is advantageously from 5.3% to 6.5% by weight. Aluminum and titanium are the primary elements comprising the gamma prime phase. These elements are added in this composition in a proportion and ratio consistent with achieving adequate alloy castability, solution heat treatability, phasial stability and high mechanical strength. Aluminum is also added to this alloy in proportions sufficient to provide oxidation resistance.
The titanium content is about 0.1-1.2% by weight. Advantageously, titanium is present in this composition in an amount from 0.2% to 0.8% by weight. Titanium is generally beneficial to the alloy's hot corrosion resistance, but it can have a negative effect to oxidation resistance, alloy castability and alloy response to solution heat treatment. Accordingly, the titanium content must be maintained within the stated range of this composition.
The columbium content is about 0-0.5% by weight and, advantageously, the columbium content is from 0 to 0.3% by weight. Columbium is a gamma prime forming element and it is an effective strengthener in the nickel-based superalloys of this invention. Generally, however, columbium is a detriment to alloy oxidation and hot corrosion properties, so its addition to the composition of this invention is minimized. Moreover, columbium is added to this invention's composition for the purpose of gettering carbon, which can be chemi-sorbed into component surfaces during non-optimized vacuum solution heat treatment procedures. Any carbon pick-up will tend to form columbium carbide instead of titanium or tantalum carbide, thereby preserving the greatest proportion of titanium and/or tantalum for gamma prime and/or solid solution strengthening in this alloy.
The hafnium content is about 0-0.15% by weight and, advantageously, hafnium is present in an amount from 0.02 to 0.05% by weight. Hafnium is added in a small proportion to the present composition in order to assist with coating adherence. Hafnium generally partitions to the gamma prime phase.
The balance of this invention's superalloy composition is comprised of nickel and small amounts of incidental impurities. Generally, these incidental impurities are entrained from the industrial process of production, and they should be kept to the least amount possible in the composition so that they do not affect the advantageous aspects of the superalloy. For example, these incidental impurities may include up to about 0.04% by weight manganese, up to about 0.05% by weight silicon, up to about 0.01% by weight zirconium, up to about 0.001% by weight sulfur, and up to about 0.10% by weight vanadium. Amounts of these impurities which exceed the stated amounts could have an adverse effect upon the resulting alloy's properties.
Additionally, the superalloy may optionally contain about 0-0.04% by weight carbon, about 0-0.01% by weight boron, about 0-0.01% by weight yttrium, about 0-0.01% by weight cerium and about 0-0.01% by weight lanthanum.
Not only does the superalloy of this invention have a composition within the above specified ranges, but it also has a phasial stability number N.sub.V3B less than about 2.10. Advantageously, the phasial stability number N.sub.V3B is less than 1.85 and, preferably, the phasial stability number N.sub.V3B is less than 1.65. As can be appreciated by those skilled in the art, N.sub.V3B is defined by the PWA N-35 method of nickel-based alloy electron vacancy TCP phase control factor calculation. This calculation is as follows:
EQUATION 1
Conversion for weight percent to atomic percent: ##EQU1## where: Wi=weight percent of element i
Ai=atomic weight of element i
EQUATION 2
Calculation for the amount of each element present in the continuous matrix phase:
______________________________________Element Atomic amount Rii remaining______________________________________Cr R.sub.Cr = 0.97P.sub.Cr - 0.375P.sub.B - 1.75P.sub.CNi R.sub.Ni = P.sub.Ni + 0.525P.sub.B - 3(P.sub.Al + 0.03P.sub.Cr + P.sub.Ti - 0.5P.sub.C + 0.5P.sub.V + P.sub.Ta + P.sub.Cb + P.sub.Hf)Ti, Al, B, Ri = OC, Ta, Cb, HfV Rv = 0.5P.sub.V ##STR1##Mo ##STR2##______________________________________ *Note: weight percentage Re is added to weight percentage W for the calculation above.
EQUATION 3
Calculation of N.sub.V3B using atomic factors from Equations 1 and 2 above: ##EQU2## where: i=each individual element in turn.
N.sub.i i=the atomic factor of each element in matrix.
(N.sub.v)i=the electron vacancy No. of each respective element.
This calculation is exemplified in detail in a technical paper entitled "PHACOMP Revisited", by H. J. Murphy, C. T. Sims and A. M. Beltran, published in Volume 1 of International Symposium on Structural Stability in Superalloys (1968), the disclosure which is incorporated by reference herein. As can be appreciated by those skilled in the art, the phasial stability number for the superalloys of this invention is critical and must be less than the stated maximum to provide a stable microstructure and capability for the desired properties under high temperature, high stress conditions. The phasial stability number can be determined empirically, once the practitioner skilled in the art is in possession of the present subject matter.
The superalloy of this invention can be used to suitably make single crystal articles, such as components for turbine engines. Preferably, this superalloy is utilized to make a single crystal casting to be used under high stress, high temperature conditions characterized by an increased resistance to creep under such conditions, particularly high temperature conditions up to about 2030.degree. F. Furthermore, it is believed that this invention has an increased resistance to creep under high stress, high temperature conditions at about 2125.degree. F. and above compared to similar prior art materials, such as the CMSX-4 superalloy. While this superalloy can be used for any purpose requiring high strength castings incorporating a single crystal, its particular use is in the casting of single crystal blades and vanes for gas turbine engines. This alloy possesses an unusual resistance to component recrystallization during solution heat treatment, which is considered an important alloy characteristic that is necessary when producing advanced technology, multi-piece, cast bonded single crystal airfoils. Additionally, this superalloy provides the alloy castability characteristics believed necessary to produce conventional-process-cast, moderately-sized turbine airfoils with intricate cooling passages.
While this superalloy's primary use is in aircraft turbine engines, there are stationary engine applications requiring the specialized high performance characteristics of this alloy. This is particularly the case in turbine engines which require performing characteristics with very restricted clearances, thereby materially limiting the amount of permissible creep. Engines designed to develop high performance characteristics are normally operated at higher component temperatures and, therefore, the problem of creep is increased. Generally, creep in excess of 1% is considered unacceptable in these cases. The creep characteristics of known state of the art alloys have limited operating temperatures and, thus, maximum performance capability. The superalloy of this invention has an increased resistance to creep under high stress, high temperature conditions, particularly up to 2030.degree. F.
The single crystal components made from this invention's compositions can be produced by any of the single crystal casting techniques known in the art. For example, single crystal directional solidification processes can be utilized, such as the seed crystal process and the choke process.
The single crystal castings made from the superalloy of the present invention are advantageously subjected to a high temperature aging heat treatment in order to optimize the creep-rupture properties of these alloys. This invention's single crystal castings can be aged at a temperature of from about 1950.degree. F. to about 2125.degree. F. for about 1 to about 20 hours. Advantageously, this invention's single crystal castings can be aged at a temperature of from about 2050.degree. F. to about 2125.degree. F. for about 1 to about 20 hours. However, as can be appreciated by those skilled in the art, the optimum aging temperature and time for aging depends on the precise composition of the superalloy.
This invention provides superalloy compositions having a unique blend of desirable properties. These properties include: excellent single crystal component castability, particularly for moderately sized blade and vane components; excellent cast component solutionability; excellent resistance to single crystal cast component recrystallization; ultra-high creep-rupture strength to about 2030.degree. F.; extremely good low cycle fatigue strength; extremely good high cycle fatigue strength; high impact strength; very good bare hot corrosion resistance; very good bare oxidation resistance; adequate component coatability; and microstructural stability, such as resistance to formation of the undesirable TCP phases. As noted above, this superalloy has a precise composition with only small permissible variations in any one element if the unique blend of properties is to be maintained.
In order to more clearly illustrate this invention and provide a comparison with representative superalloys outside the claimed scope of the invention, the examples set forth below are presented. The following examples are included as being illustrations of the invention and its relation to other superalloys and articles, and should not be construed as limiting the scope thereof.
EXAMPLES
A large number of superalloy test materials were prepared to investigate the compositional variations and ranges for the superalloys of the present invention. Some of the alloy compositions tested and reported below fall outside the claimed scope of the present invention, but are included for comparative purposes to assist in the understanding of the invention. Representative alloy aim chemistries of those materials tested are reported in Table 1 below.
TABLE 1__________________________________________________________________________ See "Key" BelowAlloy C B Cr Co Mo W Cb Ti Al Ta Re Nf Ni Nv38* 1 2 3 4__________________________________________________________________________CMSX-10A -- -- 3.0 8.5 .70 7.2 .30 .65 6.0 7.6 5.0 .05 BAL 2.08 12.46 6.65 14.55 20.7610B -- -- 2.6 8.2 .70 6.95 .30 .68 6.0 7.9 4.95 .06 BAL 2.02 11.9 6.68 14.88 20.510C -- -- 2.5 7.7 .70 6.6 .30 .65 5.9 8.2 4.8 .05 BAL 1.90 11.4 6.55 15.05 20.310D -- -- 4.0 4.8 .60 6.4 .30 .60 5.7 8.2 4.9 .03 BAL 1.95 11.3 6.30 14.80 20.110E -- -- 2.2 7.2 .70 6.3 .25 .72 5.85 8.3 4.8 .042 BAL 1.84 11.1 6.57 15.12 20.110F .02 .02 2.4 7.6 .65 6.45 .28 .63 5.9 8.5 5.0 .046 BAL 1.89 11.45 6.53 15.31 20.610G -- -- 2.4 6.3 .50 6.4 .20 .70 5.8 8.0 5.5 .04 BAL 1.82 11.9 6.5 14.7 20.410Ga -- -- 2.4 4.0 .50 6.2 .15 .55 5.8 8.3 5.6 .04 BAL 1.72 11.8 6.35 14.8 20.610K-10Gb -- -- 2.3 3.3 .40 5.5 .10 .30 5.7 8.4 6.3 .03 BAL 1.60 11.8 6.0 14.5 20.610H -- -- 2.2 5.9 .50 6.4 .15 .80 5.9 8.0 5.5 .04 BAL 1.82 11.9 6.7 14.85 20.410I -- -- 2.5 4.7 .50 6.4 .15 .70 5.8 7.9 6.0 .04 BAL 1.81 12.4 6.5 14.65 20.910Ia -- -- 2.5 3.3 .40 6.1 .10 .60 5.8 7.9 6.0 .04 BAL 1.69 12.1 6.4 14.4 20.410J .015 .01 2.65 4.0 .50 6.0 .20 .65 5.8 9.0 5.5 .04 BAL 1.79 11.5 6.45 15.65 21.010L -- -- 2.0 2.7 .40 5.3 .10 .20 5.65 8.4 6.3 .03 BAL 1.50 11.6 5.85 14.35 20.4CMSX-12A -- -- 3.0 4.5 .35 5.5 -- 1.0 5.65 9.0 5.5 .04 BAL 1.84 11.0 6.65 15.65 20.3512B -- -- 3.5 3.0 .35 5.0 -- .90 5.60 8.8 6.0 .04 BAL 1.80 11.0 6.5 15.3 20.1512C -- -- 2.8 3.5 .40 5.3 -- .73 5.60 8.8 5.8 .04 BAL 1.70 11.1 6.35 15.15 20.312D-12Ca -- -- 2.5 3.2 .45 4.7 -- .50 5.60 8.7 6.3 .03 BAL 1.61 11.0 6.10 14.8 20.1512E -- -- 2.0 3.0 .45 4.7 -- .40 5.60 8.7 6.3 .03 BAL 1.50 11.0 6.0 14.7 20.15CMSX-10Ri -- -- 2.65 7.0 .60 6.4 .40 .80 5.8 7.5 5.5 .06 BAL 1.91 11.9 6.6 14.5 20.0CMSX-12Ri -- -- 3.4 8.0 .50 6.0 -- 1.0 5.6 7.6 5.3 .06 BAL 1.92 11.3 6.6 14.6 19.4__________________________________________________________________________ Key: 1 W + Re 2 Al + Ti 3 Al + Ti + Te + Cb 4 W + Re + Mo + Ta *Calculated using PWA W35 Method
Third generation single crystal alloy development to investigate the compositional variations for the superalloys of the present invention began with the definition and evaluation of a series of experimental compositions. Increased creep-rupture strength was the primary objective of the initial development effort, with elemental balancing to provide a combination of useful engineering characteristics following the definition of a base concept for increased strength.
The initial materials explored the utility of higher levels of refractory element and gamma prime forming elements than are present in similar prior art compositions. As shown in Table 1, the alloy chromium content was reduced to improve alloy stability. Cobalt content, initially thought to be required for increased solid solubility, could be significantly reduced. Refractory element content (W+Re+Mo+Ta) was varied, while the summation of the primary gamma prime partitioning element (Al+Ti+Ta+Cb) was also varied. The alloy's Re content was initially explored at conventional levels, but it was found that the Re level had to be increased.
Standard N.sub.v3B calculations were performed during the initial alloy design stage to assist respective alloy phasial stability predictions, with that number varying from one alloy composition to another.
Some of the alloys were produced using production-type procedures. These alloys were vacuum induction melted in the Cannon-Muskegon Corporation V-1 furnace, yielding approximately 200-300 lbs. of bar product per alloy (see Table 2 below). Quantities of each compositional iteration, as reported in Table 2, were made into test bars and test blades by vacuum investment casting. Solution heat treatment procedures were developed in the laboratory in 3" and 6" diameter tube furnaces. Gamma prime aging treatments were also performed in the laboratory.
TABLE 2__________________________________________________________________________V-1 VIM FURNACE HEAT CHEMISTRIESAlloy Heat No. C B Cr Co Mo W Cb Ti Al Ta Re Nf Ni__________________________________________________________________________CMSX-10A VF 778 .001 <.001 2.9 8.5 .7 7.2 .3 .70 6.05 7.6 5.0 .05 BASE10B VF 831 .002 <.001 2.6 8.2 .7 6.9 .3 .68 6.06 7.9 4.9 .05 BASE10Ri VF 965 .001 <.001 2.65 7.0 .6 6.4 .4 .80 5.72 7.6 5.5 .06 BASE10Ri VF 966 .001 <.001 2.67 7.0 .6 6.3 .4 .80 5.66 7.6 5.4 .06 BASE10Ri VF 980 .001 <.001 2.66 7.0 .6 6.3 .4 .79 5.78 7.6 5.4 .06 BASE12Ri VF 963 .001 <.001 3.3 8.0 .48 6.0 <.05 1.01 5.69 7.6 5.3 .07 BASE12Ri VF 964 .001 <.001 3.4 8.0 .48 6.1 <.05 1.00 5.60 7.6 5.3 .04 BASE12Ri VF 979 .001 <.001 3.4 8.0 .50 6.1 <.05 1.00 3.56 7.6 5.3 .06 BASE10Ga VF 983 .001 <.001 2.4 3.95 .41 6.1 .14 .36 5.83 8.4 5.9 .03 BASE12C VF 985 .001 <.001 2.7 3.5 .45 5.3 <.05 .75 5.66 8.8 6.0 .025 BASE10Cb (-10K) VF 994 .001 <.001 2.2 3.3 .40 5.3 .09 .24 5.74 8.2 6.4 .025 BASE12Ca (-12D) VF 993 .001 <.001 2.4 3.2 .46 4.8 <.01 .50 5.64 8.6 6.4 .025 BASE__________________________________________________________________________
All other specimens reported in Table 1 above were produced by blending base alloy bar stock with the virgin elemental additions necessary to achieve the desired composition. The blending was done during test bar and blade manufacture. The base alloy bar stock plus virgin additions were placed into the casting furnace melt crucible, melted and the bath homogenized prior to pouring into an appropriate shell mold. It is believed that good correlation between alloy aim chemistry and test bar/blade chemistry was routinely achieved (see Table 3 below).
