Thermal and wear resistant tough nickel based alloy guide rolls

FIELD OF THE INVENTION
This invention relates to the thermal and wear resistant, tough alloy at elevated temperatures.
The alloy consists essentially of carbon, chromium, iron, tungsten, molybdenum, titanium, aluminum, silicon, manganese, cobalt and nickel, and the alloy further include optionally nitrogen, and at least one selected from the group consisting of niobium, tantalum and the alloy further include optionally at least one selected from the group consisting of boron, zirconium. The alloys of this invention relate to alloys for many application that can be used for providing the build-up welding and for providing the guide shoe for use a hot rolling apparatus for fabricating seamless steel pipes.
BACKGROUND OF THE INVENTION
Generally, a hot rolling apparatus for fabricating seamless steel pipes comprises a pair of upper and lower tapered rolls of a barrel shape disposed in intersecting relation to each other, opposed guide shoes disposed on opposite sides of center axes of the tapered barrel rolls and spearhead shaped plug disposed intermediate the tapered barrel rolls in front thereof. A round billet heated at temperature of 1150 to 1250.degree. C. is supplied to the hot rolling apparatus of the tapered roll type. The round billet in hot pierced at its center by the plug while it is being rotated by the tapered barrel rolls. Thereafter, the pierced billet is rolled repeatedly and formed into a seamless steel pipe. In this case, during the fabrication of the pipe, it assumes an elliptical shape due to compressive force and projective force exerted by the tapered barrel rolls. The guide shoes are arranged 90 degrees circumferentially of each roll in opposed relation to each other so as to control the outer shape and the thickness of the pipe. Therefore, the guide shoes are in contact with the steel pipe heated at elevated temperatures, so that the surface of the guide shoes are held in sliding contact with the rotatingly advancing steel pipes.
As a result, the guide shoes are repeatedly subjected to a rapid heating at elevated temperatures and a rapid cooling by cooling water. Further, the guide shoes undergo rolling sliding friction under greated stress load.
The guide shoes conventionally used under such serve conditions are made of a material such as an alloy consisting of 26% by weight of chromium--3% by weight of nickel--the balance iron alloy, 26% by weight of chromium--2% by weight of nickel--the balance iron alloy having thermal and wear resistant steel alloy at elevated temperatures, 1% by weight of carbon 5% by weight of copper--the balance iron alloy and 1% by weight of carbon--15% by weight of chromium--5% by weight of molybdenum--the balance nickel alloy. Some of these alloys affect a yield to fabricate a seamless steel pipe because of insufficient corrosion resistance at elevated temperatures. Scales or steel pieces formed at the surface of the steel pipe heated at elevated temperatures are stuck to the surface of the guide shoes by the heat involved. The stuck scales or steel pieces of the guide shoes give rise to damage to the surface thereby affecting the yield rate of the fabrication of the steel pipe. Also some of conventional alloys cannot withstand a thermal shock due to repeated of local heating and water cooling. As a result, cracks are formed on the surface of the guide shoe, so that subjected to damage.
Further some of these conventional alloys are not sufficient in wear resistance. Guide shoe made of such alloy has a shorter service life.
After an extensive study to provide an alloy which are sufficient in thermal resistance, wear resistance, toughness and hardness for use as guide shoes for a hot rolling apparatus of the tapered roller type for fabricating seamless steel pipe, this invention is achieved.
DISCLOSURE OF THE INVENTION
An object of this invention is to provided alloys having thermal shockproof, thermal and wear resistance, and corrosion resistance at elevated temperatures.
Another object of this invention is to provided such alloys for use as guide shoes for hot rolling apparatus of the tapered roller type for fabricating seamless steel pipe.
The alloy of this invention comprises 0.55 to 2.0 percent by weight of carbon, 10 to 28% by weight of chromium, 1 to 30% by weight of iron, 0.01 to 4.5% by weight of titanium, 0.01 to 4.5% by weight of aluminium, 0.1 to 10% by weight of tungsten, 0.1 to 10%, by weight of molybdenium, the balance nickel and incidental impurity, the alloy including optionally 0.1 to 3% by weight of silicon, 0.1 to 3% by weight of manganese, 1 to 8% by weight of cobalt, the alloy including optionally at least one selected from the group consisting of 0.005 to 0.2% by weight of nitrogen, 0.01 to 1.5% by weight of niobium and tantalum and the alloy including optionally at least one selected from the group consisting of 0.001 to 0.2% by weight of boron and zirconium.
The invention will now be more specifically described.
A thermal and wear resistant, tough alloy according to a first embodiment of this invention consists essentially of 0.55 to 2.0% by weight of carbon, 10 to 28% by weight of chronium, 1 to 30% by weight of iron, 0.01 to 4.5% by weight of titanium, 0.01 to 4.5% by weight of aluminium, 0.1 to 10% by weight of tungsten, 0.1 to 10% by weight of molybdenium, the balance nickel and incidental impurities, the alloy further including optionally 0.1 to 3% by weight of silicon, 0.1 to 3% by weight of manganese, the alloy further including optionally at least one selected from the group consisting of 0.005 to 0.2% by weight of nitrogen, 0.01 to 1.5% by weight of niobium and tantalum, the alloy further including optionally at least one selected from the group consisting of 0.001 to 0.2% by weight of boron and zirconium.
Furthermore, a thermal and wear resistant, tough alloy according to a second embodiment of this invention consists essentially of 0.55 to 2.0% by weight of carbon, 10 to 28% by weight of chromium, 1 to 30% by weight of iron, 0.01 to 4.5% by weight of titanium, 0.01 to 4.5% by weight of aluminium, 0.1 to 10% by weight of tungsten, 0.1 to 10% by weight of molybdenum, 1 to 8% by weight of cobalt, the balance nickel and incidental impurities, the alloy further including optionally 0.1 to 3% by weight of silicon, 0.1 to 3% by weight of manganese, the alloy further including optionally at least one selected from the group consisting of 0.005 to 0.2% by weight of nitrogen, 0.01 to 1.5% by weight of niobium and tantalum, and the alloy further including optionally at least one selected from the group consisting of 0.001 to 0.2% by weight of boron and zirconium.
Furthermore a thermal and wear resistant, tough alloy according to third embodiment of this invention consists essentially of 0.55 to 2.0% by weight of carbon, 10 to 28% by weight of chromium, 3 to 30% by weight of iron, 0.01 to 3.5% by weight of titanium, 0.01 to 3.5% by weight of aluminium, 0.5 to 10% by weight of tungsten, 0.1 to 10% by weight of molybdenum, 0.1 to 3% by weight of silicon, 0.1 to 3% by weight of manganese, the balance nickel and incidental impurities, the alloy further including optionally at least one selected from the group consisting of 0.005 to 0.2% by weight of nitrogen, 0.01 to 1.5% by weight of niobium and tantalum, the alloy further including optionally at least one selected from the group consisting of 0.001 to 0.2% by weight of boron and zirconium. Furthermore, a thermal and wear resistant, tough alloy according to a fourth embodiment of this invention consists essentially of 0.55 to 2.0% by weight of carbon, 10 to 28% by weight of chromium, 3 to 30% by weight of iron, 0.01 to 3.5% by weight of titanium, 0.01 to 3.5% by weight of aluminium, 0.5 to 10% by weight of tungsten, 0.5 to 10% by weight of molybdenum, 0.1 to 3% by weight of silicon, 0.1 to 3% by weight of manganese, 1 to 8% by weight of cobalt, the balance nickel and incidental impurities, the alloy further including optionally at least one selected from the group consisting of 0.005 to 0.2% by weight of nitrogen, 0.01 to 1.5% by weight of niobium and tantalum, the alloy further including optionally at least one selected from the group consisting of 0.001 to 0.2% by weight of boron and zirconium.
THE PREFERRED EMBODIMENTS OF THE INVENTION
The effect of the components of the thermal and wear resistant, tough alloy at elevated temperatures according to the invention and the reason why the component have specified contents will now be described.
Carbon: Carbon is dissolved into an alloy matrix at elevated temperatures. Carbon also reacts with chromium, tungsten, molybdenum, titanium, niobium, tantalum and so on to form carbides such as M.sub.7 C.sub.3, MC and M.sub.23 C.sub.6 so that the resultant alloy is improved in the strength and the hardness. Therefore, carbon content serves to impact an excellent wear resistance to the alloy and also imparts the weldability and the castability to the alloy. When the carbon content is below 0.55% by weight, the alloy fails to have the abovementioned properties. On the other hand, when the carbon content exceeds 2.0% by weight, the resultant alloy has an increased amount of deposition of carbides, and also a particle size of the carbides becomes larger to lower the toughness of the alloy so that the alloy can not withstand a thermal shock due to the rapid heating and cooling. Therefore, it is determined that the carbon content should be 0.55 to 2.0% by weight.
Chromium: Chromium is dissolved into an alloy matrix in parts and the remainder reacts with carbon to form carbides. The resultant alloy is improved in the wear resistance and the hardness at elevated temperatures. Chromium serves to impart the corrosion resistance at elevated temperatures. When chromium content is below 10% by weight, the alloy fails to have the abovementioned properties. When chromium content exceeds 28% by weight, the alloy has a decreased amount of the thermal shock resistance. Therefore, it is determined that chromium content should be 10 to 28% by weight.
Iron: Iron is dissolve into an alloy matrix and enhance the thermal shock resistance and the toughness. Iron is added as the alternative to the expensive nickel component in view of the cost. When iron contents are below 1% by weight, the resultant alloy have not sufficiently the economical use. When iron contents exceed 30% by weight, the resultant alloy is deteriorated the strength at elevated temperature. Therefore, it is determined that iron content should be 1 to 30% by weight, furthermore preferably 3 to 30% by weight.