TABLE 3__________________________________________________________________________ALLOY TEST BAR CHEMISTRIESAlloy C B Cr Co Mo W Cb Ti Al Ta Re Hf Ni Nv3B*__________________________________________________________________________CMSX-10A -- -- 2.9 8.5 .68 7.4 .29 .69 6.0 7.5 5.1 .07 BAL 2.0910B -- -- 2.7 8.1 .69 6.95 .29 .69 6.0 7.8 4.8 .06 BAL 2.0110C -- -- 2.6 7.7 .69 6.4 .30 .62 5.7 8.3 4.7 .07 BAL 1.8610D -- -- 4.0 5.0 .62 6.0 .31 .59 5.44 8.1 4.7 .04 BAL 1.8310E -- -- 2.2 7.2 .70 6.4 .26 .63 5.89 8.2 4.8 .05 BAL 1.8410F .014 .027 2.4 7.7 .65 6.4 .28 .63 5.96 7.9 5.0 .04 BAL 1.8610G -- -- 2.5 6.5 .53 5.5 .20 .68 5.6 8.2 4.6 .05 BAL 1.6810Ga -- -- 2.4 4.0 .41 6.2 .14 .55 5.79 8.3 6.0 .025 BAL 1.7310Cb (10K) -- -- 2.3 3.5 .42 5.9 .10 .43 5.67 8.5 6.0 .024 BAL 1.6310N -- -- 2.3 5.6 .51 6.2 .17 .76 5.58 7.8 5.4 .05 BAL 1.6910I -- -- 2.6 4.8 .52 6.6 .14 .67 5.65 7.4 5.4 .04 BAL 1.7010Ia -- -- 2.7 3.5 .47 5.2 .10 .60 5.80 8.0 5.8 .04 BAL 1.6710J .017 .10 2.6 4.0 .48 6.0 .19 .62 5.74 8.8 5.7 .04 BAL 1.7610L -- -- 1.9 2.7 .41 5.4 .10 .22 5.68 8.4 6.2 .03 BAL 1.4912A -- -- 3.0 4.6 .39 5.3 <.01 .96 5.61 9.4 5.0 .05 BAL 1.8012B -- -- 3.5 3.0 .38 5.1 <.01 .84 5.52 8.8 6.1 .05 BAL 1.7912C -- -- 2.7 3.5 .45 5.4 <.01 .75 5.62 8.8 6.0 .04 BAL 1.7212Ca (12D) -- -- 2.5 3.2 .46 5.0 <.01 .61 5.56 8.7 6.0 .03 BAL 1.6012E -- -- 2.0 3.0 .45 4.7 <.01 .40 5.63 8.7 6.3 .02 BAL 1.5110Ri -- -- 2.65 7.0 .60 6.4 .40 .80 5.67 7.6 5.5 .065 BAL 1.8712Ri -- -- 3.4 8.0 .48 6.1 <.01 .99 5.54 7.6 5.3 .07 BAL 1.92__________________________________________________________________________ *PWA N35 Method
For the CMSX-10D specimen (see Table 1), high quality virgin elemental additions were vacuum melted and the refined material was poured into 2" diameter bars. In turn, a quantity of the resulting bar was used to produce single crystal test bar/blade specimens by investment casting.
It was apparent that considerable variation in the investment casting process integrity may have occurred during specimen manufacture since varying levels of test bar freckle formation, secondary dendrite arm spacing and property attainment were apparent. Derivative alloy response to solution treatment (reported in Table 4 below) varied, and was a function of both alloy composition and test specimen quality.
Heat treatments developed for the alloy iterations are reported in Table 4 below. Full gamma prime solutioning was desired for each material, however, this objective was not universally achieved. Primary gamma prime aging was performed to effect a more desirable gamma prime particle size and distribution. Secondary gamma prime aging was performed to effect precipitation of conventional matrix gamma prime precipitates along with ultra-fine gamma prime precipitates located within the matrix channels between the primary gamma prime particles for these specimens.
TABLE 4__________________________________________________________________________Heat Treatment Detail Peak Solution TemperatureAlloy .degree.F. .degree.C. % .gamma." Solutioned* Primary .gamma.' Aging+ Secondary .gamma.' Aging+__________________________________________________________________________CMSX-10A 2460 1349 97.0-98.0 1975.degree. F./4 Hrs 1600.degree. F./20 + 1400.degree. F./2410B 2465 1352 97.0-98.0 1975.degree. F./4 Hrs 1600.degree. F./20 + 1400.degree. F./24 1975.degree. F/19.5 Hrs10C 2470 1354 99.0-99.5 2100.degree. F./8 Hrs 1600.degree. F./20 + 1400.degree. F./24 1975.degree. F./10 Hrs10D 2450 1343 99.9-100 1975.degree. F./10 Hrs 1600.degree. F./22 + 1400.degree. F./2410E 2465 1352 100 1975.degree. F./15 Hrs 1600.degree. F./20 + 1400.degree. F./24 1975.degree. F./21 Hrs 1600.degree. F./25.5 + 1400.degree. F./2310F 2444 1340 95 1975.degree. F./16 Hrs 1600.degree. F./23 + 1400.degree. F./2410G 2475 1357 99.0-99.5 1975.degree. F./12 Hrs 1600.degree. F./24.5 + 1400.degree. F./1710Ga 2485-90 1363-65 99.5-100 2075.degree. F./5 Hrs 1600.degree. F./20 + 1400.degree. F./23 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./30 1612.degree. F./48 + 1414.degree. F./2210Gb(10K) 2485 1363 100 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3010H 2475 1357 98.5-99.0 1975.degree. F./16 Hrs 1600.degree. F./27.5 + 1400.degree. F./27 1975.degree. F./18 Hrs 1600.degree. F./101 + 1400.degree. F./4610I 2475 1357 100 2075.degree. F./5 Hrs 1600.degree. F./22 + 1405.degree. F./2410Ia 2480 1360 99.5-100 2075.degree. F./5 Hrs 1600.degree. F./24 + 1400.degree. F./2410J 2480 1360 98.0-99.0 1975.degree. F./15 Hrs 1600.degree. F./24 + 1400.degree. F./30 2075.degree. F./5 Hrs 1600.degree. F./24 + 1400.degree. F./3010L 2490 1365 100 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3012A 2475 1357 98.5-99.0 1975.degree. F./16.5 Hrs 1600.degree. F./24 + 1400.degree. F./32 1975.degree. F./12 Hrs 1600.degree. F./24 + 1400.degree. F./27.512B 2480 1360 99.0-99.5 1975.degree. F./13 Hrs 1600.degree. F./57 + 1400.degree. F./3912C 2485-90 1363-65 99.5-100 2075.degree. F./5 Hrs 1600.degree. F./20 + 1400.degree. F./5 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3012Ca(12D) 2485 1363 100 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3012E 2490 1365 100 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3010Ri 2460 1349 98.5-99.8 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./3012Ri 2455 1346 100 2075.degree. F./6 Hrs 1600.degree. F./24 + 1400.degree. F./30__________________________________________________________________________ *Determined by visual estimation + Specimens air cooled from all aging treatments
Fully heat treated test bars were creep-rupture tested. The specimens were machined and low-stress ground to ASTM standard proportional specimen dimension. The specimens were creep-rupture tested at various conditions of temperature and stress, according to standard ASTM procedure.
A significant factor of the CMSX-10A alloy design was the shift to higher Re content. At the same time, W, Cr, Ta and other gamma prime strengtheners were balanced to provide the desired alloy characteristics and properties. The alloys higher Re level resulted in significantly improved creep-rupture strength throughout the entire test regime, as indicated by the results reported in Table 5 below for the CMSX-10A specimen.
TABLE 5__________________________________________________________________________CMSX-10A CREEP-RUPTURE TIME IN HOURS RUPTURE TIME % % FINAL CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1600.degree. F./75.0 ksi 534.4 24.2 26.9 534.2 22.331 10.9 21.0 328.4 22.0 27.8 328.3 21.055 6.3 8.7 527.3 21.1 26.3 526.3 17.552 28.4 72.21700.degree. F./50.0 ksi 305.0 31.1 34.5 304.2 28.614 62.1 108.9 292.4 19.2 19.9 291.8 19.324 71.5 123.7 87.6 2.6 5.8 85.7 1.474 65.9 --1800.degree. F./30.0 ksi 415.6 16.1 21.4 413.8 15.643 182.7 246.1 848.0 37.1 33.0 846.3 34.326 460.4 524.3 1016.2 33.2 30.5 1014.3 32.984 476.8 655.11800.degree. F./36.0 ksi 586.5 38.1 38.0 585.6 33.050 395.0 425.0 572.7 36.9 35.3 570.7 29.029 395.0 422.0 546.5 26.4 34.2 545.7 25.843 373.0 406.0 420.3 22.4 26.3 418.7 18.105 286.7 317.6 426.0 14.8 17.0 425.1 10.244 326.5 353.2 239.8 24.3 23.8 239.7 23.264 94.1 123.9 255.7 19.9 27.4 253.6 18.510 115.2 152.71900.degree. F./25.0 ksi 32.3 5.5 11.0 31.0 2.075 26.7 30.7 129.7 43.2 38.9 128.7 39.556 30.4 48.1 168.7 34.7 36.4 166.1 30.816 58.2 78.4 228.1 18.1 32.3 226.4 16.926 146.3 160.6 277.7 29.5 31.1 276.4 27.323 9.9 29.9 423.4 39.7 38.3 422.7 35.121 218.4 250.9 383.8 35.9 36.1 382.7 34.861 192.9 226.7 373.3 31.3 35.7 371.6 26.138 211.6 238.02000.degree. F./18.0 ksi 138.0 22.3 33.0 136.3 19.052 33.9 77.0 134.9 40.7 36.5 134.7 38.328 54.7 71.9 122.9 23.2 34.9 122.0 19.050 50.1 69.4 115.6 34.2 36.6 114.4 30.861 40.8 56.8 245.2 35.1 36.2 244.3 29.844 135.7 157.9 221.9 36.3 35.4 221.8 33.737 113.0 140.0 818.2 32.1 34.2 180.1 29.249 53.1 61.42050.degree. F./15.0 ksi 126.4 47.9 49.0 124.1 30.086 45.8 69.8 150.5 45.5 47.8 148.1 39.308 16.8 34.5 140.5 30.6 40.0 138.7 23.596 30.6 76.4 120.8 29.5 39.7 120.0 29.479 16.3 55.6 79.0 11.7 14.4 79.0 11.644 41.7 54.8 112.2 24.3 31.3 112.1 21.401 55.9 69.52100.degree. F./12.5 ksi 94.1 22.1 27.5 94.1 20.520 42.2 62.6 112.5 39.4 33.1 112.2 29.126 28.0 58.8 96.6 25.9 35.9 95.5 14.542 52.3 62.5 123.6 43.4 40.4 122.9 31.050 40.9 63.5 50.8 21.7 29.6 49.9 9.330 35.1 37.6 90.5 41.6 43.7 89.7 37.422 13.6 38.51800.degree. F./36.0 ksi* 420.6 23.9 35.1 419.9 23.196 213.8 286.0 396.1 37.1 34.0 394.7 31.623 239.4 264.9 384.9 31.1 34.0 382.9 25.554 220.5 247.9__________________________________________________________________________ *As-Solutioned Condition
Microstructural review of the failed rupture specimens of this alloy revealed that TCP phase precipitation occurred during the respective creep-rupture tests, particularly those at 1900.degree. F. and above. It became apparent that the N.sub.V3B phasial stability number calculation would be an effective tool in predicting alloy stability and, effectively, high temperature creep strength for the invention.
Wherein the CMSX-10A specimen's N.sub.V3B number was 2.08, CMSX-10B was designed to the 2.02 level. This was accomplished by the further reduction of alloy Cr content and similar reduction to Co and W+Re level. W was reduced more than the Re in this specimen since Re is more effective in the solid solution. Additionally, wherein some loss in W contribution to the gamma prime could be anticipated, it was sufficiently replaced by the modest increase to Ta content in this composition. These changes resulted in the CMSX-10B alloy specimen exhibiting even more improved creep strength at 1800.degree. F. Table 6 reported below illustrates that three specimens achieved an average life of 961 hours, with 1.0% creep occurring at an average of 724 hours. However, it was observed that TCP phase was present at higher temperature.
TABLE 6__________________________________________________________________________CMSX-10B CREEP-RUPTURE TIME IN HOURS RUPTURE TIME % % FINAL CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 907.1 19.2 34.0 907.0 17.832 697.2 752.7 989.3 18.9 33.5 968.5 17.657 768.1 817.8 968.4 35.9 36.1 967.3 31.813 705.8 767.5 507.0 44.1 45.4 505.7 41.548 317.9 352.6 598.1 46.9 43.4 596.1 42.340 386.5 415.2 408.3 62.6 52.1 407.2 54.479 187.3 256.5 265.3 39.7 43.7 262.7 37.102 87.6 119.2 385.3 45.5 46.2 383.5 39.031 177.4 213.4 412.8 43.4 40.5 410.6 38.771 189.1 233.4 389.3 51.5 44.2 386.8 36.920 220.5 249.2 459.5 40.0 46.3 458.0 39.513 210.2 291.1 258.0 38.1 40.6 257.9 36.743 32.1 90.2 484.1 27.9 40.0 483.4 26.296 288.1 326.7 376.9 16.4 20.4 376.8 16.088 96.0 226.6 481.0 50.5 48.2 478.8 34.557 264.4 297.5 461.5 35.1 40.6 460.1 30.786 181.1 265.3 483.0 47.1 46.8 482.1 43.714 286.2 320.7 500.1 33.4 37.0 499.7 30.486 11.9 280.11800.degree. F./40 ksi 436.7 40.2 44.1 436.2 39.818 294.6 318.9 390.8 50.1 42.8 390.3 41.817 250.9 376.2 336.9 52.7 48.1 335.2 46.697 226.5 240.91900.degree. F./25.0 ksi 237.8 55.9 45.7 237.4 53.834 33.0 113.5 295.7 57.4 49.1 295.6 46.592 123.7 170.92000.degree. F./18.0 ksi 192.7 31.5 26.6 191.6 27.733 56.3 88.6 166.5 41.4 25.3 166.5 34.102 46.2 72.7 173.3 36.6 27.0 171.4 31.481 24.0 66.12050.degree. F./15.0 ksi 219.6 40.1 40.4 218.6 37.871 13.2 56.8 122.3 28.2 47.9 120.6 26.614 37.0 63.7 118.4 33.2 60.0 116.9 29.986 36.7 56.5 179.7 44.1 48.1 179.1 39.188 8.4 75.3 74.9 44.2 48.6 74.6 34.800 6.8 14.5 168.3 48.6 49.7 167.0 43.171 36.9 77.1 104.8 17.0 27.2 102.8 1.626 66.1 -- 155.9 46.3 49.8 155.2 38.388 64.4 81.9 90.6 15.1 21.4 87.1 1.046 75.5 -- 120.5 46.3 55.8 118.7 35.143 10.3 27.7 150.7 39.8 49.7 150.1 33.903 21.4 60.9 149.5 33.2 46.2 148.9 23.166 73.3 88.3 142.9 42.0 47.5 142.5 41.524 54.9 70.52050.degree. F./15.0 ksi 163.0 52.5 49.2 161.9 46.146 20.5 76.9 151.1 66.4 45.6 150.7 59.115 52.7 75.5 131.8 57.3 44.4 131.5 48.310 26.3 57.1 *156.0 54.4 41.0 155.9 45.502 55.5 78.3 *133.7 57.2 56.0 132.7 41.753 67.5 80.7 *135.1 59.7 52.3 134.3 46.317 54.9 71.5 151.1 66.4 45.6 150.7 59.115 52.7 75.5 131.8 57.3 44.4 131.5 48.310 26.3 57.12100.degree. F./15.0 ksi 69.7 54.2 48.1 69.4 47.674 25.3 36.3__________________________________________________________________________ *As-Solutioned Condition
Only about 97-98% gamma prime solutioning was achieved in the CMSX-10A and -10B materials (see Table 4) which was insufficient for the purpose of optimizing alloy mechanical properties and microstructural homogeneity. Attainment of a greater level of gamma prime solutioning, therefore, became an equal priority in tandem with improving microstructural stability at temperatures above 1900.degree. F.
To confirm the suspected composition of the TCP phase forming in the alloys, scanning electron microscope (SEM) wavelength dispersive x-ray (WDX) microchemistry analyses of CMSX-10B test bar contained needles was undertaken and compared to the alloys gamma and gamma prime compositions. The results, reported in Table 7 below, confirm that the needles were enriched in Cr, W and Re.
TABLE 7__________________________________________________________________________CMSX-10B Micro-Chemistry AnalysesCast Test Bar (VF 831)Transverse Section. Bottom Bar Location.Solutioned to 2465.degree. F.Aged 1975.degree. F./19.5 Mrg./AC1600.degree. F./20 Mrs./AC1400.degree. F./24 Mrg./AC__________________________________________________________________________ GAMMA NEEDLEGAMMA PHASE PRIME PHASE CONSTITUENTELEM K Z A F ELEM K Z A F ELEM K Z A F__________________________________________________________________________ALK 0.0101 1.090 0.324 1.000 ALK 0.0145 1.084 0.322 1.000 ALK 0.0116 1.107 0.347 1.000TIK 0.0069 1.007 0.930 1.051 TIK 0.0084 1.002 0.934 1.052 TIK 0.0077 1.026 0.908 1.039CRK 0.0428 1.008 0.963 1.108 CRK 0.0250 1.002 0.965 1.117 CRK 0.0390 1.028 0.949 1.083COK 0.0970 0.994 0.984 1.018 COC 0.0761 0.988 0.987 1.022 COK 0.0755 1.016 0.977 1.025NIK 0.6891 1.033 0.988 1.010 NIK 0.7270 1.026 0.991 1.005 NIK 0.6143 1.056 0.983 1.024TAL 0.0485 0.794 1.020 1.000 TAL 0.0697 0.788 1.024 1.000 TAL 0.0389 0.814 1.018 1.000W L 0.0329 0.788 0.963 1.000 W L 0.0311 0.783 0.962 1.000 W L 0.0682 0.808 0.968 1.000REL 0.0422 0.785 0.968 1.000 REL 0.0085 0.779 0.968 1.000 REL 0.1083 0.805 0.973 1.000__________________________________________________________________________ WT % WT % WT %ELEM CPS ELEM ELEM CPS ELEM ELEM CPS ELEM__________________________________________________________________________AL K 12.1800 2.87 AL K 17.9400 4.19 AL K 11.9900 3.02TI K 5.5200 0.71 TI K 6.8400 0.86 TI K 5.2500 0.79CR K 27.6400 3.98 CR K 16.4500 2.31 CR K 21.5800 3.69CO K 40.6800 9.74 CO K 32.5400 7.64 CO K 27.1700 7.42NI K 253.1300 66.84 NI K 272.3800 71.11 NI K 193.7500 57.84TA L 6.5667 5.99 TA L 9.6329 8.64 TA L 4.5259 4.70W L 4.0775 4.33 W L 3.9375 4.13 W L 7.2620 8.71RE L 4.6000 5.56 RE L 0.9500 1.13 RE L 10.1300 13.82TOTAL 100.00 TOTAL 100.00 TOTAL 100.00__________________________________________________________________________
The calculated N.sub.V3B numbers were 1.90 for CMSX-10C and 1.95 for CMSX-10D. Re was maintained at around 5% while W was further reduced to improve stability in these specimens. Alloy Ta was increased since it did not participate in TCP formation and the Ta/W ratio was effectively improved, which assisted with alloy castability. Chromium was reduced in the -10C specimens but increased to 4.0% in the -10D specimens to provide an opportunity to determine the suitability of the Cr levels from a hot corrosion standpoint. Co was reduced in both materials, significantly in the -10D specimen, while Al+Ti level was also reduced to assist in achieving more complete gamma prime solutioning. Creep-rupture results for the two specimens are reported below in Tables 8 and 9, respectively. Even though the -10D alloy specimens were observed to exhibit full gamma prime solutioning (as opposed to 99.-99.5% for CMSX-10C) the alloys greater Cr content, which necessitated a lower Al+Ti level, effected lower properties than attained with CMSX-10C. However, both materials exhibited improved alloy stability and higher temperature properties, so that attempts to balance the alloys low and high temperature creep response were favorable.
TABLE 8__________________________________________________________________________CMSX-10C CREEP-RUPTURE TIME IN HOURS RUPTURE TIME % % FINAL CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 556.1 31.4 30.5 555.2 26.615 316.1 376.3 636.6 43.9 37.5 636.4 38.460 416.6 455.4 609.2 23.3 34.7 607.6 19.074 410.6 460.6 635.7 44.9 45.6 635.3 34.991 407.3 443.4 612.8 43.5 38.8 611.9 41.951 409.8 438.71850.degree. F./36.0 ksi 252.2 30.2 37.8 252.0 22.033 61.1 166.3 298.1 41.3 39.0 297.6 37.953 170.3 194.8 231.1 33.6 39.5 230.2 29.689 127.8 146.01922.degree. F./20.3 ksi 492.4 52.5 52.4 491.6 48.922 176.5 251.7 529.8 38.6 45.5 528.9 33.353 269.6 306.2 637.5 48.9 43.3 635.2 45.804 189.5 318.32000.degree. F./18.0 ksi 258.8 35.0 41.5 258.7 32.444 74.2 127.5 293.1 49.2 44.1 292.1 42.079 145.6 170.9 221.9 43.0 48.5 220.9 33.507 55.6 123.3 266.1 35.1 44.0 264.6 33.759 113.6 143.62050.degree. F./15.0 ksi 196.6 39.7 40.3 194.1 27.755 26.0 134.8 170.4 30.1 46.3 169.2 25.624 11.1 51.4 193.2 38.1 42.9 191.9 32.288 46.5 76.5__________________________________________________________________________
TABLE 9__________________________________________________________________________CMSX-10D CREEP-RUPTURE TIME IN HOURS RUPTURE TIME % % FINAL CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 428.0 26.7 29.3 426.3 24.166 189.2 248.311850.degree. F./36.0 ksi 141.0 23.1 26.8 140.1 20.660 57.8 79.7 140.7 14.7 26.1 140.2 13.741 56.2 77.6 166.0 17.5 28.9 165.0 15.640 76.5 100.11922.degree. F./20.3 ksi 519.9 23.8 24.9 518.9 22.608 202.0 345.6 667.0 17.6 23.7 665.2 16.819 151.8 391.4 680.3 14.9 28.2 678.9 14.476 340.2 500.32000.degree. F./18.0 ksi 370.3 18.8 21.3 369.9 15.560 20.9 106.9 401.5 11.1 18.0 400.0 8.903 19.8 125.5 366.6 17.5 25.8 366.6 8.049 223.9 306.12050.degree. F./15.0 ksi 465.3 12.9 20.5 465.2 12.639 61.0 305.9 338.8 9.8 24.8 337.7 9.468 30.8 204.4__________________________________________________________________________
The acceptability of the alloys' low Cr content was confirmed through extremely aggressive short-term burner rig hot corrosion tests performed at 1650.degree. F., 1% sulfur, 10 ppm sea salt condition. FIGS. 1 and 2 illustrate the results for tests performed to 117 and 144 hours for the CMSX-10C and CMSX-10D specimens, respectively. In both cases, the materials performed similar to MAR M 247-type materials, thereby confirming the suitability of the low Cr alloy design concept.
With the above-noted results, another series of alloys, CMSX-10E, -10F, -10G, -10H, -10I, and -12A were designed, produced and evaluated. The alloys explored Re level ranging 4.8-6.3%, 2.2-3.0% Cr level, 4.7-7.6% Co level and the remainder balanced to maintain castability, improve solutionability end improve phasial stability. The N.sub.v3B number ranged between 1.81-1.89.
One of the series, CMSX-10F, contained 0.02% C and 0.02% B. These additions were observed to improve casting yield and may have assisted in providing more consistent control of single crystal cast article orientation. However, the melting point depressants, C and B, restricted the specimen's response to solution heat treatment. The CMSX-10F creep-rupture properties are reported in Table 10 below.
TABLE 10__________________________________________________________________________CMSX-10F CREEP-RUPTURE TIME IN HOURS RUPTURE TIME % % FINAL CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 616.0 18.1 22.4 615.8 16.898 439.9 477.6 666.6 45.6 48.0 666.4 43.261 464.6 492.3 603.1 25.3 24.3 602.5 24.281 398.4 444.01850.degree. F./36.0 ksi 243.9 19.6 28.2 243.0 18.045 129.1 160.9 285.9 26.8 32.1 285.5 25.701 187.8 206.0 258.6 19.2 29.1 258.3 18.175 168.3 189.51922.degree. F./20.3 ksi 499.5 40.0 41.0 498.5 37.756 208.2 272.6 649.2 55.6 52.9 648.3 51.045 197.6 338.8 361.0 15.8 21.9 357.7 2.599 273.2 335.72000.degree. F./18.0 ksi 233.4 39.6 51.7 233.4 37.881 100.8 133.2 276.1 43.7 52.8 274.4 36.762 115.1 155.9 290.0 36.7 47.3 289.1 33.304 125.3 162.12050.degree. F./15.0 ksi 255.4 28.7 36.6 255.0 27.426 67.4 131.0 255.1 33.4 43.1 254.4 23.737 50.9 118.7__________________________________________________________________________
The CMSX-10E, G, H and I, plus CMSX-12A creep-rupture specimen results are reported below in Tables 11, 12, 13, 14, and 15, respectively. The results show a general improvement to alloy creep-rupture strength above 1900.degree. F. while maintaining extremely good strength at lower temperatures.
TABLE 11__________________________________________________________________________CMSX-10E CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 664.5 31.4 36.3 663.5 30.435 436.5 470.8 604.4 35.1 36.7 603.3 33.371 253.7 355.9 582.5 41.5 36.1 581.7 39.792 78.9 329.3 553.5 35.9 37.0 552.5 33.172 326.4 357.11850.degree. F./36.0 ksi 237.9 29.3 32.0 257.0 22.734 149.4 170.3 199.2 18.4 32.1 198.6 16.261 122.4 139.4 260.5 33.6 33.4 259.7 31.315 139.9 174.01922.degree. F./20.3 ksi 810.6 36.6 33.0 on.4 33.323 210.2 378.2 800.9 35.3 36.4 799.1 32.405 339.7 434.2 839.9 39.0 33.4 859.6 37.036 364.6 465.22000.degree. F./18.0 ksi 362.8 27.7 29.3 362.4 24.887 98.4 177.3 411.2 29.4 27.0 409.9 26.426 173.6 215.6 369.7 15.3 28.2 368.8 12.941 170.3 221.9 379.7 26.4 26.1 379.2 27.656 177.9 206.62050.degree. F./15.0 ksi 476.9 21.8 23.4 476.3 18.233 196.6 255.9 418.4 27.5 24.7 417.5 25.854 180.0 227.3 397.7 19.0 23.8 396.8 17.522 112.6 198.2__________________________________________________________________________
TABLE 12__________________________________________________________________________CMSX-10G CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1700.degree. F./55.0 ksi 671.8 19.6 28.6 670.5 14.775 447.2 508.1 693.6 26.0 24.2 691.7 21.750 441.2 493.4 724.9 23.3 29.7 723.2 19.913 464.8 520.4 582.5 18.6 20.1 581.1 15.200 77.0 356.7 681.2 20.9 24.1 679.2 19.115 65.4 314.8 538.4 21.6 17.5 538.3 17.837 242.1 308.7 523.0 17.7 21.8 522.4 14.157 234.3 308.0 569.7 17.5 19.8 568.5 15.035 287.0 354.91800.degree. F./36.0 ksi 773.2 29.6 29.3 773.8 28.826 315.0 539.9 719.7 29.5 28.5 717.8 27.266 321.2 486.4 741.6 28.0 25.9 740.3 24.870 284.5 464.2 682.8 45.6 34.7 681.1 39.289 409.1 452.4 764.0 23.2 33.7 764.0 22.884 543.6 586.6 790.4 41.4 35.6 789.4 38.172 511.6 565.3 799.1 27.0 32.3 797.4 25.737 529.8 579.11850.degree. F./36.0 ksi 334.4 19.3 30.2 351.9 16.000 246.7 271.4 344.5 28.5 31.9 344.3 26.174 220.8 241.9 315.4 23.7 30.7 315.1 23.5711 183.4 205.61922.degree. F./20.3 ksi 753.4 31.7 34.8 753.2 27.914 362.3 462.1 728.0 31.5 33.5 7237.1 28.362 281.1 422.2 731.6 34.3 38.8 730.5 30.770 339.3 437.31976.degree. F./28.1 ksi 95.4 29.3 29.4 94.9 22.842 41.5 50.9 95.7 26.7 27.2 94.7 20.130 45.8 54.7 104.6 30.4 33.2 104.4 27.517 41.8 54.4 100.8 25.6 33.1 98.9 21.577 40.2 58.1 95.8 25.9 28.0 93.6 19.748 41.1 51.4 110.0 29.3 30.3 108.0 22.669 48.5 60.1 108.2 43.8 104.8 45.8 104.3 48.62000.degree. F./18.0 ksi 464.4 23.1 21.3 463.6 18.190 276.7 293.5 411.9 18.3 23.0 410.4 15.347 103.5 227.6 370.0 27.0 38.7 369.8 25.326 7.6 47.32012.degree. F/14.5 ksi 790.2 31.2 34.9 788.7 24.939 299.9 406.0 671.4 23.6 23.7 670.3 13.397 303.3 396.3 512.1 22.6 28.1 510.4 21.094 192.5 277.7 651.7 27.4 39.7 651.3 16.328 316.7 434.7 754.6 29.7 25.4 753.1 24.032 193.8 388.7 008.3 17.7 18.3 -- -- -- -- 758.9 30.8 25.4 758.7 24.090 388.7 438.2 740.0 19.8 20.5 739.5 15.962 316.4 426.7 671.5 26.4 23.8 669.3 15.578 359.8 412.42050.degree. F./14.0 ksi 410.8 22.9 27.4 410.0 18.655 225.4 272.2 283.5 18.0 31.2 283.5 15.303 156.4 191.2 320.0 15.8 17.4 318.3 12.979 156.4 191.2 389.7 22.0 22.1 389.7 18.488 29.9 189.1 381.4 27.0 24.1 381.1 24.758 69.5 197.92100.degree. F./12.0 ksi 254.4 12.7 30.4 252.9 8.984 108.4 185.5 419.8 20.5 25.0 419.8 18.917 201.1 274.32100.degree. F./12.5 ksi 331.4 16.9 21.7 331.1 15.069 25.2 83.2 367.7 19.2 23.2 366.5 17.530 75.2 177.4 387.3 15.8 17.2 385.4 12.742 236.9 282.0 383.1 34.1 32.4 381.6 32.135 10.5 164.3__________________________________________________________________________
TABLE 13__________________________________________________________________________CMSX-10M CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 563.4 23.2 27.2 563.2 22.669 318.5 366.2 553.1 24.5 23.0 552.7 21.324 373.1 402.8 526.9 20.7 27.3 526.4 19.715 358.2 390.7 594.5 35.1 41.4 594.4 32.090 328.8 372.81850.degree. F./36.0 ksi 242.9 24.3 20.1 242.2 20.686 107.3 155.6 221.9 17.0 21.0 221.0 13.888 115.9 150.4 223.4 21.3 21.0 221.7 19.196 128.4 144.71922.degree. F./20.3 ksi 520.6 26.1 29.3 520.4 23.183 234.3 319.1 470.4 26.3 21.2 469.2 19.333 176.1 253.2 574.7 16.8 23.0 573.0 14.411 282.1 373.02000.degree. F./18.0 ksi 434.0 21.5 18.7 432.1 20.234 103.5 233.1 437.3 27.1 33.8 437.3 25.306 182.6 240.8 430.7 24.6 20.4 430.7 23.244 68.8 192.1 430.1 21.1 19.3 428.9 19.050 73.7 213.82050.degree. F./15.0 ksi 366.1 16.3 12.0 365.5 11.326 239.8 273.3 384.0 17.4 16.0 382.3 12.055 168.2 242.9 420.2 12.2 13.3 418.6 10.017 127.3 273.2__________________________________________________________________________
TABLE 14__________________________________________________________________________CMSX-10 1 CREEP RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 565.1 35.2 32.0 564.8 29.774 297.0 368.9 581.9 32.4 29.3 580.2 28.689 371.9 402.5 514.1 24.1 30.2 514.1 21.207 318.3 358.21850/36.0 260.5 25.0 24.8 259.3 23.255 156.7 175.3 247.5 22.4 29.1 245.7 17.730 131.0 169.0 245.1 23.7 29.0 246.1 20.277 137.6 156.71922/20.3 916.3 24.9 30.3 914.8 22.465 472.9 549.3 934.8 32.2 33.0 934.8 30.165 353.7 475.2 863.6 27.8 28.5 862.9 27.057 295.6 442.51976/28.1 116.1 19.5 20.1 116.1 19.155 57.4 70.1 65.6 22.9 20.6 64.2 21.368 17.8 26.4 91.6 23.2 25.3 90.4 15.544 37.6 49.72000/18.0 430.1 22.7 25.7 429.2 18.449 58.9 193.0 483.8 19.8 25.1 483.8 17.860 102.4 245.42050/15.0 397.7 17.0 30.0 397.3 13.264 239.8 292.9 487.7 21.4 21.9 487.1 18.854 248.2 318.4 468.3 18.4 25.5 467.9 15.800 194.1 300.12100/12.0 501.3 10.1 15.9 498.7 0.615 -- -- 401.3 16.8 26.3 399.7 15.429 6.6 25.5 210.6 11.5 12.7 210.3 0.373 -- --__________________________________________________________________________
TABLE 15__________________________________________________________________________CMSX-12A CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 491.9 40.2 41.6 491.8 38.605 254.0 293.7 420.4 23.5 31.9 420.3 19.299 234.9 277.9 383.4 25.3 25.2 382.9 22.920 198.1 244.3 456.2 24.1 26.1 454.5 22.582 89.9 265.5 458.0 30.7 32.7 457.1 26.155 253.2 292.8 386.8 30.1 30.4 386.3 27.031 172.7 216.9 403.7 34.5 28.8 402.7 31.033 140.2 204.9 398.7 21.6 23.5 398.4 20.277 181.1 236.11850/36.0 208.5 32.1 40.5 208.3 21.248 100.8 119.6 189.5 21.2 26.2 189.4 20.461 99.1 116.31922/20.3 829.6 46.5 45.3 828.8 44.488 315.8 400.7 797.0 33.5 32.5 796.9 32.856 315.3 400.52000/18.0 500.3 31.7 29.6 499.2 24.922 218.4 268.5 227.6 36.5 41.2 227.1 26.825 90.6 113.9 430.4 18.5 23.3 430.4 18.180 18.180 234.12050/15.0 424.8 17.0 27.5 423.3 15.832 263.5 301.2 366.1 26.2 42.8 365.5 20.399 146.6 197.8 400.8 18.2 25.4 400.7 16.910 184.6 251.32100/12.0 255.4 25.8 45.8 263.6 22.920 64.1 125.8 483.90 10.1 19.3 482.7 8.602 378.6 421.9 325.1 7.1 16.6 325.7 4.315 268.8 302.3__________________________________________________________________________
Varying the primary gamma prime aging treatment was explored with most of the development activity concentrated on achieving optimized gamma prime size and distribution through longer soak times at 1975.degree. F. (see Table 4) since higher temperature aging treatments accelerated TCP phase formation during the aging cycle.