Titanium: Titanium not only suppresses a growth of a crystal grain in the alloy matrix but atomize preferably the crystal grain. Titanium reacts with carbon and nitrogen to form MC type carbide and nitride, further reacts with nickel and aluminium to form the intermetallic compound such as abovementioned {Ni.sub.3 (Al, Ti)}. The resultant alloy is improved in the strength and the wear resistance at elevated temperatures. When the titanium content is below 0.01% by weight, the alloy fails to have the abovementioned properties. When the titanium content exceeds 4.5% by weight, the resultant alloy is deteriorated in the toughness of the alloy due to accelerate the formation of carbide at elevated temperatures and further deteriorated the corrosion resistance at elevated temperature due to proceed remarkably the formation oxide at elevated temperatures. Therefore, it is determined that the titanium content should be 0.01 to 4.5% by weight, furthermore preferably 0.01 to 3.5% by weight.
Aluminium: The alloy is improved by the addition of aluminium the oxidation resistance and the corrosion resistance at elevated temperatures in the coexistence of chromium. As abovementioned, aluminium reacts with nickel and titanium to from the intermetallic compound such as {Ni.sub.3 (Al, Ti)}and further reacts with nitrogen to form nitride. The resultant is improved in the strength and the wear resistance at elevated temperatures and improved in the thermal shock resistance and the toughness. When the aluminium content is below 0.01% by weight, the alloy fails to have the abovementioned properties. When the aluminium content exceeds 4.5% by weight, the resultant alloy shows the decrease of the fluidity and the castability in the melt, as a result, the resultant alloy not only becomes difficulty the production in the casting but cannot make use of the production in practice because of the deterioration of the toughness and the weldability. Therefore, it is determined that the aluminium content should be 0.01 to 4.5% by weight, furthermore preferably, 0.01 to 3.5% by weight.
Tungsten: Tungsten is dissolved into an alloy matrix. Tungsten also reacts with carbon to form a carbide. The resultant alloy is improved in the hardness and the wear resistance at elevated temperatures. When tungsten content is below 0.1% by weight, the resultant alloy fails to have the abovementioned properties. When the tungsten content exceeds 10% by weight, the resultant alloy is improved the wear resistance, but also is deteriorated the toughness and the thermal shock. Therefore, it is determined that the tungsten content should be 0.1 to 10% by weight, furthermore preferably 0.5 to 10% by weight.
Molybdenum: The alloy is improved by the addition of molybdenum the wear resistance at elevated temperatures similar to tungsten component. When molybdenum content is below 0.1% by weight, the resultant alloy fails to have the abovementioned properties. When the molybdenum content exceeds 10% by weight, the resultant alloy is deteriorated the toughness and the thermal shock resistance. Therefore, it is determined that the molybdenum content should be 0.1 to 10% by weight, furthermore preferably 0.5 to 10% by weight.
Silicon: The alloy is improved by the additon of silicon the thermal resistance, the deoxidation effect and the fluidity of the melt similar to chromium. The resistant alloy is improved in the castability and the strength at elevated temperatures. When the silicon content is below 0.1% by weight, the resultant alloy fails to have the abovementioned properties. When the silicon content exceeds 3% by weight, the resultant alloy is deteriorated the toughness and the weldability in the relation of chromium component. Therefore, it is determined that the silicon content should be 0.1 to 3% by weight. When silicon is used as the deoxidation agent, however, silicon includes below 0.1% by weight of the incidental impurities. It is suitable in this case that the silicon included with the incidental impurities is added over 0.1% by weight.
Manganese: Manganese is dissolved into the alloy matrix to stabilize the austenite matrix. The resultant alloy is improved in the thermal shock resistance and the wear resistance at elevated temperatures and the effect of the deoxidation. When the manganese content is below 0.1% weight, the resultant alloy fails to have the abovementioned properties. When the manganese content exceeds 3% by weight, the resultant alloy is deteriorated the corrosion resistance at elevated temperatures. Therefore, it is determined that the manganese content should be 0.1 to 3% by weight. Manganese component similar to silicon component includes below 0.1% by weight of the incidental impurities. It is suitable in this case that the manganese included with the incidental impurities is added over 0.1% by weight.
Cobalt: Cobalt is dissolved into the austenite matrix to improve the strength at elevated temperatures. The resultant alloy is improved in the wear resistance and the thermal shock resistance at elevated temperatures. When the cobalt content is below 1% by weight, the resultant alloy fails to have the abovementioned properties. When the cobalt content exceeds 8% by weight, the resultant alloy does not show more effective improvement but rather than shows the decrease of the abovementioned properties. Therefore, it is determined that the cobalt content should be 1 to 8% by weight.
Nitrogen: Nitrogen is dissolved into the austenite matrix to stabilize the alloy. Nitrogen also reacts with a metal component to form the nitride of the metal. The resultant alloy is improved in the strength at elevated temperatures. When the resultant alloy is required to have the strength at elevated temperatures, the nitrogen component is included optionally in the alloy. When the nitrogen content is below 0.005% by weight, the resultant alloy does not improve in more effective strength at elevated temperatures. When the nitrogen content exceeds 0.2% by weight, the resultant alloy not only has an increased amount of nitride but has a gross particle of the nitride. The resultant alloy is a brittle alloy and is deteriorated in the thermal shock resistance. Therefore, it is determined that the nitrogen content should be 0.005 to 0.2% by weight.
Niobium and tantalum: The alloy is suppressed by the addition of these component specially to the growth of the crystal in the alloy matrix. These component also react with carbon and nitrogen to form the MC type carbide and the nitride. The resultant alloy is improved in the strength and the wear resistance at elevated temperatures, also improved more homogenized action. When the resultant alloy is required to have the abovementioned properties, niobium and tantalum is added optionally into the alloy. When niobium and tantalum content are below 0.01% by weight, the resultant alloy fails to have the abovementioned properties. When niobium and tantalum content exceed 1.5% by weight, the resistant alloy is deteriorated in the corrosion resistance due to increase the growth of the oxide at elevated temperatures and furthermore deteriorated the toughness and the wear resistance due to increase extraordinarily the formation of the carbide. Therefore, it is determined that niobium and tantalum content should be 0.01 to 1.5% by weight.
Boron and zirconium: The alloy is improved by the addition of these component the homogenized action and the strength, the wear resistance, the thermal shock resistance and the corrosion resistant at elevated temperatures. When boron and zirconium contents are below 0.001% by weight, the resultant alloy fail to have the abovementioned properties. When boron and zirconium contents exceed 0.2% by weight, the resultant alloy is deteriorated in the toughness, the thermal shock resistance, the castability and the weldability. Therefore, it is determined that boron and zirconium content should be 0.001 to 0.2% by weight.
Nickel: Nickel in included as remainder in the alloy of this invention. Nickel is dissolved into an alloy matrix to stabilize austenite matrix and enhance the thermal shock resistance and the toughness. On the other hand, nickel reacts with aluminium and titanium to form an intermetallic compound such as {Ni.sub.3 (Al. Ti)}, furthermore the resultant alloy is improved in the strength and the wear resistance at elevated temperatures similar to chromium.
Each metal components are weighted and heated by the usual high frequency melting furnace under atmospheric pressure at 1400 to 1700.degree. C. for 20 to 30 min. to form the melt. The melt is casted into the sand mold and the casted alloy is prepared each of the test piece for the test. These test piece are used for the many test, such as the hardness, the impact resistance at room temperature, the thermal shock resistance and the wear resistance. The thermal shock resistance test is carried out by the repetition of the rapid heating and the rapid cooling under nearly conditions of the practical machine.
The hardness test is carried out by the measurement of Vickers hardness at room temperature, at 900.degree. C. and at 1000.degree. C. The Ohgoshi type intermetallic wear resistance test is carried out under the load of 18.2 kg, the wear velocity of 0.083 m/sec. at room temperature in the dry condition. The opposited metal having over 57 of Rockwell hardness (H.sub.R C) of the metal such as SUJ-2 is used in this test. The amount of the specific wear is estimated by the measurement of the wear resistance to the test piece. Furthermore, the test piece used for thermal shock resistance test is prepared to form in rectangular pillar shape of 12 mm.times.12 mm.times.30 mm having the recess of the spherical surface at the center of the pillar end. The thermal shock test comprises to repeating a cycle which the test piece is heated by oxygen-propane gas burner to hold at about 900.degree. C. at the recess of the spherical surface for 30 sec. and thereafter are cooled at once by blowing off with the water spray to hold at about 200.degree. C. at the recess of the spherical surface. This cycle are carried out repeatly and at every three time the test piece is observed the detection of the crack by the fluorecence permeation at the recess of the spherical surface and measured the occurrence of the crack. If the number of the cycle which the crack occurred at the test piece is over 30, the notation of the thermal shock resistance refers to >30 in the TABLE as follows. In other words, it is meant that the notation of >30 does not are observed the occurrence of the crack at the recess of the spherical surface till the repetition of thermal shock resistance test of 30 times.

The composition and the properties of comparative alloy are showed to compare with the thermal and resistant, tough alloy at elevated temperatures according to this invention in the TABLE. The content of the component put on asteristic sign at the shoulder of the numeral in comparative alloy are showed to have a different composition content from the scope of the alloy according to this invention. Furthermore, the alloy of prior art are showed in the relation with the alloy of this invention. The percentage of content refers to the percentage by weight as follow.
EXAMPLE 1
C-Cr-Fe-W-Mo-Ti-Al-Ni ALLOY As are shown in TABLE 1-1, TABLE 1-2, TABLE 1-3, and TABLE 1-4, each metal component is weighted, added to mixing, and heated by the usual high frequency melting furnace under the atmosphere to form the melt and thereafter the melt is casted into the said mold to prepare the casting.
The composition of Nos. 1 to 15 show C-Cr-Fe-W-Mo-Ti-Al-Ni base alloy according to this invention. Furthermore, Nos. 16 to 18 show the abovementioned alloy included silicon and Nos. 19 to 21 show the alloy included manganese and Nos. 22 to 23 show the alloy included nitrogen. Nos. 24 to 57 also show the abovementioned alloy including optionally at least one selected from the group consisting of silicon, manganese, nitrogen, niobium, tantalum, boron and zirconium.