Ten to twenty-one hour soak times at 1975.degree. F. were successful since they provided average gamma prime particles of about 0.5 um dimension. However, it appeared that shorter primary gamma prime aging time at higher temperature may be more practical, once more stable microstructures were defined.
Microchemical SEM WDX needle particle analyses was performed on a failed CMSX-10G creep-rupture specimen. The specimen, tested at 1976.degree. F./28.1 ksi condition, exhibited needles in its microstructure. The results of the analysis are reported in Table 16 below and indicate, again, that the needles formed in this class of material are particularly rich in Re, but are also enriched with Cr and W.
TABLE 16______________________________________CMSX-10G1976.degree. F./28.1 ksi104.6 HRS.______________________________________ELEM K Z A F______________________________________CRK 0.0426 1.105 0.793 1.049COK 0.0584 1.094 0.888 1.086NIK 0.1740 1.140 0.910 1.116W L 0.2107 0.941 0.972 1.000REL 0.4767 0.941 0.979 1.000______________________________________NEEDLE CHEMISTRY WT %ELEM CPS ELEM______________________________________CRK 113.7000 4.63COK 112.1100 5.54NIK 305.1425 15.02W L 134.8988 23.03REL 276.4000 51.76 100.00______________________________________
A standardized test for resistance to recrystallization was performed on a CMSX-10G test bar. The test method and the results are reported in Table 17 below. The test results indicate that the CMSX-10G specimen exhibited similar resistance to cast process/solution treatment/bonding process recrystallization level in comparison to CMSX-4 alloy.
TABLE 17______________________________________*Method: A controlled level of compressive stressis imparted on the entire surface of anas-cast test bar. The bar is then solutionheat treated. Following solutiontreatment, the bar is sectioned and thetransverse section is observedmetallographically. Depth of recrystallizationmeasurements are taken.*Evaluation Standards: Resistance To RX Anticipated in BladeAlloy Depth of RX Castings______________________________________CMSX-4 .004" Very GoodSX 792 Entire Bar Very PoorCMSX-10G .004" Very Good______________________________________
The CMSX-10Ga -10Ia, -12B, -12C, -10J, -10Ri and -12Ri compositions were defined and evaluated. No creep-rupture properties were generated for the CMSX-10J specimen, although test bars were produced and a solution heat treatment developed. Again, the inclusion of C and B in the -10J composition appeared to have positive effect to single crystal test specimen yield. Additionally, the lower levels of C and B than evaluated in CMSX-10F specimen, particularly lower B, made the material more amenable to solution heat treatment. Ninety-eight to ninety-nine percent gamma prime solutioning was achieved, as opposed to the approximate 95% level typical of the CMSX-10F composition.
The CMSX-10Ga and -10Ia alloys were designed with N.sub.v3B numbers of about 1.70. These alloy specimens contain about 2.5% Cr, 3.3-4.0% Co, 5.6-6.0% Re, greater Ta/W ratio, reduced Cb, and reduced Al+Ti content. Such reduction to Cb+Al+Ti level improved the solutioning characteristics of the materials (see Table 4), plus achievement of increased alloy stability. Both specimens exhibited nearly full gamma prime solutioning.
The lowered N.sub.v3b number continued to show effectiveness in providing better creep-rupture capability at temperature greater then 1900.degree. F., while maintaining extremely good creep-strength at lower temperature. CMSX-10Ga test results from specimens produced with improved casting process controls exhibited 700 hours or more life with about 475hours required to creep to 1.0% for 1800.degree. F./36.0 ksi condition. Fur higher temperature exposure, the specimen provided the improved average life of about 500 hours at 2050.degree. F./15.0 ksi condition and average 1.0% creep deformation that occurred at about 250 hours, as indicated by the results reported in Table 18 below.
TABLE 18__________________________________________________________________________CMSX-10Ga CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 500.7 19.9 25.2 499.7 19.541 316.5 360.1 584.2 29.1 25.4 583.9 26.395 370.0 401.8 505.1 22.6 29.8 503.7 18.212 307.4 347.3 730.9 42.0 42.8 730.7 40.216 477.6 516.1 460.6 428.51850/36.0 184.5 41.0 33.90 183.2 37.154 82.3 94.5 291.5 27.3 29.9 290.2 19.323 191.6 207.8 279.5 33.9 32.5 278.1 29.054 155.3 180.5 323.9 30.9 36.6 322.9 29.218 194.1 217.1 326.5+ 8.9 12.6 -- -- -- -- 295.2+ 33.3 33.5 -- -- -- -- 174.1 162.3 300.1+ 22.8 22.4 -- -- -- --1976/28.1 88.6 34.9 33.9 88.6 25.502 39.7 48.9 100.1 28.2 29.2 96.8 19.706 53.9 61.3 107.9 28.8 31.4 107.0 23.657 51.1 62.1 87.1 27.0 33.8 87.1 24.177 39.2 48.5 82.8 23.3 27.7 81.0 17.301 20.6 38.0 88.2 31.2 35.2 86.4 24.463 33.6 44.4 83.7 34.0 34.3 83.4 29.718 36.3 45.1 114.1 24.3 26.3 113.0 20.544 62.1 73.2 122.3 18.3 21.3 120.7 15.740 76.5 86.0 117.7 23.2 25.6 117.5 22.284 78.0 85.3 (INTERRUPTED TESTS) 40.2 1.036 39.9 -- 43.4 1.187 42.3 -- 99.3+ 60.1 38.8 -- -- -- -- 127.9 41.5 34.5 127.5 37.493 51.2 62.6 96.8 22.9 27.9 96.5 20.124 45.9 54.4 118.9 31.3 27.1 118.0 24.603 49.5 61.3 111.1 25.0 22.8 110.2 21.521 46.4 58.0 96.6+ 24.1 22.9 -- -- -- -- 120.3+ 25.8 29.4 -- -- -- -- 113.0+ 27.6 20.5 -- -- -- --1976/18.85 (INTERRUPTED TESTS) 261.5 1.015 260.3 -- 207.2 1.017 204.6 -- 592.1 25.8 22.4 590.4 23.596 210.1 305.9 570.7 27.2 26.9 570.7 26.289 293.3 332.6 535.5 19.3 23.9 535.2 17.513 308.2 344.2 240.5 307.62050/15.0 536.8 28.5 27.5 535.6 20.662 232.3 321.3 497.0 23.7 23.9 496.2 17.600 260.3 317.9 514.8 23.4 24.4 513.1 12.500 230.4 340.4 454.1 16.6 35.2 453.7 15.476 263.2 317.1 420.3+ 33.7 33.2 -- -- -- -- (INTERRUPTED TESTS) -- -- -- 239.1 -- -- -- -- 189.6 -- -- -- -- 280.3 -- 560.1+ -- 22.9 -- -- -- --2012/14.5 536.6+ 7.3 8.1 -- -- -- -- 424.62100/12.0 354.1 14.8 36.5 353.8 12.646 91.2 219.1 343.4+ -- 27.2 -- -- -- -- 91.4 147.2 491.0+ -- 16.7 -- -- -- --1700/50.0 +__________________________________________________________________________ + Machined From Blade Specimen
1% creep strength is a significant property. Limiting creep strains to 1.0% and 2.0% is extremely important to gas turbine component design, since a component's usefulness is generally measured by its resistance to creep to an approximate 1-2% level, not its ultimate rupture strength. Many prior art alloys may exhibit attractive rupture strength at the >1900.degree. F. level, however, they lack the level of useful strength, i.e., creep strength to 2.0%, that this invention provides in tandem with its far superior strength in test conditions below 1900.degree. F.
The CMSX-10Ia specimens also provided significantly increased creep strength at the higher temperature extremes, but it did not appear to develop strength as good as the CMSX-10Ga specimens in lower temperature tests, as indicated by the results in Table 19 below.
TABLE 19__________________________________________________________________________CMSX-10 1a CREEP RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 532.0 34.8 32.7 530.7 33.000 259.1 312.5 474.6 23.8 29.2 473.1 22.886 201.0 269.2 374.3 20.0 21.0 372.8 19.238 171.1 214.71850/36.0 256.0 28.7 28.5 256.0 27.867 135.4 157.1 251.4 34.4 30.3 250.7 33.055 121.6 144.6 217.8 30.5 22.4 217.2 27.000 94.2 117.91976/28.1 85.7 27.5 28.9 83.8 21.754 36.9 46.2 81.9 33.6 31.8 81.0 24.384 32.1 42.1 68.9 26.1 25.8 67.6 20.960 23.1 32.42012/14.5 930.2 10.0 14.4 928.4 9.649 104.6 455.7 844.4 17.7 23.2 842.8 16.132 339.7 502.3 864.2 15.3 11.9 862.8 14.558 179.9 453.42050/15.0 510.2 17.8 19.7 508.4 15.703 187.2 312.7 528.6 17.9 24.2 527.0 14.873 293.7 364.3 438.8 14.3 11.3 436.4 13.556 56.0 136.92100/12.0 616.4 19.0 19.1 616.3 14.112 60.0 422.5 467.7 19.1 26.1 466.0 11.373 273.6 374.8__________________________________________________________________________
Similarly, CMSX-12B, with Nv3B at 1.80 level and additional chemistry balance as presented in Table 1, provided attractive creep strength at test condition greater than 1900.degree. F., but did not perform quite as well as CMSX-10Ga in lower temperature tests, as indicated by the results reported in Table 20 below.
TABLE 20__________________________________________________________________________CMSX-12B CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1076.degree. F./28.1 ksi 91.7 15.3 17.2 91.2 14.070 43.9 56.2 72.6 19.4 23.2 72.6 17.396 27.4 36.8 14.1 5.0 1.3 12.7 2.300 8.6 11.9 98.1 16.9 17.6 96.4 13.670 17.8 38.9 108.2 25.2 24.1 108.0 22.794 43.8 58.7 106.9 24.7 24.2 106.3 21.024 46.1 60.1 104.8 24.0 26.8 104.3 20.094 45.8 58.7 104.3 26.8 21.4 103.2 22.347 48.6 60.81800/36.0 515.0 24.7 24.2 513.3 19.468 320.1 358.0 536.4 23.2 21.1 530.8 22.184 318.3 359.5 304.7 13.2 19.9 302.9 12.582 166.0 200.81850/36.0 262.6 18.4 23.1 262.4 17.660 12.5 142.22012/14.5 1031.3 17.2 18.5 1029.5 15.113 428.0 703.7 1078.7 15.6 20.0 1076.7 15.217 704.2 819.2 839.4 14.9 22.8 839.2 9.282 607.6 677.7 836.9 23.2 21.0 834.8 18.024 591.1 658.5 722.0 16.4 21.1 721.9 15.913 170.8 333.6 711.3 14.5 18.8 710.8 12.490 381.9 531.5 711.9 18.3 20.0 711.4 16.201 447.7 530.72050/15.0 507.5 10.0 10.1 507.2 9.394 70.4 360.4 434.0 17.5 16.8 434.0 13.847 241.7 309.02100/12.0 487.5 25.3 20.3 486.6 20.986 18.2 224.7 444.9 7.8 11.0 442.2 3.884 347.3 413.6__________________________________________________________________________
Alloy composition has the greatest effect on ultimate creep strength. However, some of the variation experienced between alloy derivatives, and particularly for tests exhibiting inconsistent results for a given alloy, can be caused by variation in casting process condition. Casting process thermal gradient variation affects the cast specimen dendrite arm spacing and ultimately, its response to solution heat treatment and primary gamma prime aging treatment. It must, therefore, be recognized that much of the creep-rupture results reported herein may have been generated under non-optimized conditions and may be capable of improvement. Improved casting process control may provide casting microstructures more amenable to solution treatment and study to determine the appropriate primary gamma prime aging treatment to provide the optimum gamma prime particle size, which may result in further mechanical property enhancement.
The CMSX-12C composition was designed to provide a calculated N.sub.v3B number of 1.70. The alloy Cr content was designed at 2.8% and Co set at 3.5% aim for this alloy. An attractive Ta/W ratio was maintained while Re content was moderate at 5.8%. The alloy's Al+Ti content was reduced, in comparison to the CMSX-12A and CMSX-12B specimens, to provide improved alloy response to solution procedure.
Similar to the CMSX-10Ga specimen, the CMSX-12C specimen exhibited an improved balance of creep strength for test condition ranging 1800.degree.-2100.degree. F., as reported in Table 21 below.
TABLE 21__________________________________________________________________________CMSX-12C CREEP-RUPTURE FINAL CREEP TIME IN HOURS RUPTURE TIME % % READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1800.degree. F./36.0 ksi 465.2 31.8 21.0 464.5 30.543 173.0 262.4 918.0 26.1 31.2 517.9 24.947 268.1 334.3 480.9 28.3 33.6 480.0 27.715 239.7 297.5 713.3 30.0 28.0 713.2 28.899 455.0 503.71830/36.0 237.7 28.2 26.8 237.7 27.054 11.4.4 145.3 221.2 22.9 27.3 220.7 22.491 111.3 135.2 231.7 23.3 24.7 231.0 22.614 121.0 144.7 338.9 26.2 27.0 337.5 23.256 216.0 236.3 300.1+ -- -- -- -- 295.2+ 33.3 33.5 -- -- -- --1976/28.1 73.2 20.8 29.1 72.2 17.768 29.3 38.9 79.0 28.1 31.8 77.4 21.533 31.4 41.4 83.8 21.6 26.5 82.3 17.860 34.2 63.8 67.6 31.2 29.8 67.5 24.177 25.5 34.6 113.0+ 79.4 30.8 76.2 32.8 68.8 29.3 118.1 26.0 28.0 116.2 23.822 49.3 62.0 -- -- 29.0 -- (INTERRUPTED TESTS) -- -- 29.4 -- -- -- 32.9 --1976/18.85 ksi 65.4 218.0 271.9 -- (INTERRUPTED TESTS) -- -- 168.9 -- -- -- 116.4 -- 240.52012/14.5 1001.8 23.6 20.0 1000.7 23.348 349.6 542.8 865.5 20.7 26.1 864.8 18.807 418.2 569.3 61.9 267.12050/15.0 509.4 13.7 22.3 508.0 12.860 158.1 315.1 546.4 15.6 23.6 546.4 14.044 323.0 404.0 180.8 44.2 240.7 190.92100.degree. F./12.0 404.3 11.2 21.6 404.3 8.438 290.1 326.4 321.7 9.5 15.0 320.4 7.671 156.6 254.1 545.1 8.2 22.1 542.2 5.351 236.0 452.9 457.4 8.6 23.4 455.8 6.612 309.3 380.92100.degree. F./12.0 371.4+ 14.2 17.1 -- -- -- --1730.degree. F./30.0 446.9+ 16.8 20.4 -- -- -- --1976.degree. F./18.85 476.6+ 19.2 27.1 -- -- -- -- 459.9+ 30.6 30.2 -- -- -- --1976.degree. F./28.1 ksi 120.5+ 24.1 22.9 -- -- -- -- 99.6+ 25.8 29.4 -- -- -- --2050.degree. F./15.0 469.8 -- 30.8 -- -- -- -- 485.4 -- 22.7 -- -- -- --2012.degree. F./14.5 ksi 638.1 521.8 267.1 61.9 395.7__________________________________________________________________________
With improved casting process controls, this specimen has shown the following 1.0% longitudinal creep strengths, as reported in Table 22 below.
TABLE 22______________________________________ Time to 1.0% StrainTest Condition Hrs______________________________________1800.degree. F./36.0 ksi 4552100.degree. F./12.0 ksi 309.3______________________________________
Both alloys provide similarly greater rupture strength than CMSX-4 alloy at condition to 1976.degree. F. Respective improvements to metal temperature capability are reported below in Table 23.
TABLE 23______________________________________ Approx. Strength AdvantageTemperature Relative to CMSX-4______________________________________1800.degree. F. 40.degree. F.1850.degree. F. 45.degree. F.1976.degree. F. 43.degree. F.Based on 1.0% creep strength, the respective approximateadvantages are:1800.degree. F. +46.degree. F.1850.degree. F. +60.degree. F.1976.degree. F. +55.degree. F.______________________________________ Note that the comparison in not density corrected.
For test temperature above 1976.degree. F., the test results indicate that the CMSX-10Ga and CMSX-12C specimens provided slightly lower strength than CMSX-4 alloy. The reduction in strength advantage for these alloys is believed to be the result of TCP phase formation. To address this issue, the alloys CMSX-10Gb, CMSX-10L, CMSX-12Ca, and CMSX-12E, are designed with N.sub.v3B number as low as 1.50 (see Table 1) to provide greater phasial stability, and effect much improved high temperature creep-strength while maintaining most of the creep advantage demonstrated for the 1800.degree.-1976.degree. F. test regime.
The CMSX-10Ri and CMSX-12Ri compositions were designed at the 1.91 and 1.92 N.sub.v3B levels, respectively. These specimens were subjected to the most extensive testing of properties. They were designed with 2.65% and 3.4% respective Cr levels, with other features remaining similar to the aforementioned alloy design considerations. The properties generated for these two materials confirm the overall invention design concept with the other material iterations able to provide similar physical properties and relatively better blends of mechanical properties.
The CMSX-10Ri and CMSX-12Ri specimens' respective creep-rupture capabilities are reported below in Tables 24 and 25.
TABLE 24__________________________________________________________________________CMSX-10(Ri) CREEP-RUPTURE TIME RUPTURE FINAL IN HOURS TIME % % CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi 227.3 21.2 33.8 225.4 14.359 52.8 131.5 231.6 19.3 31.0 231.3 16.671 51.0 125.1 223.4 17.0 22.3 223.3 15.360 68.5 126.61750/50.0 425.9 18.3 33.7 425.6 16.047 303.4 334.7 428.0 18.4 29.7 427.3 16.229 309.2 343.0 460.8 17.1 25.7 459.0 15.308 314.7 360.31800/36.0 698.5 39.9 34.3 696.8 36.980 492.8 521.5 676.3 28.3 33.3 674.5 27.221 479.0 513.8 692.9 38.5 31.3 692.2 36.494 469.3 504.91850/36.0 291.2 34.1 33.1 291.1 31.774 194.1 210.4 260.0 29.3 32.1 258.8 25.321 170.2 186.4 272.3 34.5 31.8 271.1 30.940 169.3 187.11850/27.56 614.0 52.0 42.0 613.5 50.482 365.8 415.5 576.3 49.7 39.0 575.9 49.193 345.1 368.2 481.1 40.4 35.4 480.7 38.294 309.3 335.41976/28.1 76.2 23.5 31.7 75.9 22.130 38.6 46.7 80.5 19.0 26.3 79.8 14.665 44.3 51.3 99.7 26.2 28.1 98.9 23.480 40.4 54.0 (INTERRUPTED TESTS) 41.4 -- 37.0 -- 40.5 --1976/18.85 265.6 29.5 35.7 264.7 29.010 158.7 184.8 278.8 51.4 38.8 278.1 46.026 82.0 155.0 (INTERRUPTED TESTS) 139.7 -- 128.8 -- 100.1 --2012/14.5 490.8 40.2 33.5 490.5 37.678 286.5 335.3 447.0 37.0 41.5 445.0 32.814 291.4 319.9 (INTERRUPTED TESTS) -- -- 113.5 -- -- -- 205.7 -- -- -- 202.2 --2050/15.0 251.9 33.6 35.9 250.0 25.559 100.0 149.5 318.9 27.1 30.0 318.2 23.149 177.5 221.2 (INTERRUPTED TESTS) -- -- 181.0 -- -- -- 95.5 -- -- -- 34.5 --2100/12.0 400.3 17.9 27.2 400.1 17.877 102.8 225.0 362.1 15.3 22.9 361.8 14.986 125.7 217.2 389.5 19.9 24.0 388.2 19.510 41.1 180.7__________________________________________________________________________
TABLE 25__________________________________________________________________________CMSX-12(Ri) CREEP-RUPTURE TIME RUPTURE FINAL IN HOURS TIME % % CREEP READING TO REACHTEST CONDITION HOURS ELONG. RA t. hours % deformation 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi 209.8 22.3 23.1 209.3 19.958 2.6 46.3 191.4 14.3 17.4 189.7 12.483 1.6 42.5 189.6 22.0 22.8 188.3 19.080 1.5 22.31750/50.0 448.1 26.7 26.6 447.9 26.054 302.3 335.5 403.1 19.0 26.9 401.9 18.566 210.0 290.2 435.0 19.4 26.9 434.4 18.503 89.1 284.11800/36.0 604.5 34.7 29.9 604.3 34.170 349.4 407.1 583.6 37.0 32.0 581.3 30.443 391.3 420.6 627.0 25.3 29.7 627.0 24.417 412.4 455.81850/36.0 302.9 33.1 31.3 301.7 29.034 198.9 215.1 314.4 32.0 27.1 312.7 27.479 201.4 220.21976/28.1 90.0 19.7 29.2 88.5 16.627 33.9 48.8 91.5 30.3 31.9 90.6 29.001 37.3 47.9 68.6 35.3 32.2 68.4 28.869 17.3 27.6 (INTERRUPTED TESTS) 43.7 -- 41.4 -- 38.7 --2012/14.5 324.1 31.4 30.8 323.9 24.403 160.1 207.7 481.4 30.9 31.9 481.1 29.581 129.9 299.6 551.7 29.9 31.1 549.2 25.622 304.4 375.5 (INTERRUPTED TESTS) 256.1 -- 182.8 -- 101.5 --2050/15.0 243.4 36.1 35.0 243.3 20.614 143.1 174.22100/12.0 374.8 12.1 20.3 374.7 11.743 166.6 280.4 463.6 15.4 25.9 463.3 13.594 245.7 363.3 488.0 20.3 25.9 487.1 19.550 25.7 118.9__________________________________________________________________________
The method and results of W and Re microstructural segregation investigation undertaken on fully solutioned and partially solutioned CMSX-12Ri test specimens are reported in Table 26 below. The investigation indicated that it is desirable to minimize the amount of microstructure-contained residual eutectic and that for fully solutioned specimens, the solution treatments developed for the invention are successful in minimizing elemental segregation, which is important in attaining optimized mechanical properties and microstructural stability.
TABLE 26______________________________________Alloy: CMSX-12 RiTest Specimen: 3/8" Diameter Solid BarSpecimen Condition: Fully Solutioned Solutioned with 2.0% Residual EutecticAnalyses Method: Microprobe Analyses+ Random array of 350 points across a section at right angles to the growth direction+ Seven line scans, 51.degree. apart, 50 point analyses per lineThe standard deviation of the W and Re measurements arethe measure of homogeneity______________________________________Results: Standard DeviationsCMSX-12 Ri W Re______________________________________Fully Solutioned 0.27 0.502% Residual Eutectic 0.36 0.90ComparisonTypical CMSX-4 0.57 0.60______________________________________
Table 27 below reports results of burner rig hot corrosion test undertaken with the CMSX-12Ri specimen. The measurements were taken at the bar location which experienced the maximum attack, i.e., 1652.degree. F. location, with the results showing the DS MAR M 002 alloy experienced approximately 20.times. more metal loss than the CMSX-12Ri specimen. Visual observation showed a similar result for the CMSX-10Ri alloy. Both CMSX-10Ri alloy and CMSX-12Ri alloy showed similar resistance to attack as CMSX-4 alloy based on visual specimen review at 60, 90 and 120 hours.
TABLE 27______________________________________HOT CORROSION______________________________________METHOD+ Burner Rig 1742.degree. F. (950.degree. C.) 2 ppm salt, standard fuel+ Measurements taken at point of maximum attack which was at 1652.degree. F. (900.degree. C.)+ Measurements reported were taken at the average minimum diameter of useful metal______________________________________RESULTS+ 90 Hour Test Post Test Metal LossAlloy Initial Dia. Useful Dia. Per Side______________________________________DS Mar M 002 6.88 mm 5.14 mm .87 mm (.034")CMSX-12 Ri 6.86 mm 6.75 mm .04 mm (.0016")______________________________________
Table 28 below reports the results of cyclic oxidation tests undertaken at 2012.degree. F. with March 1 gas velocity. The CMSX-12Ri specimen was similarly resistant to oxidation attack at 2012.degree. F., however, it was not as good as CMSX-4 at approximately 1886.degree. F. exposure.
TABLE 28______________________________________Cyclic Oxidation Test______________________________________15 Minute Cycles to 2012.degree. F. (1100.degree. C.),Cooled To Ambient Between CyclesMach 1 Gas Velocity89 Hours Total With 77 Hours at 2012.degree. F.______________________________________RESULT:at 1100.degree. C. CMSX-12 Ri Approx. 0.1 mm loss per side for every 300 cycles CMSX-4 Approx. 0.1 mm loss per side for every 380 cyclesat 1030.degree. C. CMSX-12 Ri Approx. .105 mm loss per side after 355 cycles CMSX-4 Approx. .03 mm loss per side after 355 cycles______________________________________
CMSX-12Ri elevated temperature tensile data is reported in Table 29 below, while the results of impact tests are reported in Table 30 below. The CMSX-12Ri elevated temperature impact strength minimum is similar to CMSX-4 and its maximum occurring at 1742.degree. F., is better.
TABLE 29______________________________________TENSILE DATACMSX-12 Ri AlloyTest 0.1% Yld 0.2% Yld UTS Elong RATemp .degree.F. LAUE ksi ksi ksi % %______________________________________1382 2.3.degree. 150.0 160.8 188.7 13 141382 2.3.degree. 153.6 165.1 190.0 13 151562 6.2.degree. 136.5 130.8 152.3 27 241562 6.2.degree. 135.0 128.9 160.1 25 231742 5.6.degree. 92.7 89.2 125.3 24 301742 5.6.degree. 99.9 106.2 129.2 24 321922 3.8.degree. 69.5 74.3 104.1 19 361922 3.8.degree. 72.4 77.6 106.0 19 36______________________________________
TABLE 30______________________________________IMPACT DATACMSX-12 Ri0.35 Inch Diameter Plain Cylindrical Specimens Test Temperature, .degree.F. 1382 1562 1742 1922______________________________________CMSX-12 Ri (1 only) 26 J 20 J 60 J 32 JCMSX-4 (Ave. of 4) 26 J 21 J 42 J 45 J______________________________________Further Impact Property ComparisonCMSX-2 Min. Impact Strength 16.5 JoulesSRR 99 Min. Impact Strength 20 Joules______________________________________
The results of CMSX-12Ri low cycle fatigue tests undertaken at 1382.degree. F. and 1742.degree. F. test conditions, with R=0, are reported in Table 31 below. The data indicates that CMSX-12Ri performance similar to CMSX-4 at 1382.degree. F. condition, while the alloy exhibits approximately 2.5 times the typical CMSX-4 life at 1742.degree. F. condition.
TABLE 31______________________________________LOW CYCLE FATIGUECMSX-12 Ri AlloyR = 0 (zero to maximum stressing)1382.degree. F. (750.degree. C.) 1742.degree. F. (950.degree. F.)PEAK STRESS PEAK STRESSksi (MPa) Cycles ksi (MPa) Cycles______________________________________142 (980) 8686 110 (760) 4427130 (900) 11950 99 (680) 15510125 (860) 20810 87 (600) 37430119 (820) >100000 75 (520) 92580______________________________________ Performance is similar to CMSX4 at 1382.degree. F. (750.degree. C.) Compared to CMSX4, at 1742.degree. F. (950.degree. C.) and in the 20000 cycle region, CMSX12 Ri exhibits 2.5 times life or 15% on strength.
Notched low cycle fatigue test results show the CMSX-12Ri is 21/2 times better than CMSX-4 out to about 30000 cycles, while at 50000 cycles and above, the alloy performance is similar to CMSX-4. The results of these tests performed at 1382.degree. F., K.sub.t =2.0 and R=0 test condition, are reported in Table 32 below.
TABLE 32______________________________________NOTCHED LOW CYCLE FATIGUECMSX-12 Ri Alloy1382.degree. F. (750.degree. C.), K.sub.t = 2.0, R = 0PEAK STRESSksi (MPa) CYCLES______________________________________113.13 (780) 4879107.33 (740) 978495.72 (660) 2847084.12 (580) 4981081.22 (560)78.32 (540) >115,00075.42 (520) >115,000______________________________________ Results are 21/2 times better than CMSX4 out to about 30000 cycles. Results are similar to CMSX4 at 50000 cycles, and above.
High cycle fatigue test results for the CMSX-10Ri alloy are reported in Table 33 below. For 1742.degree. F., 100 Hz, R=0 test condition, the alloy exhibited about 21/2 times the typical CMSX-4 lives.
TABLE 33______________________________________HIGH CYCLE FATIGUECMSX-10 Ri Alloy1742.degree. F. (950.degree. C.), 100 Hz., R = 0PEAK STRESS CYCLESksi (MPa) (M.sub.f)______________________________________81.22 (560) 15.2 .times. 10.sup.692.82 (640) 3.59 .times. 10.sup.6104.43 (720) 0.6 .times. 10.sup.6______________________________________ *Lives are 21/2 times better than CMSX4
The CMSX-10Ri and CMSX-12Ri test data indicates that adequate hot corrosion and oxidation resistance can be achieved with extremely low alloy chromium content. Additionally, extremely good thermo-mechanical fatigue tensile and impact strengths are apparent with the superalloys of this invention.
The results of alloy specimen density measurements are reported in Table 34 below.
TABLE 34______________________________________SINGLE CRYSTAL ALLOY DENSITY DATA DENSITYALLOY Lbs/In3______________________________________CMSX-10A .324CMSX-10B .324CMSX-10C .325CMSX-10D .325CMSX-10E .325CMSX-10F .323CMSX-10G .322CMSX-10Ga .322CMSX-10H .324CMSX-10I .322CMSX-10Ia .322CMSX-10J .327CMSX-10Gb (10K) .329CMSX-12A .323CMSX-12B .325CMSX-12C .326CMSX-12Ca (12D) .326CMSX-10 Ri .326CMSX-10 Ri .323______________________________________
The alloys of this invention are amenable to HIP processing. Specimens HIP treated as reported in Table 35 below, showed nearly complete pore closure and absence from incipient melting.
TABLE 35______________________________________HIP condition______________________________________1. Heat Specimens in the HIP vessel to 2455.degree. F. at minimum Argon pressure (approximately 1500 psi) and hold for 4 hours while maintaining 2455.degree. F./1500 psi condition.2. While maintaining the 2455.degree. F. operating temperature, increase the Argon pressure over 1 hour to 20 ksi. Soak specimens at 2455.degree. F./20 ksi condition for 4______________________________________ hours.
Further evaluation of the CMSX-10Ri and CMSX-12Ri alloys was undertaken. The data reported below further shows the unique capabilities exhibited by the alloys of this invention. More specifically, very attractive hot corrosion and dynamic oxidation resistance are exhibited by these alloys in tandem with exceptionally high creep-rupture, thermo-mechanical fatigue, tensile and impact strengths, despite the extremely low level of chromium content employed, thereby providing a unique blend of desirable properties.
Additional tensile data is reported in Table 36 below for the CMSX-10Ri and CMSX-12Ri alloys. These alloys were evaluated at temperatures ranging from Room Temperature (RT) to about 2100.degree. F. This data complements the data reported in Table 29 above.
TABLE 36______________________________________Tensile Data______________________________________CMSX-10 Ri AlloyTEST TEMP 0.1% PS 0.2% PS TS ELONG RA.degree.F. ksi ksi ksi % %______________________________________68 123.3 123.9 124.0 13 181202 146.2 147.2 173.2 7 21202 145.8 146.5 171.6 9 131382 144.6 147.8 174.8 6 71382 141.3 144.2 172.6 6 51562 134.7 132.3 158.1 27 321562 135.8 132.0 163.0 27 281742 95.6 90.5 136.2 23 271742 93.5 90.1 134.2 23 431922 71.8 76.0 115.4 22 341922 72.4 73.2 114.6 20 26______________________________________CMSX-12 Ri AlloyTEST TEMP 0.1% PS 0.2% PS UTS ELONG RA.degree.F. ksi ksi ksi % %______________________________________1202 132.4 132.4 154.6 12 201202 133.6 133.7 157.7 13 231382 150.0 160.8 188.7 13 141382 153.6 165.1 190.0 13 151562 136.5 130.8 152.3 27 241562 135.0 128.9 160.1 25 231742 93.1 89.3 125.3 24 301742 99.9 106.2 129.2 24 321922 73.5 76.6 104.1 19 361922 72.4 77.6 106.0 19 362102 37.7 41.5 62.9 31 522102 36.5 40.6 62.4 28 47______________________________________
Further results of impact tests, in addition to the results reported in Table 30 above, are reported in Table 37 below. Both the CMSX-10Ri and CMSX-12Ri compositions were evaluated at temperatures ranging from 1382.degree.-1922.degree. F.