The comparative alloy of Nos. 58 to 70 show to include the content of the composition that the content were without the scope of this invention according to C-Cr-Fe-W-Mo-Ti-Al-Ni alloy. Furthermore, the prior art alloy of Nos. 71 to 72 show to include the content of the composition.
As are shown in TABLE 2-1, TABLE 2-2, and TABLE 2-3, the results of the properties of the alloy is shown each Vickers hardness at room temperature, at 900.degree. C., and at 1000.degree. C., furthermore Charpy impact strength at room temperature, the amount of the specific wear, and the number of the cycle till the occurrence of the crack.
No. 8 in TABLE 1 consists essentially of 0.98% by weight of carbon, 15.53% of chromium, 17.87% of iron, 0.11 of tungsten, 8.75% of molybdenum, 0.64% of titanium, 0.62% of aluminium and the balance nickel (% refers to percent by weight). The properties of No. 8 alloy is shown in TABLE 2-1. For example, No. 8 alloy show 365 of Vickers hardness at room temperature, 231 at 900.degree. C., 172 at 1000.degree. C., and 1.46 kg-m/cm.sup.2 of Charpy impact strength, 1.32.times.10.sup.-7 of the amount of the specific wear, >30 of the number of the cycle till the occurrence of the crack.
The comparative alloy of No. 62 consists essentially of 1.08% by weight of carbon, 20.18% of chromium, 31.91% of iron, 0.02% of titanium, 1.62% of aluminium, 9.01% of tungsten, 2.01% of molybdenum and the balance nickel (% refers to percent by weight). This No. 62 showed >30 as the number of the cycle till the occurrence of the crack in TABLE 2-3. The No. 62 also is shown 2.84.times.10.sup.-7 of the amount of the specific wear, 2.83 kg-m/cm.sup.2 of Charpy impact strength at room temperature, 294 of Vickers hardness at room temperature, 133 at 900.degree. C., and 110 at 1000.degree. C.
The prior art alloy No. 72 consists essentially of 1.28% by weight of carbon, 33.92% of chromium, 17.89% of iron, 3.06% of tungsten, 2.98% of molybdenum, 4.98% of copper and the balance nickel (% refers to percent by weight). This No. 72 alloy showed 3 as the number of the cycle till the occurrence of the crack, 1.97.times.10.sup.-7 of the amount of the specific wear, 0.43 kg-m/cm.sup.2 Charpy impact strength at room temperature, 305 of Vickers hardness at room temperature, 143 at 900.degree. C., and 130 at 1000.degree. C.
These alloys are shown the content of the composition and the properties of the alloy in TABLE 1-1, TABLE 1-2, TABLE 1-3, TABLE 1-4 and TABLE 2-1, TABLE 2-2, TABLE 2-3, respectively.
TABLE 1__________________________________________________________________________ COMPONENT OF COMPOSITION (% by weight) C Cr Fe W Mo Ti Al Si Mn N Nb Ta B Zr Ni__________________________________________________________________________ALLOY .rarw.OF THISINVENTION 1 0.58 20.11 26.96 4.94 5.06 1.54 0.12 -- -- -- -- -- -- -- bal. 2 1.34 20.12 26.98 4.95 5.04 1.52 0.14 -- -- -- -- -- -- -- bal. 3 1.97 20.10 26.97 4.97 5.03 1.52 0.11 -- -- -- -- -- -- -- bal. 4 0.86 10.5 18.01 5.96 4.58 1.55 0.06 -- -- -- -- -- -- -- bal. 5 0.83 27.3 18.03 5.93 4.55 1.57 0.03 -- -- -- -- -- -- -- bal. 6 1.05 20.20 1.2 8.94 2.00 0.04 1.51 -- -- -- -- -- -- -- bal. 7 1.07 20.21 29.7 8.98 2.04 0.03 1.60 -- -- -- -- -- -- -- bal. 8 0.98 15.53 17.87 0.11 8.75 0.64 0.62 -- -- -- -- -- -- -- bal. 9 0.97 15.54 17.86 9.87 2.19 0.65 0.64 -- -- -- -- -- -- -- bal.10 1.02 15.55 17.88 8.79 0.11 0.63 0.65 -- -- -- -- -- -- -- bal.11 1.03 15.57 17.90 1.56 9.93 0.62 0.63 -- -- -- -- -- -- -- bal.12 0.92 20.08 18.03 6.06 3.04 0.012 3.57 -- -- -- -- -- -- -- bal.13 0.89 20.05 18.00 6.01 3.01 4.47 0.015 -- -- -- -- -- -- -- bal.14 0.93 20.04 18.03 5.03 4.06 3.30 0.011 -- -- -- -- -- -- -- bal.15 0.90 20.01 18.04 5.05 4.03 0.014 4.45 -- -- -- -- -- -- -- bal.16 0.99 15.20 18.06 5.21 3.07 1.39 0.10 0.11 -- -- -- -- -- -- bal.17 1.00 15.18 18.03 5.18 3.04 1.40 0.09 1.49 -- -- -- -- -- -- bal.18 0.96 15.16 18.00 5.20 3.01 1.38 0.10 2.94 -- -- -- -- -- -- bal.19 1.00 25.10 7.90 6.76 3.22 0.10 1.05 -- 0.12 -- -- -- -- -- bal.20 0.97 25.09 7.88 6.78 3.24 0.12 1.03 -- 1.48 -- -- -- -- -- bal.21 0.98 25.11 7.87 6.77 3.22 0.10 1.03 -- 2.98 -- -- -- -- -- bal.22 1.24 15.03 10.04 5.00 4.99 0.60 0.14 0.81 -- 0.084 -- -- -- -- bal.23 1.22 15.04 10.01 5.02 4.97 0.59 0.13 -- 0.74 0.059 -- -- -- -- bal.24 1.00 20.06 18.06 6.04 3.00 2.03 0.97 -- -- -- 0.012 -- -- -- bal.25 0.99 20.05 18.07 6.02 3.03 2.04 0.98 -- -- -- 0.96 -- -- -- bal.26 0.98 20.02 18.06 6.03 3.01 2.02 0.96 -- -- -- 1.47 -- -- -- bal.27 0.96 20.00 18.07 6.06 3.03 2.01 0.98 -- -- -- -- 0.013 -- -- bal.28 0.98 20.05 18.06 6.03 3.08 2.00 0.96 -- -- -- -- 0.99 -- -- bal.29 0.96 20.07 18.03 6.01 3.05 2.03 0.97 -- -- -- -- 1.49 -- -- bal.30 0.98 20.06 18.05 6.04 3.06 2.04 0.94 -- -- -- 0.40 0.41 -- -- bal.31 0.99 20.06 18.07 6.09 3.04 2.06 0.92 0.51 -- -- 0.96 -- -- -- bal.32 0.96 20.09 18.03 6.07 3.02 2.04 0.95 0.55 -- -- -- 0.93 -- -- bal.33 0.98 20.11 18.04 6.01 3.03 2.01 0.97 -- 0.84 -- 0.06 -- -- -- bal.34 0.96 20.12 18.06 6.04 3.07 2.05 0.97 -- 0.83 -- -- 0.05 -- -- bal.35 0.99 20.09 18.05 6.05 3.04 2.02 0.98 0.66 -- -- 0.35 0.36 -- -- bal.36 0.96 20.10 18.05 5.01 4.05 0.90 1.99 -- -- -- -- -- 0.0011 -- bal.37 0.97 20.09 18.07 5.04 4.04 0.91 1.97 -- -- -- -- -- 0.102 -- bal.38 0.96 20.07 18.05 5.03 4.03 0.93 1.98 -- -- -- -- -- 0.197 -- bal.39 0.98 20.13 18.17 5.14 4.15 1.05 2.06 -- -- -- -- -- -- 0.0012 bal.40 0.97 20.15 18.14 5.13 4.12 1.06 2.02 -- -- -- -- -- -- 0.098 bal.41 0.99 20.12 18.16 5.15 4.13 1.04 2.05 -- -- -- -- -- -- 0.198 bal.42 0.96 20.13 18.14 5.14 4.12 1.05 2.03 -- -- -- -- -- 0.0017 0.0019 bal.43 0.97 20.16 18.13 5.16 4.15 1.04 2.02 0.73 -- -- -- -- -- 0.0057 bal.44 0.99 20.15 18.15 5.13 4.13 1.02 2.00 -- 0.78 -- -- -- 0.074 -- bal.45 0.97 20.16 18.14 5.16 4.14 1.04 2.01 0.57 -- -- -- -- 0.050 0.047 bal.46 1.05 15.22 10.03 5.20 5.01 0.72 0.23 -- -- 0.080 -- 0.50 -- -- bal.47 1.06 15.23 10.01 5.18 5.04 0.74 0.20 -- -- 0.069 -- -- -- 0.042 bal.48 1.02 15.20 10.02 5.13 5.02 0.70 0.24 -- -- -- -- 1.00 0.0013 -- bal.49 0.80 20.00 18.03 6.00 3.02 1.96 0.86 0.40 -- 0.006 0.52 -- -- -- bal.50 0.81 20.02 