TABLE 37______________________________________Impact Data IMPACT ENERGY,ALLOY TEST TEMP .degree.F. JOULES______________________________________CMSX-10 Ri 1382 31 1382 23 1562 13 1562 16 1742 12 1742 12 1922 16 1922 10CMSX-12 Ri 1382 26 1382 28 1562 20 1562 25 1742 62 1742 44 1922 32 1922 54______________________________________
Plain low cycle fatigue data for the CMSX-10Ri and CMSX-12Ri specimens is reported in Table 38 below. This data complements the data reported in Table 31 above. The tests were performed at 1382.degree. F. and 1742.degree. F., with R=0 and 0.25 Hz test conditions.
TABLE 38______________________________________Plain Low Cycle Fatigue DataPEAK STRESS, ksi LIFE, CYCLES BROKEN?______________________________________CMSX-12 Ri Alloy; 1742.degree. F., R = 0, 0.25 Hz98.6 5,403 Y92.8 21,123 Y87.0 39,811 Y81.2 47,942 Y75.4 63,454 Y72.5 67,009 Y69.6 101,019 NCMSX-12 Ri Alloy; 1382.degree. F., R = 0, 0.25 Hz150.8 6,940 Y147.9 5,284 Y142.1 8,686 Y130.5 11,950 Y124.7 20,810 Y121.8 62,950 Y118.9 106,600 NCMSX-12 Ri Alloy; 1742.degree. F., R = 0, 0.25 Hz116.0 1,220 Y110.2 4,427 Y98.6 15,510 Y87.0 37,430 Y75.4 92,580 Y72.5 123,100 Y69.6 130,070 N______________________________________
The results of notched low cycle fatigue tests (K.sub.t =2.2) undertaken with CMSX-10Ri and CMSX-12Ri specimens is reported in Table 39 below. The tests were performed at 1382.degree. F. and 1742.degree. F., with R=0 and 0.25 Hz test conditions.
TABLE 39______________________________________K.sub.t = 2.2 NOTCHED LOW CYCLE FATIGUE DATAPEAK NOMINAL STRESSKSI LIFE, CYCLES BROKEN?______________________________________CMSX-10 Ri Alloy; 1742.degree. F., R = 0, 0.25 Hz87.0 5,103 Y75.4 28,342 Y69.6 83,687 Y63.8 66,054 Y60.9 41,720 Y58.0 101,263 NCMSX-12 Ri Alloy; 1382.degree. F., R = 0, 0.25 Hz113.1 4,879 Y107.3 9,784 Y95.7 28,470 Y84.1 49,810 Y81.2 125,900 N78.3 115,200 N75.4 118,200 NCMSX-12 Ri Alloy; 1742.degree. F., R = 0, 0.25 Hz116.0 1,220 Y110.2 4,427 Y98.6 15,510 Y87.0 37,430 Y75.4 92,580 Y72.5 123,100 Y69.6 130,070 N______________________________________
High cycle fatigue data, which complements the data reported in Table 33 above, is reported in Table 40 below. The data is reported for tests undertaken with CMSX-10Ri and CMSX-12Ri specimens at the respective test conditions of: a) 1742.degree. F., R=0, 100 Hz; and b) 1022.degree. F., R=-1, 100 Hz.
TABLE 40______________________________________HIGH CYCLE FATIGUE DATAPEAK STRESS, ksi CYCLES .times. 10.sup.6 BROKEN?______________________________________CMSX-10 Ri Alloy; 1742.degree. F., R = 0, 100 Hz121.8 0.063 Y116.0 0.364 Y113.1 0.117 Y104.4 0.600 Y92.8 3.590 Y81.2 15.194 Y72.5 53.485 YCMSX-12 Ri Alloy; TESTED AT 1022.degree. F., R = -1, 100 Hz.+-.63.8 0.260 Y.+-.58.0 0.216 Y.+-.52.2 1.566 Y.+-.47.9 0.316 Y.+-.42.1 1.185 Y.+-.39.2 21.75 N.+-.36.2 27.66 N______________________________________
Bare alloy oxidation data are presented in FIGS. 3 and 4. Both Figures compare the test results for CMSX-10Ri and CMSX-12Ri alloys to results from identical tests performed on the DSM002, CMSX-4 and CMSX-4+Y (120 ppm) alloys. The data presented in these Figures complements the data reported in Table 28 above. FIG. 3 illustrates the results of tests performed out to about 375 cycles at about 2012.degree. F., while FIG. 4 illustrates the results obtained at about 1886.degree. F.
FIG. 5 illustrates a similar alloy capability comparison, except for bare alloy hot corrosion resistance. The burner-rig tests were performed to about 120 hours duration at about 1742.degree. F. with ingestion of 2 ppm salt.
Additional alloy compositions were defined in accordance with this invention for the purpose of further optimizing alloy solution heat treatment characteristics, alloy stability, and creep-rupture strength, while maintaining the extremely good oxidation, hot corrosion and thermo-mechanical fatigue strengths already achieved with the invention.
Table 41 below reports the aim chemistries for additional materials tested, which provide an even better blend of useful engineering property characteristics than the above-described alloys. These optimized compositions typically contain lower chromium and cobalt contents than the materials described in Table 1 above. Furthermore, these optimized alloys typically contain higher rhenium, lower tungsten and lower phasial stability number N.sub.v3B.
TABLE 41__________________________________________________________________________ALLOY C B Cr Co Mo W Cb Ti Al Ta Re Hf Ni Nv3B* 1 2 3 4__________________________________________________________________________CMSX-10M -- -- 2.0 1.75 .40 5.4 .08 .24 5.78 8.2 6.5 .03 BAL 1.50 11.9 6.02 14.3 20.510K Mod -- -- 1.9 2.0 .35 5.3 .05 .15 5.83 8.3 6.5 .03 BAL 1.49 11.8 5.98 14.33 20.4510M Mod -- -- 1.8 1.6 .30 5.3 .05 .12 5.90 8.2 6.6 .03 BAL 1.47 11.9 6.02 14.27 20.4CMSX-12F -- -- 2.0 1.8 .40 4.5 -- .35 5.80 8.8 6.5 .03 BAL 1.50 11.0 6.15 14.95 20.212D Mod -- -- 1.9 2.0 .40 4.8 -- .40 5.75 8.6 6.5 .03 BAL 1.49 11.3 6.15 14.75 20.312F Mod -- -- 1.8 1.6 .35 4.4 -- .12 5.92 8.7 6.6 .03 BAL 1.44 11.0 6.04 14.74 20.05__________________________________________________________________________ Key: 1 W + Re 2 Al + Ti 3 Al + Ti + Ta + Cb 4 W + Re + Mo + Ta *Calculated using PWA N35 Method
Table 42 below reports the chemistries for additional alloy heats (200-320 lb. quantities). As with the alloys reported in Table 1 above, the alloys having optimized compositions were produced using production-type procedures, and were made into test bars and test blades by vacuum investment casting.
TABLE 42__________________________________________________________________________V-1 VIM FURNACE HEAT CHEMISTRIESALLOY HEAT NO. C B Cr Co Mo W Cb Ti Al Ta Re Hf Ni__________________________________________________________________________CMSX-12D VG 30 .001 <.001 2.34 3.2 .46 4.5 <.05 .50 5.60 8.8 6.3 .03 BASECMSX-10K VG 31 .002 <.001 2.2 3.3 .40 5.4 .10 .31 5.68 8.5 6.3 .03 BASECMSX-12D VG 35 .001 <.002 2.5 3.2 .46 4.7 <.05 .49 5.65 8.7 6.2 .03 BASECMSX-10K VG 36 .001 <.002 2.3 3.2 .40 5.5 .10 .31 5.73 8.3 6.3 .03 BASECMSX-10M VG 37 .001 <.002 2.0 1.7 .41 5.4 .09 .26 5.80 8.2 6.5 .03 BASECMSX-12F VG 38 .001 <.002 2.0 1.8 .42 4.5 <.05 .35 5.81 8.8 6.5 .02 BASECMSX-12D VG 44 .001 <.003 2.5 3.2 .47 4.6 <.05 .50 5.62 8.8 6.2 .02 BASECMSX-12D VG 45 .001 <.003 2.5 3.2 .47 4.7 <.05 .50 5.62 8.8 6.3 .02 BASECMSX-10K VG 46 .001 <.002 2.3 3.3 .40 5.5 .10 .31 5.67 8.3 6.3 .03 BASECMSX-10K VG 47 .001 <.002 2.3 3.3 .41 5.5 .10 .30 5.72 8.3 6.3 .03 BASECMSX-10K VG 76 .001 <.002 2.0 3.0 .36 5.3 .08 .22 5.75 8.2 6.4 .03 BASECMSX-10K VG 77 .001 <.002 1.9 2.0 .36 5.3 .05 .17 5.81 8.4 6.5 .04 BASEMODCMSX-10M VG 78 .001 <.002 1.8 1.5 .33 5.3 .06 .12 5.92 8.2 6.6 .03 BASEMODCMSX-12D VG 79 .001 <.002 1.8 2.0 .40 4.9 <.05 .21 5.78 8.6 6.5 .03 BASEMODCMSX-12F VG 80 .002 <.002 1.8 1.6 .38 4.5 <.05 .14 5.92 8.8 6.6 .02 BASEMODCMSX-10K VG 81 .001 <.002 2.1 3.1 .36 5.3 .08 .22 5.70 8.2 6.4 .03 BASECMSX-10K VG 91 .001 <.003 2.0 3.1 .37 5.4 .08 .21 5.76 8.2 6.5 .03 BASE__________________________________________________________________________
Table 43 below reports heat treatment detail for the optimized alloy compositions. They typically require solution heat treatment to 2490.degree.-2500.degree. F. peak process temperature, which generally results in complete .gamma.' solutioning without the occurrence of incipient melting. A three-step aging treatment was utilized.
TABLE 43__________________________________________________________________________Heat Treatment Detail PEAK SOLUTION TEMP. .degree.F. %.gamma.' PRIMARY SECONDARYALLOY .degree.C. SOLUTIONED* .gamma.'AGING+ .gamma.'AGING+__________________________________________________________________________CMSX-10K 2490 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 1365CMSX-12D 2490 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 1365CMSX-10M 2499 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 1370CMSX-12F 2499 99.0-99.5 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 137010K MOD 2490 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 136510M MOD 2499 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 137012D MOD 2490 100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 136512F MOD 2499 99.5-100 2106.degree. F./6 hrs 1600.degree. F./24 + 1400.degree. F./30 1370__________________________________________________________________________ *Determined by visual estimation +Specimens air cooled from all aging treatments
The optimized alloy compositions were evaluated. However, significant data was generated for the CMSX-10K and CMSX-12D compositions, while some test results were generated for the remaining compositions reported in Table 41 above.
Table 44 below reports the results of stress- and creep-rupture tests undertaken with CMSX-10K specimens. Variously sized test bar and blade specimens, which were cast at industrial sources, were utilized for these tests. The test results show extremely good stress and creep-rupture properties for these alloys.
TABLE 44__________________________________________________________________________CMSX-10K ALLOY STRESS- AND CREEP-RUPTURE DATA RUPTURE TIME IN HRS TIME FINAL CREEP READING TO REACHTEST CONDITION HRS % EL % RA t, HRS % DEFORMATION 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi 153.1 22.0 28.2 148.6 15.868 2.6 26.9(913.degree. C./517 MPa) 174.2 21.3 29.9 173.0 19.471 4.1 30.1 177.1 28.0 32.1 176.6 22.934 3.2 24.9 144.6 25.9 28.7 144.0 22.431 4.9 23.5 166.7 28.0 30.0 166.3 23.971 7.5 28.61750.degree. F./50.0 ksi 416.4 26.0 35.3 416.4 24.749 215.1 259.5(954.degree. C./345 MPa) 378.1 26.0 34.5 376.8 24.783 103.4 196.9 401.4 26.0 28.1 400.8 23.538 193.3 237.9 396.8 36.5 31.5 396.6 32.691 168.9 219.4 379.8 22.5 25.1 378.6 19.364 192.5 240.61800.degree. F./36.0 ksi 746.3 30.7 32.0 744.7 28.128 402.0 466.6(982.degree. C./248 MPa) 781.6 30.0 34.1 781.2 27.314 441.3 505.2 536.1 24.2 30.0 534.6 17.794 237.2 303.6 673.8 18.9 28.1 672.6 15.822 289.1 450.9 699.0 26.8 30.2 698.4 24.839 304.6 412.6 * 775.5 27.7 27.0 774.2 25.177 436.7 505.7 * ** -- -- -- -- 605.8 -- * 809.6 29.7 32.1 807.7 27.896 519.8 568.11850.degree. F./36.0 ksi 308.5 32.9 27.1 308.3 31.302 75.3 130.0(1010.degree. C./248 MPa) 311.4 22.4 26.2 311.1 22.214 155.8 193.1 313.4 17.8 24.8 313.1 17.552 186.3 212.3 360.3 24.5 27.6 359.8 22.360 203.4 233.9 326.5 27.4 28.2 290.7 21.828 165.3 188.8 326.5 27.4 28.2 325.0 25.191 144.6 191.5 273.8 25.5 21.4 -- -- -- -- 262.6 22.5 21.0 -- -- -- -- 306.0 23.4 30.4 305.6 21.833 164.8 192.0 286.4 21.9 29.7 285.4 19.817 137.8 169.5 326.0 23.9 26.3 325.1 21.846 159.8 193.9 252.8 19.4 29.3 251.8 16.618 138.2 163.5 329.8 19.5 25.8 329.0 17.332 179.4 214.3 * 363.4 15.3 21.0 361.8 13.560 227.7 259.5 * 339.9 21.4 31.4 338.3 21.425 180.2 211.9 * ** -- -- -- -- 224.1 -- * 338.1 14.0 26.2 337.2 12.981 232.6 260.21976.degree. F./28.1 ksi 108.5 22.8 30.4 107.8 19.413 39.4 56.2(1080.degree. C./194 MPa) 105.7 27.7 29.2 105.6 26.812 44.1 58.0 112.7 27.5 31.1 112.5 24.063 44.5 