18.06 6.04 3.04 1.95 0.85 0.17 -- 0.008 -- -- -- 0.122 bal.51 0.82 20.04 18.04 6.01 3.00 1.98 0.87 0.23 -- -- 1.03 -- 0.007 -- bal.52 0.83 20.05 18.05 6.03 3.02 1.97 0.86 -- 0.26 0.035 -- 0.79 -- -- bal.53 0.82 20.06 18.07 6.02 3.03 1.96 0.88 -- 0.19 0.007 -- -- 0.125 -- bal.54 0.84 20.07 18.02 6.01 3.05 1.90 0.86 -- 0.41 -- 0.59 -- 0.0016 0.0015 bal.55 0.80 20.03 18.04 6.03 3.02 1.91 0.85 -- -- 0.103 -- 0.58 -- 0.0013 bal.56 0.83 20.01 18.05 6.04 3.01 1.95 0.84 0.30 -- 0.006 0.50 0.53 -- 0.0017 bal.57 0.80 20.01 18.07 6.02 3.05 1.97 0.86 -- 0.51 0.008 0.35 0.20 0.002 0.003 bal.COMPARA-TIVEALLOY58 0.46* 20.13 26.95 4.95 5.05 1.55 0.13 -- -- -- -- -- -- -- bal.59 2.23* 20.11 26.94 4.97 5.01 1.54 0.14 -- -- -- -- -- -- -- bal.60 0.87 8.6* 18.04 5.96 4.59 1.58 0.05 -- -- -- -- -- -- -- bal.61 0.86 30.5* 18.02 5.96 4.54 1.59 0.04 -- -- -- -- -- -- -- bal.62 1.08 20.18 31.9*.sup.1 9.01 2.01 0.02 1.62 -- -- -- -- -- -- -- bal.63 0.99 15.54 17.89 --* 8.70 0.61 0.63 -- -- -- -- -- -- -- bal.64 0.96 15.56 17.90 10.91* 8.69 0.63 0.65 -- -- -- -- -- -- -- bal.65 1.04 15.57 17.89 8.80 --* 0.64 0.68 -- -- -- -- -- -- -- bal.66 1.02 15.56 17.87 1.53 10.81* 0.61 0.64 -- -- -- -- -- -- -- bal.67 0.94 20.10 18.05 6.05 3.06 --* 3.59 -- -- -- -- -- -- -- bal.68 0.90 20.06 18.04 6.02 3.04 4.63* 0.014 -- -- -- -- -- -- -- bal.69 0.94 20.02 18.05 5.05 4.07 3.32 --* -- -- -- -- -- -- -- bal.70 0.91 20.03 18.06 5.03 4.09 0.013 4.74* -- -- -- -- -- -- -- bal.prior art alloy71 1.32 25.89 bal. -- 0.50 -- -- 1.59 2.00 -- -- -- -- V: 11.0472 1.28 33.92 17.89 3.06 2.98 -- -- -- -- -- -- -- -- Cu: bal.__________________________________________________________________________
TABLE 2__________________________________________________________________________ VICKERS HARDNESS Charpy impact Amount Number cycle at room strength specific till occurrence temp. 900.degree. C. 1000.degree. C. kg -m/cm.sup.2 wear .times. 10.sup.-7 of crack__________________________________________________________________________ALLOYOF THISINVENTION 1 316 153 143 1.87 1.95 >30 2 335 174 152 1.78 1.76 >30 3 382 254 189 1.18 1.06 30 4 329 152 140 2.33 1.61 >30 5 356 193 180 1.57 1.36 30 6 344 181 157 1.99 1.79 >30 7 321 150 138 2.70 2.00 >30 8 365 231 172 1.46 1.32 >30 9 382 252 203 1.37 1.00 2710 364 231 172 1.90 1.37 >3011 381 247 198 1.40 1.01 2712 335 173 147 1.20 1.59 >3013 384 259 196 1.17 0.99 2414 338 176 151 1.29 1.50 >3015 411 275 219 1.11 0.96 2116 325 151 139 1.76 1.94 >3017 348 169 151 1.78 1.81 >3018 376 174 158 1.32 1.41 3019 345 163 150 1.80 1.76 >3020 342 161 147 1.92 1.61 >3021 321 150 138 2.00 1.50 >3022 379 251 170 1.47 1.14 >3023 356 243 164 1.65 1.21 >3024 323 155 139 2.24 1.72 >3025 331 193 148 2.00 1.61 >3026 353 231 173 1.90 1.42 >3027 328 157 140 1.97 1.72 >3028 337 196 154 1.90 1.63 >3029 356 238 175 1.83 1.40 >3030 352 226 170 1.64 1.18 >3031 360 231 173 1.48 1.16 >3032 361 232 175 1.44 1.10 >3033 342 159 144 1.90 1.61 >3034 344 161 147 1.86 1.59 >3035 358 237 175 1.85 1.54 >3036 350 224 149 1.84 1.28 >3037 355 228 157 1.79 1.14 3038 362 231 176 1.65 1.00 2739 347 220 144 1.90 1.31 >3040 352 223 155 1.81 1.19 3041 358 226 172 1.70 1.07 2742 351 224 151 1.76 1.24 >3043 349 221 148 1.89 1.18 >3044 347 220 147 1.90 1.21 >3045 352 227 152 1.76 1.09 >3046 358 250 158 1.59 1.00 >3047 357 242 156 1.70 1.00 >3048 365 253 162 1.61 0.93 >3049 358 247 156 1.64 0.99 >3050 369 252 176 1.81 0.92 3051 359 248 158 1.62 0.94 >3052 364 246 168 1.94 0.95 >3053 376 258 179 1.75 0.91 3054 350 221 154 1.81 1.22 >3055 364 253 162 1.57 0.90 3056 365 254 175 1.93 0.99 >3057 366 256 183 1.90 0.97 >30COMPARA-TIVE ALLOY58 293 134 119 0.96 3.62 >3059 418 273 228 0.63 0.82 1560 296 121 93 2.44 2.71 >3061 362 198 188 0.62 1.43 1562 294 133 110 2.83 2.84 >3063 276 114 98 1.69 1.93 >3064 410 265 223 0.39 0.87 665 279 115 103 1.64 1.88 >3066 406 256 215 0.42 0.90 667 311 133 119 0.86 2.19 >3068 432 293 238 0.52 0.80 669 310 126 109 1.00 2.45 >3070 452 298 247 0.41 0.72 3prior art alloy71 259 77 64 0.89 3.28 1872 305 143 130 0.43 1.97 3__________________________________________________________________________
EXAMPLE 2
C-Cr-Fe-W-Mo-Co-Ti-Al-Ni ALLOY The thermal and wear resistant, tough at elevated temperatures alloy in this invention are shown in EXAMPLE 2. The alloy is different from the content of the composition that the cobalt included one to 8% by weight in comparison with the alloy of EXAMPLE 1.
Alloys of Nos. 73 to 134 according to this invention, the comparative alloys of Nos. 135 to 148 and the prior art alloys of Nos. 149 to 150 are shown in TABLE 3-1, TABLE 3-2, TABLE 3-3 and TABLE 3-4 respectively. Furthermore similar to EXAMPLE 1, the properties of these alloys are shown in TABLE 4-1, TABLE 4-2, TABLE 4-3, respectively. No. 80 alloy in TABLE 3-1 consists essentially of 0.99% by weight of carbon, 15.50% chromium, 17.86% of iron, 0.12% of tungsten, 8.73 of molybdenum, 4.02% of cobalt, 0.62% of titanium, 0.65% of aluminium and the balance nickel (% refers to percent by weight). No 80 alloy is shown 369 of Vickers hardness at room temperature, 236 at 900.degree. C., and 177 at 1000.degree. C. in TABLE 4-1. No. 80 alloy also is shown 1.39 kg-m/cm.sup.2 of Charpy impact strength at room temperature, 1.29.times.10.sup.-7 of the amount of the specific wear, >30 of the number of the cycle till the occurrence of the crack. No. 80 alloy is improved in the hardness, the wear resistance at elevated temperatures due to include the content of cobalt in comparison with No. 6 of EXAMPLE 1.
In the comparison with comparative alloys (Nos. 135 to 148) and prior art alloys (Nos. 149 to 150), for example, No. 80 alloy of this invention is shown >30 of the number of the cycle till the occurrence of the crack, 177 of Vickers hardness at 1000.degree. C., on other hand No. 149 alloy of prior art showed 18 of the number of the cycle till the occurrence of the crack, 64 of Vickers hardness at 1000.degree. C.
The scope of the composition in this invention and its properties showed in TABLE 3-1, TABLE 3-2, TABLE 3-3, TABLE 3-4 and TABLE 4-1, TABLE 4-2, TABLE 4-3, respectively.
TABLE 3__________________________________________________________________________ COMPONENT OF COMPOSITION (% by weight) C Cr Fe W Mo Co Ti Al Si Mn N Nb Ta B Zr Ni__________________________________________________________________________ALLOYOF THISINVENTION73 0.57 20.13 26.98 4.91 5.08 5.00 1.53 0.11 -- -- -- -- -- -- -- bal.74 1.19 20.14 26.96 4.93 5.05 5.03 1.55 0.13 -- -- -- -- -- -- -- bal.75 1.96 20.11 26.95 4.95 5.02 5.04 1.54 0.10 -- -- -- -- -- -- -- bal.76 0.84 10.2 18.00 5.95 4.59 2.10 1.59 0.06 -- -- -- -- -- -- -- bal.77 0.85 27.5 18.06 5.94 4.56 2.09 1.56 0.02 -- -- -- -- -- -- -- bal.78 1.06 20.19 1.1 8.95 2.03 5.00 0.05 1.62 -- -- -- -- -- -- -- bal.79 1.08 20.24 29.7 8.99 2.06 5.04 0.02 1.59 -- -- -- -- -- -- -- bal.80 0.99 15.50 17.86 0.12 8.73 4.02 0.62 0.65 -- -- -- -- -- -- -- bal.81 0.98 15.53 17.88 9.89 2.13 4.04 0.61 0.63 -- -- -- -- -- -- -- bal.82 1.04 15.56 17.89 8.79 0.11 4.06 0.67 0.66 -- -- -- -- -- -- -- bal.83 1.01 15.58 17.91 1.58 9.92 4.01 0.65 0.64 -- -- -- -- -- -- -- bal.84 1.33 25.95 18.01 5.20 5.00 1.1 0.60 0.67 -- -- -- -- -- -- -- bal.85 1.32 25.96 18.00 5.19 5.03 7.9 0.62 0.64 -- -- -- -- -- -- -- bal.86 0.90 20.10 18.01 6.04 3.02 1.55 0.012 3.54 -- -- -- -- -- -- -- bal.87 0.91 20.09 18.04 6.06 3.05 1.52 4.48 0.013 -- -- -- -- -- -- -- bal.88 0.92 20.02 18.01 5.01 4.09 2.08 3.27 0.012 -- -- -- -- -- -- -- bal.89 0.91 20.04 18.05 5.06 4.07 2.10 0.015 4.46 -- -- -- -- -- -- -- bal.90 1.00 15.19 18.00 5.18 3.09 3.00 1.37 0.11 0.011 -- -- -- -- -- -- bal.91 0.98 15.17 18.04 5.20 3.06 3.01 1.39 0.10 1.46 -- -- -- -- -- -- bal.92 0.99 15.19 18.02 5.19 3.04 3.00 1.37 0.11 2.93 -- -- -- -- -- -- bal.93 0.99 25.00 7.89 6.72 3.20 4.60 0.11 1.04 -- 0.0053 -- -- -- -- -- bal.94 0.97 25.06 7.86 6.78 3.21 4.61 0.13 1.05 -- 1.46 -- -- -- -- -- bal.95 0.99 25.03 7.88 6.79 3.19 4.59 0.14 1.07 -- 2.98 -- -- -- -- -- bal.96 1.22 15.05 10.03 5.06 4.99 2.05 0.60 0.12 -- -- 0.0051 -- -- -- -- bal.97 1.18 15.08 10.06 5.04 4.97 2.03 0.61 0.14 -- -- 0.098 -- -- -- -- bal.98 1.21 15.07 10.04 5.03 4.98 2.06 0.60 0.11 -- -- 0.198 -- -- -- -- bal.99 1.23 15.05 10.02 5.01 5.00 2.04 0.61 0.13 0.83 -- 0.089 -- -- -- -- bal.100 1.22 15.06 10.03 5.04 4.99 2.02 0.64 0.12 -- 0.76 0.058 -- -- -- -- bal.101 0.98 20.04 18.05 6.01 3.01 2.50 2.05 0.99 -- -- -- 0.011 -- -- -- bal.102 0.97 20.03 18.04 6.05 3.00 2.47 2.06 0.96 -- -- -- 0.96 -- -- -- bal.103 0.95 20.01 18.02 6.04 3.02 2.49 2.03 0.98 -- -- -- 1.48 -- -- -- bal.104 0.98 20.04 18.03 6.08 3.06 2.57 1.99 0.99 -- -- -- -- 0.013 -- -- bal.105 0.99 20.01 18.04 6.05 3.07 2.55 2.01 1.00 -- -- -- -- 1.04 -- -- bal.106 0.97 20.05 18.06 6.04 3.03 2.58 2.00 0.98 -- -- -- -- 1.47 -- -- bal.107 0.96 20.09 18.04 6.07 3.02 2.56 2.01 0.96 -- -- -- 0.42 0.40 -- -- bal.108 0.95 20.10 18.05 6.06 3.01 2.52 2.03 0.92 0.50 -- -- 0.98 -- -- -- bal.109 0.97 20.08 18.07 6.04 3.04 2.53 2.02 0.94 0.52 -- -- -- 0.96 -- -- bal.110 0.98 20.10 18.05 6.03 3.06 2.55 2.00 0.96 -- 0.87 -- 0.05 -- -- -- bal.111 0.99 20.09 18.07 6.05 3.04 2.54 2.03 0.98 -- 0.89 -- -- 0.06 -- -- bal.112 0.97 20.11 18.09 6.07 3.03 2.52 2.01 0.97 0.65 -- -- 0.34 0.36 -- -- bal.113 0.99 20.09 18.06 5.03 4.07 2.04 0.93 1.98 -- -- -- -- -- 0.0011 -- bal.114 0.97 20.07 18.08 5.06 4.06 2.05 0.92 1.96 -- -- -- -- -- 0.099 -- bal.115 0.95 20.04 18.09 5.04 4.10 2.03 0.92 1.97 -- -- -- -- -- 0.197 -- bal.116 0.97 20.11 18.15 5.13 4.14 2.07 1.07 2.04 -- -- -- -- -- -- 0.0012 bal.117 0.98 20.13 18.14 5.15 4.10 2.06 1.08 2.01 -- -- -- -- -- -- 0.104 bal.118 0.96 20.11 18.16 5.12 4.11 2.04 1.06 2.03 -- -- -- -- -- -- 0.199 bal.119 0.97 20.12 18.15 5.12 4.10 2.03 1.07 2.00 -- -- -- -- -- 0.0016 0.0018 bal.120 0.99 20.14 18.16 5.14 4.12 2.05 1.08 2.01 0.70 -- -- -- -- -- 0.0052 bal.121 0.98 20.15 18.13 5.15 4.11 2.03 1.03 2.00 -- 0.77 -- -- -- 0.076 -- bal.122 0.97 20.14 18.17 5.13 4.14 2.04 1.05 2.03 0.59 -- -- -- -- 0.054 0.049 bal.123 1.06 15.21 10.04 5.19 5.00 2.02 0.70 0.24 -- -- 0.083 0.51 -- -- -- bal.124 1.07 15.20 10.03 5.17 5.01 2.03 0.73 0.21 -- -- 0.071 -- -- -- 0.046 bal.125 1.03 15.22 10.06 5.11 5.04 2.01 0.74 0.22 -- -- -- 1.01 -- -- 0.0012 bal.126 0.81 20.03 18.00 6.03 3.01 2.50 1.98 0.87 0.41 -- 0.007 -- 0.53 -- -- bal.127 0.82 20.01 18.07 6.02 3.00 2.49 1.96 0.85 0.24 -- 0.013 -- -- 0.003 -- bal.128 0.84 20.04 18.06 6.04 3.03 2.48 1.97 0.86 0.15 -- -- -- 0.07 -- 0.124 bal.129 0.81 20.02 18.08 6.05 3.04 2.50 1.96 0.87 -- 0.23 0.033 0.78 -- -- -- bal.130 0.83 20.03 18.07 6.02 3.02 2.50 1.98 0.88 -- 0.20 0.006 -- -- 0.126 -- bal.131 0.80 20.05 18.06 6.04 3.01 2.49 1.99 0.86 -- 0.59 -- -- 0.87 -- 0.007 bal.132 0.82 20.02 18.05 6.05 3.03 2.51 1.95 0.85 -- -- 0.007 -- 0.30 0.005 0.003 bal.133 0.82 20.05 18.00 6.07 3.09 2.51 1.99 0.89 0.51 -- 0.056 -- 0.62 -- 0.005 bal.134 0.83 20.03 18.03 6.09 3.08 2.50 2.01 0.87 -- 0.53 0.009 0.32 0.21 0.003 0.002 bal.135 0.50* 20.12 26.97 4.90 5.09 5.01 1.54 0.12 -- -- -- -- -- -- -- bal.136 2.13* 20.15 26.98 4.95 5.03 5.00 1.56 0.15 -- -- -- -- -- -- -- bal.137 0.86 8.9* 18.02 5.96 4.57 2.10 1.55 0.07 -- -- -- -- -- -- -- bal.138 0.84 31.3* 18.05 5.95 4.53 2.07 1.57 0.03 -- -- -- -- -- -- -- bal.139 1.06 20.20 31.1* 9.03 2.02 5.05 0.01 1.61 -- -- -- -- -- -- -- bal.140 1.00 15.51 17.88 --* 8.75 4.01 0.65 0.64 -- -- -- -- -- -- -- bal.141 0.98 15.53 17.89 11.03* 8.73 4.03 0.64 0.62 -- -- -- -- -- -- -- bal.142 1.03 15.58 17.87 8.80 --* 4.07 0.65 0.67 -- -- -- -- -- -- -- bal.143 1.02 15.57 17.89 1.54 10.89* 4.03 0.62 0.65 -- -- -- -- -- -- -- bal.144 1.34 25.90 18.04 5.21 5.02 --* 0.63 0.68 -- -- -- -- -- -- -- bal.145 0.92 20.13 18.06 6.07 3.05 1.59 --* 3.57 -- -- -- -- -- -- -- bal.146 0.89 20.07 18.03 6.06 3.06 1.54 4.71* 0.015 -- -- -- -- -- -- -- bal.147 0.94 20.05 18.04 5.04 4.08 2.10 3.29 --* -- -- -- -- -- -- -- bal.148 0.93 20.02 18.03 5.06 4.07 2.12 0.014 4.69* -- -- -- -- -- -- -- bal.prior art alloy149 1.32 25.89 bal. -- 0.50 -- -- -- 1.59 2.00 -- -- -- -- V: 11.04150 1.28 33.92 17.89 3.06 2.98 -- -- -- 0.83 0.76 -- -- -- -- Cu: bal.__________________________________________________________________________
TABLE 4__________________________________________________________________________ VICKERS HARDNESS Charpy impact Amount Number cycle at room strength specific till occurrence temp. 900.degree. C. 1000.degree. C. kg -m/cm.sup.2 wear .times. 10.sup.-7 of crack__________________________________________________________________________ALLOYOF THISINVENTION73 319 161 150 1.82 1.89 >3074 340 182 157 1.75 1.73 >3075 391 258 192 1.05 0.98 3076 331 157 143 2.21 1.59 >3077 360 198 185 1.53 1.26 3078 349 186 162 1.91 1.77 >3079 326 152 141 2.64 1.98 >3080 369 236 177 1.39 1.29 >3081 387 257 208 1.30 0.93 2782 368 235 176 1.89 1.32 >3083 386 252 203 1.31 0.96 2784 331 168 145 1.99 1.92 >3085 350 189 178 2.14 1.42 >3086 340 178 151 1.16 1.53 >3087 389 264 201 1.09 0.96 2488 343 180 155 1.20 1.43 >3089 416 279 223 1.03 0.92 2190 329 156 141 1.74 1.92 >3091 351 172 155 1.71 1.78 >3092 379 178 163 1.22 1.37 3093 349 169 155 1.77 1.74 >3094 347 166 151 1.86 1.52 >3095 326 155 142 1.92 1.47 >3096 353 221 155 1.59 1.28 >3097 385 254 173 1.46 1.12 3098 435 293 266 1.08 0.91 2199 384 256 175 1.41 1.03 >30100 360 248 170 1.55 1.10 >30101 328 159 143 2.17 1.68 >30102 336 198 152 2.06 1.59 >30103 358 236 178 1.92 1.34 >30104 331 162 145 2.01 1.67 >30105 342 201 157 1.98 1.54 >30106 360 242 179 1.90 1.31 >30107 359 230 175 1.50 1.09 >30108 363 234 178 1.43 1.06 >30109 364 236 179 1.41 1.05 >30110 345 163 149 1.87 1.54 >30111 346 165 150 1.85 1.53 >30112 362 241 181 1.85 1.44 >30113 354 228 153 1.82 1.17 >30114 359 231 162 1.76 1.03 30115 365 236 180 1.63 0.98 27116 352 225 151 1.84 1.20 >30117 357 228 160 1.82 1.13 30118 362 233 178 1.76 1.04 27119 355 228 155 1.74 1.16 >30120 353 226 153 1.82 1.12 >30121 352 225 152 1.84 1.14 >30122 357 230 157 1.72 1.06 >30123 363 254 162 1.53 0.98 >30124 361 247 160 1.61 0.99 >30125 371 258 166 1.54 0.87 >30126 362 251 160 1.55 0.96 >30127 365 253 164 1.57 0.94 >30128 374 257 180 1.80 0.90 30129 370 251 173 1.90 0.93 >30130 380 263 184 1.72 0.87 30131 368 249 171 1.93 0.95 >30132 371 253 174 1.91 0.90 >30133 373 256 190 1.76 0.96 >30134 370 252 187 1.89 0.94 >30COMPARA-TIVE ALLOY135 300 137 125 0.93 3.51 30136 423 279 233 0.53 0.70 12137 300 126 98 2.30 2.57 >30138 370 210 192 0.57 1.34 15139 303 132 115 2.67 2.68 >30140 281 122 107 1.61 1.72 >30141 418 275 230 0.32 1.90 6142 286 135 111 1.50 1.59 >30143 415 270 227 0.34 0.82 6144 308 134 120 2.20 2.14 >30145 323 135 122 0.85 2.10 >30146 438 304 246 0.48 0.70 6147 314 134 114 0.97 2.02 >30148 456 309 250 0.36 0.57 3prior art alloy149 259 77 64 0.89 3.28 18150 305 143 130 0.43 1.97 3__________________________________________________________________________
EXAMPLE 3
C-Si-Mn-Cr-Fe-W-Mo-Ti-Al-Ni ALLOY The alloys shown in EXAMPLE 3 are different from the content of the composition that the alloy include silicon and manganese in comparison with the alloy of EXAMPLE 1.