59.6 101.2 29.0 37.6 100.8 20.434 30.7 48.3 90.8 31.4 35.2 90.3 24.775 10.9 33.1 81.2 35.7 31.7 -- -- -- -- 72.6 -- 23.5 -- -- -- -- 97.0 25.5 33.2 95.0 20.800 33.1 47.8 100.6 28.0 35.3 100.4 24.890 37.8 52.2 93.4 29.1 32.1 93.1 28.746 30.3 45.9 95.3 27.5 38.5 94.1 21.202 37.5 50.3 94.6 25.5 40.2 93.5 19.415 41.7 54.1 * 109.3 29.6 35.1 109.1 25.613 39.7 55.4 * 105.8 30.4 33.8 105.5 26.232 42.2 55.8 * ** -- -- -- -- 54.1 -- * 109.8 25.9 33.9 109.3 19.947 55.9 65.7 * 83.1 20.0 29.3 82.1 16.771 25.3 42.7 * 76.1 15.9 24.3 76.0 14.884 22.7 38.1 * 73.2 15.9 29.4 71.5 13.536 25.1 39.1 * 97.1 25.1 23.5 96.0 20.700 27.5 44.41976.degree. F./18.85 ksi 751.2 21.7 28.3 750.4 19.963 352.7 469.5(1080.degree. C./130 MPa) 598.8 28.3 28.4 597.4 26.745 85.6 267.1 573.2 23.2 24.2 572.6 21.393 253.9 340.2 528.8 22.4 25.6 526.6 19.462 57.4 213.2 787.6 22.7 32.6 787.3 20.841 265.8 498.1 702.1 27.0 33.7 -- -- -- -- 391.3 17.9 26.0 -- -- -- -- 764.0 22.6 27.9 763.7 22.044 326.1 447.3 648.0 16.6 17.4 647.2 15.384 258.5 387.0 527.3 26.9 34.3 526.4 18.976 166.8 294.3 488.9 16.1 28.1 486.6 13.975 175.5 284.7 714.3 25.5 39.4 713.8 23.576 309.0 552.9 * 742.8 27.2 33.5 742.6 25.578 344.7 450.5 * 707.4 22.5 30.6 707.2 21.315 290.8 414.7 * 618.1 21.2 18.8 -- -- -- -- * 562.8 17.3 24.4 -- -- -- -- * 436.4 15.7 16.9 433.1 15.580 -- -- * 411.6 10.7 17.1 411.2 10.648 81.5 238.5 * ** -- -- -- -- 236.5 -- 595.8 21.8 30.7 595.0 21.612 63.9 192.0 632.1 18.6 28.9 631.3 17.166 188.8 362.6 646.6 23.9 27.4 644.6 20.277 258.6 376.5 706.9 29.6 31.4 704.9 24.728 211.9 385.4 699.2 21.8 30.7 698.8 19.584 110.5 356.0 * 726.2 23.9 27.1 725.3 21.555 360.5 440.41995.degree. F./27.5 ksi 81.1 30.6 34.6 80.8 26.770 29.1 40.9(1090.degree. C./190 MPa)2012.degree. F./14.5 ksi 923.7 26.7 27.5 921.7 20.433 154.3 530.7(1100.degree. C./100 MPa) 802.2 25.1 25.9 800.2 17.830 92.9 430.7 875.4 18.4 20.5 873.7 17.249 204.2 440.5 1005.4 19.5 29.2 -- -- -- -- 973.3 23.9 27.2 971.9 21.912 85.5 451.8 991.8 22.6 28.5 990.2 18.238 497.0 646.52030.degree. F./18.85 ksi 263.9 18.3 26.7 262.8 16.085 115.6 152.9(1110.degree. C./130 MPa) 348.7 24.8 30.0 374.4 20.774 111.6 207.8 * 281.3 30.0 34.3 280.7 26.564 116.7 169.8 * 292.1 17.6 29.6 290.5 15.035 131.1 189.4 * 219.5 -- 8.5 -- -- -- -- * 212.5 14.9 13.6 -- -- -- -- * 219.5 -- 8.5 -- -- -- -- * 197.9 -- 13.8 196.0 13.386 3.5 59.3 * 179.4 14.1 19.5 178.1 13.013 5.5 38.1 * ** -- -- -- -- 98.9 -- * 311.4 21.7 25.7 311.1 20.961 144.2 190.42030.degree. F./23.93 ksi 87.4 21.9 27.0 87.3 21.802 35.1 47.5(1110.degree. C./165 MPa) 80.6 18.4 22.9 79.3 15.286 34.3 44.9 96.1 21.5 31.2 95.0 15.687 17.4 40.8 99.6 24.1 34.7 99.6 20.676 34.1 53.9 73.5 22.9 33.9 73.0 19.341 23.2 37.4 86.9 23.2 31.1 86.6 20.502 23.8 42.2 62.1 25.1 39.7 -- -- -- -- 75.6 23.9 31.7 -- -- -- -- 93.6 30.2 41.0 92.8 21.605 29.2 47.0 82.9 22.2 31.7 82.1 18.867 18.4 29.4 84.3 27.0 41.0 82.7 19.003 26.6 42.7 77.1 26.2 36.0 76.7 17.478 36.6 46.1 89.1 25.7 33.8 87.7 17.166 30.8 46.4 82.8 38.3 39.2 82.5 33.075 21.8 37.3 80.6 28.1 31.5 79.6 24.158 8.6 24.1 67.1 27.0 35.5 66.3 20.514 17.5 29.8 74.5 23.8 38.3 73.3 17.457 22.1 37.8 66.6 19.2 34.5 65.5 12.587 23.1 36.8 77.9 32.6 37.2 77.5 22.917 19.1 34.6 * 100.2 27.1 35.7 96.3 16.134 27.8 51.0 * 104.8 35.5 37.4 102.0 17.886 38.3 57.1 * 74.6 22.3 25.1 -- -- -- -- * 56.0 15.3 15.7 -- -- -- -- * 74.6 15.2 20.4 -- -- -- -- * ** -- -- -- -- 47.3 -- * 104.5 18.4 29.7 101.4 12.862 44.9 61.192050.degree. F./15.0 Ksi 732.8 19.5 25.7 731.0 17.012 330.4 525.7(1121.degree. C./103 MPa) 551.4 20.3 27.5 -- -- -- -- 524.4 15.8 10.2 523.0 13.524 266.2 356.5 318.3 6.8 16.3 316.4 3.986 262.9 295.5 557.4 18.4 29.0 557.0 15.720 250.1 381.3 555.3 16.3 27.5 555.0 14.471 204.3 372.7 511.1 15.6 23.3 -- -- -- -- 378.8 8.4 12.1 -- -- -- -- 675.7 19.0 29.1 675.3 18.076 166.6 424.6 600.7 14.6 25.7 600.0 13.074 232.9 425.7 573.6 22.4 27.9 573.3 20.727 109.0 328.0 542.0 21.7 25.9 540.5 16.646 192.4 344.6 521.4 17.5 27.0 521.2 12.517 327.9 398.2 * 619.2 14.9 29.1 619.1 14.395 180.8 396.4 * 646.3 17.7 31.0 645.5 15.110 203.8 419.7 * 582.9 9.5 27.6 580.8 7.222 155.7 406.0 * 415.8 14.2 23.5 -- -- -- -- * 429.0 22.3 25.1 -- -- -- -- * ** -- -- -- -- 320.4 -- -- -- -- -- -- 17.7 183.7 666.3 20.8 28.4 665.0 18.694 9.1 82.4 597.3 14.6 27.9 595.8 11.641 75.0 344.6 597.3 14.6 27.9 595.8 11.641 75.0 344.6 683.9 26.6 31.4 683.0 25.604 9.5 126.6 670.9 17.9 28.1 670.5 16.094 70.5 289.0 * 454.6 21.5 30.3 454.4 21.210 168.1 275.72100.degree. F./12.0 ksi 666.0 11.5 24.5 665.6 10.469 100.7 448.5(1149.degree. C./83 MPa) 597.9 20.0 32.0 597.2 19.809 14.3 76.0 662.1 24.6 25.1 662.1 18.709 33.3 188.7 575.0 17.1 25.1 573.5 16.194 15.1 116.1 473.2 20.6 33.7 472.4 19.563 0.6 22.5 543.4 23.1 35.3 542.3 21.563 24.7 171.3 * 484.0 14.0 48.0 483.1 2.370 227.7 452.5 * ** -- -- -- -- 104.2 -- 590.0 plus -- -- 590.8 8.070 22.5 104.2 791.0 17.4 31.1 789.6 19.722 40.7 145.2 746.9 16.5 31.2 745.9 15.607 61.2 192.3 359.1 plus -- -- 359.1 7.643 26.1 82.6 * 423.2 25.0 34.7 421.6 23.157 76.8 209.52100.degree. F./10.0 ksi 839.6 18.0 24.0 -- -- -- --(1149.degree. C./69 MPa) 868.1 12.7 15.2 -- -- -- --2150.degree. F./10.0 ksi 566.1 10.6 18.33 564.1 8.579 193.6 443.1(1177.degree. C./69 (MPa) 400.6 15.6 25.2 399.8 15.545 9.8 88.0 399.7 18.8 27.8 -- -- -- -- 263.7 10.7 22.0 -- -- -- -- 493.7 23.5 31.4 491.9 22.850 2.6 25.2 441.3 21.6 31.7 440.5 19.291 38.9 124.6 427.6 14.2 25.1 426.5 9.801 258.2 351.8 * 472.3 19.4 33.5 472.0 17.482 42.6 271.4 * ** -- -- -- -- 135.8 -- * 426.6 21.2 39.2 423.7 16.940 184.1 299.22150.degree. F./12.0 ksi 264.1 8.0 27.3 264.0 5.097 185.5 238.2(1177.degree. C./83 MPa) 236.2 18.5 29.4 234.8 16.343 27.7 74.3 225.8 22.7 40.7 223.8 12.435 14.4 147.1 * 265.2 11.8 30.9 264.0 8.747 68.0 193.8 * ** -- -- -- -- 74.4 -- * 215.9 26.8 28.6 215.9 25.00 86.7 155.42200.degree. F./10.0 ksi 163.2 14.7 41.9 161.8 7.273 70.7 139.9(1204.degree. C./69 MPa) 110.6 13.0 43.1 109.4 10.797 16.1 42.5 136.1 9.4 42.1 135.7 7.305 22.5 99.7 136.5 15.2 21.8 -- -- -- -- 213.9 18.8 20.6 -- -- -- -- *)205.1 17.8 39.4 204.6 14.341 72.0 164.6 * ** -- -- -- -- 4.1 --__________________________________________________________________________ * 2106.degree. F./6 Hr/AC Primary Age ** Interrupted Creeprupture Test. All results with 2075.degree. F./6 Hr/AC Primary Age.
CMSX-10K alloy tensile data are reported in Table 45 below. The tests were performed at temperatures ranging from RT-2012.degree. F. The test results show improvement relative to earlier alloy test results presented in Table 36 above.
TABLE 45__________________________________________________________________________Tensile DataCMSX-10K AlloyTEST TEMP. 0.1% PS 0.2% PS UTS ELONG RA STATIC MODULUS.degree.F. ksi ksi ksi % % E, psi .times. 10.sup.6__________________________________________________________________________68 135.0 134.7 136.6 10 9 20.3 135.3 134.9 139.8 11 12 19.0842 136.3 136.0 139.7 17 14 18.8 133.9 134.4 136.8 11 9 18.31202 137.2 137.6 157.4 13 18 17.1 136.9 136.9 157.4 15 28 17.21382 143.6 144.6 177.7 15 8 16.4 140.7 141.4 173.2 11 11 15.41562 143.7 142.1 166.6 24 24 15.5 144.2 141.7 168.5 22 20 14.91742 96.2 91.4 133.6 26 31 14.9 94.6 90.4 131.8 26 29 14.41922 74.7 78.0 107.6 28 34 13.0 73.7 77.4 107.0 30 35 12.8__________________________________________________________________________
Dynamic elastic modulus data are reported in Table 46 below. The CMSX-10K alloy data are reported for test conditions ranging from RT-2012.degree. F.
TABLE 46__________________________________________________________________________Dynamic Elastic Modulus, ECMSX-10K Alloy__________________________________________________________________________TEST TEMP 68 212 392 572 752 932 1112 1292 1472 1652 1832 2012.degree.F.E 19.2 19.1 18.9 18.7 18.2 17.3 16.8 16.3 15.3 14.4 13.1 11.6psi .times. 10.sup.6__________________________________________________________________________
Elevated temperature (1202.degree.-1922.degree. F.) impact data for CMSX-10K and CMSX-12D specimens are reported in Table 47 below. Comparison to other material capabilities can be made by review of the respective Tables 30 and 37, above.
TABLE 47______________________________________Impact DataTEST ALLOY ALLOYTEMPER- CMSX-10K CMSX-12DATURE IMPACT ENERGY, IMPACT ENERGY,.degree.F. JOULES JOULES______________________________________1202 21, 28, 29 22, 24, 291382 30, 28, 26 32, 30, 291562 21, 23, 18 23, 25, 211742 28, 20, 17 19, 44, 381922 63, 54, 50 34, 33, 53______________________________________
Plain low cycle fatigue data for CMSX-10K and CMSX-12D specimens is reported in Table 48. The tests were performed at 1382.degree. F., 1562.degree. F. and 1742.degree. F., respectively, with R=0 and 0.25 Hz test conditions. Comparative results are found above in Tables 31 and 38, respectively.
TABLE 48______________________________________Plain Low Cycle Fatigue DataCMSX-10K Alloy; R = 0, 0.25 HzTEST TEMP PEAK STRESS,.degree.F. ksi CYCLES BROKEN ?______________________________________1382 150.8 8088 Y 137.8 11,120 Y 137.1 21,490 Y 123.3 45,460 Y 119.0 122,111 N1562 150.8 912 Y 142.3 1688 Y 137.8 5101 Y 123.3 10,640 Y 108.8 54,270 Y1742 101.5 9227 Y 84.1 *22,487 N1382 150.8 18,197 Y 137.8 15,290 Y 127.6 48,450 Y 121.8 35,886 Y 116.0 166,893 N 110.2 101,812 N______________________________________ *Test Stopped: Specimen pulled out of threads
CMSX-10K notched low cycle fatigue (K.sub.t =2.2) data is reported in Table 49 below. The tests were performed at 1742.degree. F., R=0 and 0.25 Hz test conditions. Comparative results are found above in Tables 32 and 39, respectively.
TABLE 49______________________________________K.sub.t = 2.2 Notched Low Cycle Fatigue DataCMSX-10K Alloy; 1742.degree. F., R = 0, 0.25 HzPEAK NOMINALSTRESS,ksi LIFE, CYCLES BROKEN ?______________________________________87.0 11,070 Y75.4 41,660 Y______________________________________
Bare alloy oxidation data for CMSX-10K and CMSX-12D specimens are reported in Table 50 below. The tests were performed with test conditions of 2012.degree. F., 0.25 ppm salt and cycled four times per hour. Test duration was 200 hours, or 800 cycles. The test results indicate that both alloys exhibit extremely good resistance to oxidation.
TABLE 50______________________________________Bare Alloy Oxidation Data______________________________________CONDITIONS 2012.degree. F.; 0.25 ppm Salt; Cycled 4 times per hourTEST DURATION 200 hours (800 cycles)RESULTS CMSX-10K - 0.2 mm Loss on Diameter CMSX-12D - 0.44 mm Loss on DiameterSIGNIFICANCE Both alloys performed as good or better than CMSX-4; CMSX-10 Ri and CMSX-12 Ri results illustrated in FIG. 3______________________________________
FIG. 6 illustrates the results of initial measurements taken on corrosion pins having CMSX-10K and CMSX-12D compositions, which were run at 1742.degree. F., 2 ppm salt conditions out to about 200 hours.
CMSX-12D stress- and creep-rupture data are reported in Table 51 below, while this alloy's respective tensile properties for tests conducted at RT-2102.degree. F. conditions are reported in Table 52 below.