In EXAMPLE 4, the alloys according to this invention (Nos. 153 to 180), the comparative alloys (Nos. 181 to 197) and the prior art alloys (Nos. 151 to 152) are shown in TABLE 5-1, TABLE 5-2, TABLE 5-3 similar to EXAMPLE 1.
No. 157 of TABLE 5-1 consists essentially of 0.97% by weight of carbon, 1.63% of silicon, 0.67% of manganese, 15.10% of chromium, 17.98% of iron, 5.19% of tungsten, 3.04% of molybdenum, 1.21% of titanium, 0.15% of aluminium and the balance nickel (% refers to percent by weight).
Furthermore, the alloy of Nos. 176 to 190 include optionally at least one selected from the group consisting of 0.005 to 0.2% of nitrogen, 0.01 to 1.5% of niobium and tantalum, 0.001 to 0.2% of boron and zirconium.
The properties of Nos. 151 to 207 alloys are shown in TABLE 6-1, TABLE 6-2 similar to EXAMPLE 1. For example, No. 157 alloy is shown 349 of Vickers hardness at room temperature, 169 at 900.degree. C., 154 at 1000.degree. C. and 1.74 kg-m/cm.sup.2 of Charpy impact strength at room temperature, 1.80.times.10.sup.-7 of the amount of the specific wear and >30 of the number of the cycle till the occurrence of the crack. Alloys of EXAMPLE 3 are shown the component of the composition and its properties in TABLE 5-1, TABLE 5-2, TABLE 5-3 and TABLE 6-1, TABLE 6-2, respectively.
TABLE 5__________________________________________________________________________COMPONENT OF COMPOSITION (% by weight)C Si Mn Cr Fe W Mo Ti Al N Nb Ta B Zr Cu V Ni__________________________________________________________________________ Prior artalloy151 1.32 1.59 2.00 25.89 bal. -- 0.50 -- -- -- -- -- -- -- -- 0.18 11.04152 1.28 0.83 0.76 33.92 17.89 3.06 2.98 -- -- -- -- -- -- -- 4.98 -- bal.ALLOYOF THISINVEN-TION153 0.57 0.81 0.68 20.16 26.98 4.90 5.04 1.52 0.06 -- -- -- -- -- -- -- bal.154 1.24 0.83 0.69 20.22 27.14 5.03 5.08 1.50 0.08 -- -- -- -- -- -- -- bal.155 1.98 0.80 0.71 20.23 27.09 4.99 5.06 1.48 0.06 -- -- -- -- -- -- -- bal.156 0.98 0.12 0.70 15.09 18.04 5.18 3.01 1.20 0.13 -- -- -- -- -- -- -- bal.157 0.97 1.63 0.67 15.10 17.98 5.19 3.04 1.21 0.15 -- -- -- -- -- -- -- bal.158 0.94 2.95 0.69 15.12 18.07 5.15 3.06 1.20 0.11 -- -- -- -- -- -- -- bal.159 0.99 0.67 0.10 25.04 7.87 6.78 3.20 0.11 1.03 -- -- -- -- -- -- -- bal.160 0.97 0.68 1.59 24.99 7.90 6.80 3.21 0.13 1.05 -- -- -- -- -- -- -- bal.161 0.98 0.69 2.99 25.06 7.99 6.79 3.20 0.11 1.03 -- -- -- -- -- -- -- bal.162 0.84 0.70 0.72 10.52 18.06 5.88 4.63 1.58 0.06 -- -- -- -- -- -- -- bal.163 0.86 0.72 0.69 27.79 17.93 5.92 4.60 1.59 0.02 -- -- -- -- -- -- -- bal.164 1.01 0.69 0.80 20.18 3.12 8.96 2.04 0.02 1.48 -- -- -- -- -- -- -- bal.165 1.00 0.70 0.83 20.20 29.59 8.98 2.03 0.05 1.50 -- -- -- -- -- -- -- bal.166 0.97 0.66 0.79 15.42 17.98 0.53 8.68 0.50 0.53 -- -- -- -- -- -- -- bal.167 0.99 0.70 0.80 15.51 17.68 9.91 2.14 0.53 0.50 -- -- -- -- -- -- -- bal.168 1.00 0.62 0.79 15.48 17.92 8.70 0.52 0.50 0.54 -- -- -- -- -- -- -- bal.169 1.03 0.60 0.80 15.53 17.94 2.02 9.91 0.49 0.51 -- -- -- -- -- -- -- bal.170 0.91 0.68 0.79 20.04 18.00 6.04 3.11 0.013 2.50 -- -- -- -- -- -- -- bal.171 0.88 0.69 0.77 20.06 18.10 6.10 3.20 1.73 1.03 -- -- -- -- -- -- -- bal.172 0.89 0.66 0.79 20.03 18.08 6.04 3.09 3.47 0.07 -- -- -- -- -- -- -- bal.173 0.91 0.70 0.80 19.97 18.07 5.06 4.01 3.06 0.011 -- -- -- -- -- -- -- bal.174 0.90 0.71 0.81 20.02 18.10 5.10 4.06 0.96 1.69 -- -- -- -- -- -- -- bal.175 0.89 0.69 0.80 19.97 18.06 5.13 4.09 0.05 3.49 -- -- -- -- -- -- -- bal.176 1.16 0.70 0.78 15.07 10.11 5.07 4.98 0.57 0.07 0.0056 -- -- -- -- -- -- bal.177 1.18 0.70 0.80 15.00 10.01 5.00 4.99 0.60 0.11 0.103 -- -- -- -- -- -- bal.178 1.20 0.72 0.83 15.07 10.07 5.01 4.96 0.58 0.12 0.192 -- -- -- -- -- -- bal.179 0.92 0.71 0.80 20.00 18.02 6.08 3.02 2.03 0.98 -- 0.012 -- -- -- -- -- bal.180 0.94 0.70 0.78 20.11 18.08 6.09 3.10 1.98 0.99 -- -- 1.428 -- -- -- -- bal.181 0.90 0.70 0.80 20.07 18.01 6.03 3.06 1.96 0.93 -- 0.321 0.330 -- -- -- -- bal.182 0.97 0.69 0.78 19.99 18.08 5.09 4.10 0.93 1.97 -- -- -- 0.0012 -- -- -- bal.183 0.98 0.67 0.79 20.13 18.10 5.10 4.13 1.08 2.03 -- -- -- -- 0.195 -- -- bal.184 0.97 0.70 0.81 20.18 18.09 5.08 4.11 1.03 2.01 -- -- -- 0.052 0.051 -- -- bal.185 1.07 0.68 0.78 15.12 9.98 5.16 5.00 0.63 0.20 0.091 0.763 -- -- -- -- -- bal.186 1.06 0.71 0.81 15.14 10.03 5.23 4.98 0.59 0.17 0.064 -- 0.631 -- -- -- -- bal.187 1.08 0.69 0.80 15.20 10.08 5.26 4.99 0.61 0.19 0.080 -- -- 0.089 -- -- -- bal.188 1.04 0.70 0.79 15.13 10.06 5.18 5.00 0.57 0.16 0.073 -- -- -- 0.065 -- -- bal.189 0.92 0.69 0.78 20.02 18.10 6.00 3.12 1.97 0.93 -- 0.465 0.321 -- 0.033 -- -- bal.190 0.91 0.60 0.73 20.08 18.02 6.04 3.09 2.00 0.92 0.070 0.412 0.396 0.061 0.031 -- -- bal.COM-PAR-ATIVEALLOY191 0.50* 0.82 0.70 20.09 26.96 4.92 4.98 1.49 0.08 -- -- -- -- -- -- -- bal.192 2.14* 0.85 0.69 20.10 27.00 4.98 4.99 1.51 0.06 -- -- -- -- -- -- -- bal.193 1.01 --* 0.68 15.11 18.02 5.21 3.04 1.21 0.11 -- -- -- -- -- -- -- bal.194 1.04 3.24* 0.71 15.22 18.01 5.18 3.07 1.22 0.10 -- -- -- -- -- -- -- bal.195 1.00 0.68 --* 25.00 8.01 6.81 3.18 0.11 1.02 -- -- -- -- -- -- -- bal.196 