TABLE 51__________________________________________________________________________CMSX-12D ALLOY STRESS- AND CREEP-RUPTURE DATA RUPTURE TIME IN HRS TIME FINAL CREEP READING TO REACHTEST CONDITION HRS % EL % RA t, HRS % DEFORMATION 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi 112.2 20.1 23.8 111.2 18.232 1.6 12.0(913.degree. C./517 MPa) 109.6 19.8 22.8 108.6 16.246 2.1 9.91750.degree. F./50.0 ksi 394.4 28.5 31.0 393.1 24.805 178.2 231.3(954.degree. C./345 MPa) 374.9 28.1 30.9 373.3 23.876 175.7 225.11800.degree. F./36.0 ksi 611.9 26.0 35.2 611.8 25.725 306.9 369.5(982.degree. C./248 MPa) 592.3 29.7 31.7 591.6 27.977 308.4 366.5 * 693.1 25.1 22.8 692.7 23.926 378.5 441.6 * ** -- -- -- -- 459.9 --1850.degree. F./36.0 ksi 237.5 20.5 29.9 236.6 18.377 135.6 158.4(1010.degree. C./248 MPa) 264.0 23.9 26.2 262.5 22.362 113.4 151.8 252.2 24.8 24.6 251.1 22.049 125.5 151.1 305.9 28.8 33.1 305.0 26.500 157.3 185.8 255.5 19.6 29.7 254.4 18.328 139.2 163.1 266.7 31.3 33.6 264.8 30.686 146.7 169.6 278.3 25.8 27.9 278.0 24.451 137.7 164.6 245.7 25.1 33.2 245.5 24.532 115.1 141.7 * 285.0 29.9 32.4 284.6 27.967 149.4 174.5 292.3 24.6 31.0 291.9 24.299 101.9 149.2 266.4 27.1 31.2 264.9 24.323 97.7 146.5 239.1 23.5 26.4 238.7 19.758 122.3 147.3 * ** -- -- -- -- 139.4 -- * 320.5 22.8 29.5 319.4 20.654 194.6 216.81922.degree. F./32.63 ksi 105.0 20.1 32.0 103.5 16.107 39.0 55.9(1050.degree. C./225 MPa) 105.8 32.5 37.5 104.9 24.887 42.2 56.91976.degree. F./28.1 ksi 75.1 14.4 19.6 74.8 11.765 38.1 46.4(1080.degree. C./194 MPa) 101.2 25.0 25.5 98.7 20.433 40.7 52.7 100.8 27.8 26.6 98.9 21.658 45.0 54.0 95.8 29.9 36.0 95.8 25.347 37.1 50.4 86.8 30.0 30.8 83.9 24.506 3.6 19.7 95.7 34.7 38.6 93.4 23.003 41.4 54.2 93.7 25.3 37.0 93.6 24.721 35.2 48.1 97.7 24.0 37.6 97.5 21.918 35.3 49.5 * 100.8 28.7 32.4 100.4 26.164 41.5 54.1 * 88.9 30.5 36.2 88.8 28.500 38.3 49.9 86.5 24.6 35.4 85.3 18.215 32.3 45.2 84.6 39.0 37.5 83.4 24.246 27.0 39.9 79.0 26.3 64.8 76.6 17.737 33.1 43.5 * ** -- -- -- -- 41.0 -- * 101.1 25.4 28.8 99.1 19.064 45.9 57.8 85.4 25.7 35.3 84.3 21.424 27.1 42.91976.degree. F./18.85 ksi 576.0 23.9 28.0 575.5 22.40 240.1 341.8(1080.degree. C./130 MPa) 653.6 27.1 30.0 653.5 24.514 205.0 356.7 618.6 24.4 28.7 618.0 24.047 141.0 294.3 687.2 28.1 32.5 685.5 24.805 353.3 435.9 544.3 14.7 32.3 542.7 12.314 319.1 385.2 594.1 25.0 34.8 593.7 24.809 30.4 204.6 625.7 16.9 25.6 627.7 16.868 258.0 377.3 621.3 20.0 28.0 619.7 18.805 202.2 359.2 * 621.5 22.2 29.7 621.5 21.492 263.9 377.8 * 591.6 28.7 32.8 591.3 26.922 276.0 356.3 * -- -- -- -- * ** -- -- -- -- 300.5 --1995.degree. F./27.5 ksi 77.0 27.8 37.0 75.9 15.867 25.3 36.4(1090.degree. C./190 MPa)2012.degree. F./14.5 ksi 816.1 17.9 25.5 836.6 16.222 115.0 498.4(1100.degree. C./100 MPa) 644.2 19.3 25.4 643.1 15.538 410.0 482.5 1014.7 11.4 12.4 1012.8 10.433 90.3 486.22012.degree. F./25.38 ksi 66.4 30.4 36.5 65.6 22.457 26.1 34.9(1100.degree. C./175 MPa) 70.4 33.0 40.1 70.2 25.294 21.6 33.62030.degree. F./23.93 ksi 74.6 29.3 32.5 72.8 20.312 26.9 37.9 74.6 25.5 31.3 72.9 17.439 32.9 42.2 82.0 28.0 29.8 80.9 22.297 21.7 37.2 89.0 24.1 33.1 86.9 15.458 28.4 45.4 90.1 26.6 34.9 89.1 17.031 44.1 55.3 89.4 27.3 34.9 87.6 19.087 30.5 46.3 75.7 14.3 33.2 74.3 11.315 33.3 46.3 74.7 22.0 34.1 74.6 15.939 21.7 36.8 39.3 22.9 28.4 -- -- -- -- 65.9 22.5 24.7 -- -- -- -- 18.3 17.2 16.2 18.3 16.215 3.7 7.7 86.1 32.8 38.6 85.8 28.107 12.9 31.1 77.7 25.3 32.9 76.1 19.766 11.9 27.2 77.5 31.8 36.7 77.5 21.250 6.2 24.6 79.9 35.4 40.0 79.3 27.691 20.9 34.8 71.0 23.0 40.5 70.5 17.631 24.8 37.0 * 81.8 17.7 36.6 81.3 15.115 32.7 46.0 * 83.9 34.3 38.6 83.3 26.080 25.9 42.3 75.9 40.0 38.0 74.9 24.783 31.8 41.9 71.5 32.0 34.9 68.9 18.452 21.7 35.4 72.4 22.2 28.0 71.2 21.872 11.0 22.9 * ** -- -- -- -- 19.3 -- * 94.6 25.5 29.9 94.4 23.742 39.2 52.0 65.7 35.5 39.0 65.2 23.050 24.1 33.4 47.7 27.9 40.2 46.9 13.700 9.6 21.3 * 56.0 14.2 23.5 -- -- -- --2030.degree. F./18.85 ksi 254.5 11.3 30.6 254.1 11.229 94.0 165.4(1110.degree. C./130 MPa) 292.1 22.7 30.9 291.8 21.808 47.3 151.7 * 348.8 21.8 28.2 346.9 18.201 159.4 226.7 * 241.8 26.9 55.6 241.8 6.474 99.1 167.8 * 212.5 14.9 13.6 -- -- -- -- * ** -- -- -- -- 130.2 --2030.degree. F./17.40 ksi 332.1 22.2 27.2 330.4 20.391 54.2 144.5(1110.degree. C./120 MPa)2050.degree. F./15.0 ksi 515.1 18.8 23.8 513.1 15.217 217.5 355.9(1121.degree. C./103 MPa) 587.2 16.8 20.7 585.4 12.339 375.5 448.5 589.4 12.3 15.9 589.0 11.075 208.5 403.3 615.4 20.8 20.4 614.7 19.363 56.5 222.6 565.1 18.5 28.5 564.3 16.599 353.4 418.0 631.9 17.3 28.4 631.9 15.830 403.4 477.7 462.6 15.9 20.5 -- -- -- -- 497.7 12.7 18.3 -- -- -- -- 561.5 9.2 28.5 561.1 9.113 129.3 391.7 463.1 9.6 24.2 461.4 7.376 316.6 388.4 * 624.2 21.8 26.9 623.7 21.386 171.3 262.8 * 587.3 19.2 23.5 586.3 16.712 236.9 403.3 * 482.9 23.7 30.2 481.2 20.389 28.4 169.4 336.7 13.3 37.9 335.0 10.433 38.3 173.6 24.3 7.1 14.5 22.8 3.021 13.0 19.4 * ** -- -- -- -- 316.9 --2050.degree. F./19.58 ksi 145.1 28.0 31.2 143.9 19.913 12.0 68.2(1121.degree. C./135 MPa)2100.degree. F./ 12.0 ksi 454.2 12.1 24.3 -- -- -- --(1149.degree. C./83 MPa) 384.3 12.5 32.6 382.1 5.913 95.2 304.6 674.6 16.6 26.1 673.3 14.670 165.2 469.7 302.0 13.3 32.7 -- -- -- -- 453.1 -- 23.2 -- -- -- -- * 631.8 16.0 25.4 630.8 13.560 424.4 516.4 585.5 13.0 27.1 584.2 9.484 233.2 462.3 534.1 22.9 28.8 532.2 17.201 44.2 102.1 667.8 17.9 33.8 667.2 15.477 351.5 454.4 * ** -- -- -- -- 73.7 --2150.degree. F./10.0 ksi 169.0 24.6 59.1 168.2 5.338 6.9 35.3(1177.degree. C./69 MPa) 356.5 11.6 42.1 356.4 9.793 132.6 267.6 264.9 16.7 42.2 -- -- -- -- 587.4 -- 35.9 -- -- -- -- * 367.7 10.7 52.6 366.9 4.018 11.9 171.6 382.6 -- -- 382.6 5.588 30.2 92.2 461.9 14.5 44.1 461.7 12.483 63.8 160.5 457.2 25.9 35.9 453.6 13.854 13.3 110.9 * ** -- -- -- -- 177.5 --2150.degree. F./12.0 ksi 222.0 14.2 54.4 219.5 2.024 58.6 218.6(1177.degree. C./83 MPa) * 301.9 18.3 39.2 300.2 12.751 102.9 236.6 * ** -- -- -- -- 51.7 --2200.degree. F./10.0 ksi 102.3 8.9 22.7 100.1 6.302 8.0 43.6(1204.degree. C./69 MPa) 178.7 10.0 40.1 178.6 9.854 20.5 61.0 76.9 8.9 23.1 -- -- -- -- 133.7 14.7 20.4 -- -- -- -- * 196.0 9.9 31.1 195.9 8.651 30.5 82.3 * 199.4 17.4 40.2 199.0 16.811 16.7 128.6 * ** -- -- -- -- 97.1 --__________________________________________________________________________ * 2106.degree. F./6 Hr/AC Primary Age ** Interrupted Creeprupture Test. All results with 2075.degree. F./6 Hr/AC Primary Age.
TABLE 52__________________________________________________________________________Tensile DataCMSX-12D AlloyTEST TEMP 0.1% PS 0.2% PS UTS ELONG RA STATIC MODULUS.degree.F. ksi ksi ksi % % E, psi .times. 10.sup.6__________________________________________________________________________68 137.4 137.2 148.8 11 12 19.9 133.6 132.6 154.6 17 18 20.3842 138.7 138.7 146.9 14 15 18.6 139.8 140.1 145.3 13 15 19.41202 142.6 142.7 163.0 13 13 16.8 139.7 139.8 162.4 13 13 17.01382 137.5 137.5 161.0 14 19 15.71562 140.2 138.5 168.5 24 22 15.2 138.4 140.0 158.8 24 27 15.71742 94.6 90.8 138.1 28 35 14.5 95.1 90.8 136.0 27 35 15.21922 69.8 72.5 100.4 28 40 13.6 70.6 73.2 101.8 28 39 13.62102 41.0 43.5 66.0 29 52 11.6 41.3 43.5 66.6 37 54 11.7__________________________________________________________________________
Initial creep-rupture test data for CMSX-10M and CMSX-12F specimens is reported below in Tables 53 and 54, respectively.
TABLE 53__________________________________________________________________________CMSX-10M ALLOY STRESS- AND CREEP-RUPTURE DATA RUPTURE TIME IN HRS TIME FINAL CREEP READING TO REACHTEST CONDITION HRS % EL % RA t, HOURS % DEFORMATION 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi * 241.4 25.2 32.5 240.6 21.422 15.5 56.3(913.degree. C./517 MPa)1750.degree. F./50.0 ksi * 433.4 23.5 30.6 433.4 22.209 224.1 271.1(954.degree. C./345 MPa)1800.degree. F./36.0 ksi 812.5 22.8 29.7 811.5 21.894 526.4 583.5(982.degree. C./248 MPa) * 832.5 36.3 37.2 831.4 33.464 513.3 564.7 * 902.3 25.9 37.4 901.6 24.806 585.5 637.21850.degree. F./36.0 ksi * 368.9 29.1 36.0 368.1 28.043 216.4 241.6(1010.degree. C./248 MPa) * 338.7 32.1 38.8 337.5 28.224 197.7 220.8 * 306.6 38.2 35.1 305.3 34.139 110.0 171.9 * 279.2 40.5 38.5 277.7 34.006 129.6 156.3 * 300.4 23.2 36.3 299.5 20.613 167.4 194.91976.degree. F./28.1 ksi * 129.8 23.7 25.4 127.3 20.141 63.6 77.9(1080.degree. C./194 MPa) * 120.7 19.8 29.7 120.6 17.196 55.8 70.0 * 111.2 31.1 33.5 110.9 29.119 43.0 57.4 * 91.8 22.6 33.7 91.0 19.257 31.4 47.8 * 107.3 31.4 32.7 106.1 23.852 61.7 68.31976.degree. F./18.85 ksi * 628.7 21.8 27.3 627.2 20.507 268.8 364.2(1080.degree. C./130 MPa) * 505.1 28.8 34.0 504.2 27.062 23.9 160.5 * 440.9 36.5 33.8 439.2 32.847 114.7 196.7 * 825.7 25.8 27.1 825.7 24.969 350.5 446.72030.degree. F./18.85 ksi * 278.9 13.9 30.3 277.8 12.367 80.6 160.8(1110.degree. C./130 MPa)2030.degree. F./23.93 ksi * 122.1 25.6 33.4 120.9 20.097 45.0 62.9(1110.degree. C./165 MPa) * 109.9 27.3 29.9 109.7 24.963 41.6 57.3 * 97.6 30.8 33.5 97.2 33.590 2.9 10.1 * 92.9 28.3 31.3 92.5 23.808 33.3 46.9 * 101.8 29.4 32.9 100.8 21.883 21.9 43.22050.degree. F./15.0 ksi * 447.2 21.8 30.1 446.9 19.430 88.4 252.1(1121.degree. C./103 MPa) * 426.4 26.3 32.6 425.5 23.532 172.3 272.4 * 401.5 29.6 30.2 400.2 25.848 167.5 236.6 * 389.5 25.8 35.3 388.3 18.538 262.0 293.3 502.7 21.6 30.9 503.3 20.013 162.5 291.2 616.7 25.6 32.8 616.0 25.199 131.5 347.32100.degree. F./12.0 ksi * 581.5 11.2 23.0 581.5 10.455 297.7 393.6(1149.degree. C./83 MPa) * 439.3 26.3 24.8 439.1 25.869 140.3 251.9 * 396.4 26.1 34.6 395.0 21.641 70.1 203.1 * 360.8 24.2 24.4 359.2 21.834 53.0 152.3 * 612.9 22.7 34.2 612.4 21.508 281.2 395.92150.degree. F./10.0 ksi * 343.5 15.3 38.5 342.9 11.968 151.3 244.8(1177.degree. C./69 MPa) * 301.3 25.4 33.8 299.4 18.100 56.3 162.6 * 316.7 27.0 30.4 314.2 26.101 39.4 105.7 * 214.1 18.0 39.0 213.3 14.428 47.1 114.8 * 536.8 17.2 42.0 534.8 13.419 221.3 380.52150.degree. F./12.0 ksi * 224.4 19.9 37.3 222.9 18.898 8.7 57.7(1177.degree. C./83 MPa) * 192.3 12.3 28.7 190.3 10.641 7.1 39.8 * 172.6 19.7 32.5 170.3 14.187 7.5 42.8 * 168.8 25.6 37.8 166.9 19.507 59.1 96.2 * 369.6 8.8 28.9 368.4 8.783 118.1 267.62200.degree. F./10.0 Ksi * 186.1 18.2 44.9 185.3 17.445 15.4 69.4(1204.degree. C./69 MPa)__________________________________________________________________________ * 2106.degree. F./6 Hr/AC Primary Age. ** Interrupted Creeprupture Test.
TABLE 54__________________________________________________________________________CMSX-12F ALLOY STRESS- AND CREEP-RUPTURE DATA RUPTURE TIME IN HRS TIME FINAL CREEP READING TO REACHTEST CONDITION HRS % EL % RA t, HOURS % DEFORMATION 1.0% 2.0%__________________________________________________________________________1675.degree. F./75.0 ksi * 199.8 26.6 34.2 197.0 21.502 8.1 34.0(913.degree. C./517 MPa)1750.degree. F./50.0 ksi * 457.4 20.3 37.7 457.3 18.056 255.1 306.4(954.degree. C./345 MPa) * 519.7 32.4 34.5 517.7 28.241 279.2 331.1 * 551.7 23.1 32.3 551.6 21.854 280.4 347.51800.degree. F./36.0 ksi * 837.8 32.2 35.1 837.3 31.208 479.2 565.3(982.degree. C./248 MPa)1850.degree. F./36.0 ksi * 290.3 28.2 37.6 288.6 24.734 151.7 184.8(1010.degree. C./248 MPa) * 298.3 36.2 42.0 297.2 32.862 163.9 187.3 * 292.5 31.5 39.5 291.0 29.619 132.2 167.4 * 345.3 31.3 33.8 343.6 27.245 220.9 236.01976.degree. F./28.1 ksi * 128.7 28.8 34.8 128.2 25.763 60.5 72.91080.degree. C./194 MPa) * 81.3 25.8 37.8 80.1 17.825 40.0 48.6 * 109.3 23.4 32.5 108.9 22.496 50.9 62.4 * 109.2 30.8 35.5 107.7 25.243 40.0 55.81976.degree. F./18.85 ksi * 782.5 25.3 31.4 782.4 22.654 373.3 443.1(1080.degree. C./130 MPa) * 567.3 26.2 37.1 565.5 20.919 188.5 280.0 * 507.8 30.3 39.1 507.0 27.958 221.0 276.6 * 538.2 34.8 38.6 537.8 31.820 222.1 291.01995.degree. F./27.5 ksi(1090.degree. C./190 MPa)2012.degree. F./14.5 ksi(1100.degree. C./100 MPa)2030.degree. F./23.93 ksi * 56.3 30.4 42.0 55.7 21.806 16.4 24.5(1110.degree. C./165 MPa) * 98.3 30.8 37.8 96.9 23.348 21.4 40.9 * 81.9 19.8 40.4 81.5 18.866 31.8 43.1 * 88.7 34.9 36.2 88.0 25.703 29.3 41.62030.degree. F./18.85 ksi * 355.4 26.8 27.1 355.1 26.607 139.7 188.1(1110.degree. C./130 MPa)2050.degree. F./15.0 ksi * 712.2 21.1 27.0 711.3 20.870 74.3 325.3(1121.degree. C./103 MPa) * 432.4 33.9 38.9 430.7 29.991 79.5 211.2 * 442.1 34.5 32.4 440.2 32.314 206.8 261.9 * 463.3 34.6 37.7 462.5 28.676 87.1 218.72100.degree. F./12.0 ksi * 682.0 13.2 18.9 681.9 13.080 367.9 500.3(1149.degree. C./83 MPa)2150.degree. F./10.0 ksi * 573.1 22.4 34.9 571.3 20.297 159.3 249.3(1177.degree. C./69 MPa)2150.degree. F./12.0 ksi * ** -- -- -- -- 40.8 89.7(1177.degree. C./83 MPa)2200.degree. F./10.0 ksi(1204.degree. C./69 MPa)__________________________________________________________________________ * 2106.degree. F./6 Hr/AC Primary Age ** Interrupted Creeprupture Test.
While this invention has been described with respect to particular embodiments thereof, it is apparent that numerous other forms and modifications of this invention will be obvious to those skilled in the art. The appended claims and this invention generally should be construed to cover all such obvious forms and modifications which are within the true spirit and scope of the present information.

Number	Name	Date
RE29920	Baldwin	Feb 1979
3765879	Hockin et al.	Oct 1973
4045255	Jackson	Aug 1977
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4116723	Gell et al.	Sep 1978
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Number	Date	Country
2029539	Nov 1990	CAX
0240451	Oct 1987	EPX
0434996	Jul 1991	EPX
2234521	Feb 1991	GBX
2235697	Mar 1991	GBX

Single crystal nickel-based superalloy

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