0.98 0.70 3.16* 25.04 7.99 6.80 3.19 0.14 1.00 -- -- -- -- -- -- -- bal.197 0.85 0.72 0.70 9.01* 18.02 5.90 4.64 1.59 0.05 -- -- -- -- -- -- -- bal.198 0.89 0.69 0.72 30.01* 18.01 5.92 4.66 1.60 0.08 -- -- -- -- -- -- -- bal.199 1.04 0.70 0.80 20.16 32.03* 9.01 2.00 0.07 1.50 -- -- -- -- -- -- -- bal.200 0.99 0.71 0.79 15.51 18.01 --* 9.03 0.52 0.51 -- -- -- -- -- -- -- bal.201 1.00 0.68 0.80 15.50 17.70 11.03* 8.97 0.54 0.50 -- -- -- -- -- -- -- bal.202 1.02 0.59 0.81 15.49 18.00 8.84 --* 0.51 0.54 -- -- -- -- -- -- -- bal.203 1.00 0.69 0.79 15.52 17.99 2.01 10.85 0.49 0.50 -- -- -- -- -- -- -- bal.204 0.91 0.68 0.80 20.08 18.00 6.07 3.17 --* 2.51 -- -- -- -- -- -- -- zbal.205 0.92 0.71 0.79 20.02 18.05 6.08 3.11 3.59* 0.06 -- -- -- -- -- -- -- bal.206 0.90 0.66 0.81 20.01 18.05 5.09 4.07 3.01 --* -- -- -- -- -- -- -- bal.207 0.93 0.70 0.78 20.03 18.09 5.12 4.05 0.06 3.61* -- -- -- -- -- -- -- bal.__________________________________________________________________________
TABLE 6__________________________________________________________________________ VICKERS HARDNESS Charpy impact Amount Number cycle at room strength specific till occurrence temp. 900.degree. C. 1000.degree. C. kg -m/cm.sup.2 wear .times. 10.sup.-7 of crack__________________________________________________________________________prior art alloy151 259 77 64 0.89 3.28 18152 305 143 130 0.43 1.97 3ALLOYOF THISINVENTION153 319 158 147 1.84 1.92 >30154 340 179 159 1.77 1.76 >30155 387 259 193 1.11 1.02 30156 328 154 150 1.76 1.95 >30157 349 169 154 1.74 1.80 >30158 376 172 160 1.24 1.48 30159 347 166 152 1.78 1.79 >30160 345 163 148 1.87 1.60 >30161 326 154 141 1.96 1.47 >30162 330 157 143 2.16 1.58 >30163 359 193 182 1.53 1.26 30164 347 181 161 1.86 1.78 >30165 322 150 139 2.69 1.96 >30166 370 231 174 1.33 1.30 >30167 389 252 207 1.24 0.94 27168 367 230 172 1.31 1.30 >30169 384 249 199 1.30 0.98 27170 334 169 139 1.17 1.70 >30171 346 221 168 2.21 1.62 >30172 368 249 189 1.30 1.03 27173 336 170 141 1.20 1.67 >30174 357 229 173 1.98 1.50 >30175 394 270 214 1.28 1.00 27176 348 219 149 1.62 1.36 >30177 378 250 171 1.46 1.18 30178 428 283 257 1.10 0.98 21179 348 224 170 2.03 1.70 >30180 357 231 174 1.92 1.31 >30181 358 234 176 1.96 1.26 >30182 352 227 172 2.03 1.42 >30183 361 231 178 1.43 1.04 >30184 363 237 181 1.60 0.93 >30185 351 226 152 1.70 1.21 >30186 350 224 150 1.69 1.17 >30187 354 229 158 1.53 1.00 >30188 357 231 160 1.58 1.01 >30189 359 233 178 1.98 1.60 >30190 364 240 183 1.92 0.92 >30COMPARA-TIVE ALLOY191 302 139 124 0.95 3.57 >30192 421 276 230 0.61 0.73 15193 300 127 105 0.37 2.67 12194 394 208 182 0.58 1.38 15195 360 236 148 0.68 2.59 12196 306 136 124 2.08 1.22 >30197 300 126 97 2.41 2.61 >30198 367 201 190 0.64 1.42 15199 301 138 114 2.71 2.73 >30200 281 119 100 1.64 1.83 >30201 413 267 225 0.37 0.84 6202 284 120 107 1.59 1.72 >30203 410 261 221 0.39 0.81 6204 318 134 120 0.84 2.17 >30205 412 271 219 0.60 0.87 9206 311 130 113 0.98 2.34 >30207 423 280 224 0.51 0.80 6__________________________________________________________________________
EXAMPLE 4
C-Si-Mn-Cr-Fe-W-Mo-Co-Ti-Al-Ni ALLOY The alloys shown in EXAMPLE 4 are different from the content of the composition that the alloys include one to 8% by weight in comparison with alloys of EXAMPLE 3. Alloys of this invention (Nos. 210 to 247), comparative alloys (Nos. 248 to 265), and prior art alloys (Nos. 208 to 209) are shown the component of the composition in TABLE 7-1, TABLE 7-2, and TABLE 7-3. The properties of alloys are shown in TABLE 8-1 and TABLE 8-2.
No. 214 alloy consists essentially of 0.96% by weight of carbon, 1.67% of silicon. 0.66% of manganese, 15.13% of chromium, 18.01% of iron, 3.04% of cobalt, 5.14% of tungsten, 3.08% of molybdenum, 1.22% of titanium, 0.12% of aluminium, and the balance nickel (% refers to percent by weight).
Furthermore, alloys of Nos. 235 to 247 include optionally at least one selected from the group consisting of 0.005 to 0.2% of nitrogen, 0.01 to 1.5% of niobium and tantalum, and 0.001 to 0.2% of boron and zirconium.
The properties of Nos. 208 to 265 alloys are shown in TABLE 8-1 and TABLE 8-2 similar to EXAMPLE 1.
For example, No. 214 alloy is shown 352 of Vickers hardness at room temperature, 173 at 900.degree. C., 157 at 1000.degree. C. and 1.70 kg-m/cm.sup.2 of Charpy impact strength at room temperature 1.77.times.10.sup.-7 of the amount of the specific wear, and >30 of the number of the cycle till the occurrence of the crack.
No. 214 in EXAMPLE 4 include, 3.04% by weight of cobalt in comparison with alloy having similar composition of No. 157 in EXAMPLE 3. No. 157 alloy is shown 349 of Vickers hardness at room temperature, 169 at 900.degree. C., 154 at 1000.degree. C. Furthermore No. 157 alloy shows 1.74 kg-m/cm.sup.2 of Charpy impact strength at room temperature, 1.80.times.10.sup.-7 of the amount of the specific wear, >30 of the number of the cycle till the occurrence of the crack. The component of the composition and its properties are shown in TABLE 7-1, TABLE 7-2, TABLE 7-3 and TABLE 8-1, TABLE 8-2, respectively.
TABLE 7 COMPONENT OF COMPOSITION (% by weight) C Si Mn Cr Fe W Mo Co Ti Al N Nb T a B Zr Cu V Ni Prior art alloy 208 1.32 1.59 2.00 25.89 bal. -- 0.50 -- -- -- -- -- -- -- -- -- 0.18 11.04 209 1.28 0.83 0.76 33.92 17.89 3.06 2.98 -- -- -- -- -- -- -- -- 4.98 -- bal. ALLOY OF THIS INVENTION 210 0.56 0.87 0.70 20.20 27.03 4.89 5.10 4.89 1.51 0.08 -- -- -- -- -- -- -- bal. 211 1.21 0.84 0.68 20.19 27.10 5.01 5.09 4.98 1.49 0.07 -- -- -- -- -- -- -- bal. 212 1.97 0.79 0.69 20.23 27.08 4.97 5.04 4.95 1.47 0.05 -- -- -- -- -- -- -- bal. 213 0.99 0.11 0.68 15.18 18.09 5.16 3.07 3.01 1.25 0.11 -- -- -- -- -- -- -- bal. 214 0.96 1.67 0.66 15.13 18.01 5.14 3.08 3.04 1.22 0.12 -- -- -- -- -- -- -- bal. 215 0.94 2.97 0.68 15.16 18.06 5.13 3.10 3.02 1.21 0.10 -- -- -- -- -- -- -- bal. 216 0.98 0.66 0.11 24.98 7.85 6.71 3.19 4.54 0.12 1.01 -- -- -- -- -- -- -- bal. 217 0.99 0.69 1.60 25.04 7.89 6.76 3.24 4.55 0.14 1.02 -- -- -- -- -- -- -- bal. 218 0.97 0.67 2.96 25.01 7.86 6.78 3.21 4.54 0.10 1.04 -- -- -- -- -- -- -- bal. 219 0.85 0.72 0.74 10.32 18.04 5.93 4.57 2.03 1.57 0.05 -- -- -- -- -- -- -- bal. 220 0.87 0.71 0.70 27.01 17.96 5.96 4.66 2.01 1.58 0.01 -- -- -- -- -- -- -- bal. 221 1.03 0.67 0.79 20.16 3.09 8.92 2.02 5.06 0.03 1.49 -- -- -- -- -- -- -- bal. 222 1.04 0.72 0.81 20.23 29.54 8.97 2.05 5.07 0.06 1.51 -- -- -- -- -- -- -- bal. 223 0.98 0.65 0.84 15.44 17.90 0.51 8.70 4.06 0.56 0.52 -- -- -- -- -- -- -- bal. 224 0.96 0.69 0.81 15.50 17.73 9.95 2.17 4.02 0.55 0.51 -- -- -- -- -- -- -- bal. 225 1.01 0.61 0.78 15.49 17.90 8.76 0.52 4.04 0.52 0.55 -- -- -- -- -- -- -- bal. 226 1.05 0.62 0.81 15.56 17.96 2.01 9.94 4.05 0.50 0.51 -- -- -- -- -- -- -- bal. 227 1.31 0.72 0.80 25.93 17.95 5.16 5.02 1.03 0.48 0.54 -- -- -- -- -- -- -- bal. 228 1.27 0.70 0.78 25.97 17.98 5.14 5.00 7.86 0.50 0.51 -- -- -- -- -- -- -- bal. 229 0.89 0.67 0.77 20.08 18.03 6.01 3.09 1.52 0.012 2.52 -- -- -- -- -- -- -- bal. 230 0.90 0.70 0.76 20.06 18.07 6.08 3.14 1.50 1.96 1.06 -- -- -- -- -- -- -- bal. 231 0.92 0.69 0.78 20.07 18.02 6.03 3.06 1.54 3.47 0.05 -- -- -- -- -- -- -- bal. 232 0.90 0.68 0.83 19.98 18.04 5.08 4.07 2.06 3.08 0.011 -- -- -- -- -- -- -- bal. 233 0.92 0.70 0.79 19.99 18.07 5.11 4.03 2.03 0.98 1.99 -- -- -- -- -- -- -- bal. 234 0.90 0.68 0.80 19.86 18.08 5.10 4.10 2.05 0.06 3.48 -- -- -- -- -- -- -- bal. 235 1.20 0.72 0.79 15.04 10.09 5.04 4.97 2.00 0.58 0.10 0.0053 -- -- -- -- -- -- bal. 236 1.19 0.69 0.81 15.06 10.10 5.03 4.98 1.99 0.59 0.09 0.105 -- -- -- -- -- -- bal. 237 1.17 0.70 0.80 15.05 10.06 5.04 4.93 1.98 0.60 0.11 0.196 -- -- -- -- -- -- bal. 238 0.94 0.74 0.79 20.03 18.04 6.07 3.06 2.50 2.00 0.97 -- 1.41 -- -- -- -- -- bal. 239 0.96 0.69 0.81 20.09 18.07 6.10 3.09 2.53 1.97 0.98 -- -- 0.013 -- -- -- -- bal. 240 0.91 0.68 0.77 20.12 18.05 6.08 3.05 2.51 1.99 0.94 -- 0.412 0.405 -- -- -- -- bal. 241 0.93 0.70 0.81 20.01 18.06 5.07 4.08 1.99 0.91 1.98 -- -- -- 0.197 -- -- -- bal. 242 0.96 0.68 0.79 20.14 18.13 5.11 4.16 2.06 1.09 2.06 -- -- -- -- 0.0013 -- -- bal. 243 0.98 0.69 0.81 20.16 18.10 5.07 4.14 2.01 1.04 2.04 -- -- -- 0.050 0.052 -- -- bal. 244 1.09 0.70 0.79 15.10 9.99 5.12 5.03 2.04 0.62 0.22 0.093 -- 0.612 -- -- -- -- bal. 245 1.08 0.74 0.82 15.16 10.01 5.19 4.99 2.01 0.64 0.19 0.069 -- -- -- 0.098 -- -- bal. 246 0.93 0.70 0.79 20.06 18.07 6.03 3.14 2.49 1.98 0.95 -- 0.531 0.412 0.075 -- -- -- bal. 247 0.94 0.62 0.74 20.04 18.01 6.05 3.10 2.52 1.99 0.90 0.082 0.393 0.402 0.061 0.052 -- -- bal. COMPARA- ALLOY 248 0.48* 0.83 0.67 20.11 26.99 4.91 4.97 5.00 1.50 0.05 -- -- -- -- -- -- -- bal. 249 2.09* 0.84 0.69 20.08 26.97 4.96 4.98 5.01 1.54 0.05 -- -- -- -- -- -- -- bal. 250 1.03 --* 0.68 15.20 18.07 5.16 3.05 3.00 1.23 0.13 -- -- -- -- -- -- -- bal. 251 1.02 3.18* 0.70 15.24 18.04 5.19 3.05 3.01 1.20 0.12 -- -- -- -- -- -- -- bal. 252 1.01 0.69 --* 25.02 8.00 6.84 3.20 4.53 0.15 1.04 -- -- -- -- -- -- -- bal. 253 1.02 0.71 3.11* 25.06 8.03 6.82 3.17 4.51 0.12 1.01 -- -- -- -- -- -- -- bal. 254 0.87 0.70 0.73 9.05* 18.05 5.94 4.60 2.01 1.56 0.07 -- -- -- -- -- -- -- bal. 255 0.88 0.71 0.69 30.52* 18.04 5.96 4.67 1.99 1.59 0.06 -- -- -- -- -- -- -- bal. 256 1.05 0.69 0.82 20.18 31.53* 9.03 2.02 5.00 0.05 1.53 -- -- -- -- -- -- -- bal. 257 0.98 0.72 0.77 15.49 18.04 --* 8.96 4.05 0.54 0.50 -- -- -- -- -- -- -- bal. 258 1.01 0.66 0.79 15.54 17.81 11.01* 8.98 4.03 0.57 0.53 -- -- -- -- -- -- -- bal. 259 1.04 0.60 0.83 15.51 18.01 8.88 --* 4.01 0.50 0.54 -- -- -- -- -- -- -- bal. 260 1.03 0.63 0.81 15.54 17.98 2.04 10.51* 4.03 0.54 0.52 -- -- -- -- -- -- -- bal. 261 1.30 0.69 0.82 25.96 17.97 5.13 5.01 --* 0.53 0.52 -- -- -- -- -- -- -- bal. 262 0.94 0.70 0.77 20.04 18.06 6.05 3.15 1.51 --* 2.54 -- -- -- -- -- -- -- bal. 263 0.93 0.72 0.79 20.06 18.02 6.04 3.08 1.54 3.59* 0.07 -- -- -- -- -- -- -- bal. 264 0.96 0.68 0.76 20.04 18.13 5.12 4.09 2.01 3.04 --* -- -- -- -- -- -- -- bal. 265 0.91 0.67 0.77 20.06 18.07 5.16 4.07 2.04 0.07 3.58* -- -- -- -- -- -- -- bal.
TABLE 8__________________________________________________________________________ VICKERS HARDNESS Charpy impact Amount Number cycle at room strength specific till occurrence temp. 900.degree. C. 1000.degree. C. kg -m/cm.sup.2 wear .times. 10.sup.-7 of crack__________________________________________________________________________Prior art alloy208 259 77 64 0.89 3.28 18209 305 143 130 0.43 1.97 3ALLOYOF THISINVENTION210 324 166 154 1.81 1.87 >30211 345 186 162 1.74 1.70 >30212 394 263 197 1.03 0.97 30213 330 157 153 1.73 1.91 >30214 352 173 157 1.70 1.77 >30215 380 179 165 1.20 1.36 30216 350 170 156 1.76 1.72 >30217 349 169 152 1.84 1.51 >30218 329 157 144 1.93 1.44 >30219 337 161 148 2.10 1.50 >30220 366 201 189 1.42 1.12 30221 354 193 167 1.82 1.70 >30222 329 157 146 2.60 1.93 >30223 374 239 182 1.30 1.24 >30224 393 261 211 1.21 0.89 27225 371 237 181 1.29 1.28 >30226 390 257 208 1.26 0.92 27227 336 171 147 1.93 1.86 >30228 355 193 180 2.05 1.32 >30229 338 173 148 1.04 1.64 >30230 353 226 172 2.16 1.47 >30231 374 254 196 1.27 1.00 27232 340 177 152 1.18 1.60 >30233 364 236 179 1.90 1.42 >30234 401 276 219 1.20 0.97 27235 355 224 158 1.50 1.24 >30236 386 257 175 1.40 1.03 30237 439 296 269 1.00 0.82 21238 361 237 180 1.90 1.30 >30239 354 230 171 1.84 1.61 >30240 363 234 179 1.48 1.00 >30241 368 239 184 1.61 0.94 >30242 356 227 155 1.82 1.17 >30243 358 230 157 1.71 1.09 >30244 389 260 168 1.42 0.97 >30245 361 239 163 1.60 1.00 >30246 363 242 182 1.84 1.42 >30247 371 253 189 1.87 0.92 >30COMPARA-TIVE ALLOY248 304 141 127 0.92 3.49 30249 428 281 235 0.54 0.69 12250 305 131 113 0.40 2.59 12251 400 219 189 0.64 1.30 15252 365 242 153 0.73 2.48 12253 310 140 127 2.03 1.15 >30254 301 130 101 2.37 2.54 >30255 374 214 197 0.60 1.30 15256 305 140 121 2.63 2.60 >30257 286 127 109 1.57 1.66 >30258 420 278 231 0.31 0.78 6259 289 138 114 1.52 1.53 >30260 417 274 229 0.32 0.80 6261 310 139 124 2.13 2.07 >30262 325 138 126 0.80 2.08 >30263 419 284 227 0.55 0.82 9264 316 137 119 0.94 2.29 >30265 427 288 236 0.49 0.76 6__________________________________________________________________________
ABILITY OF INDUSTRIAL UTILITY
The alloy of this invention are employed for the guide shoe included the pierced billet used in a hot rolling apparatus for fabricating seamless steel pipe due to improve in the thermal and wear resistance, toughness at elevated temperatures.
The alloy of this invention have the industrial utilizable properties and the extremely long life and the stability. Furthermore, the alloy according to this invention is applied widely to employing for the build-up weld.

Number	Date	Country	Kind
56-138594	Sep 1981	JPX
56-138595	Sep 1981	JPX

Thermal and wear resistant tough nickel based alloy guide rolls

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