The present invention relates generally to alloy compositions, and specifically to niobium alloy compositions operable to withstand oxidation.
Advanced designs in turbine airfoils, in addition to numerous other industrial applications, have previously utilized alloys, such as nickel base superalloys, to provide superior mechanical properties. However, these nickel alloys have shown to be ineffective at surface temperatures above surface temperatures above 1000° C., for example, these Ni-base alloys soften above 1150° C. and melt at about 1350° C. As a result, designers in the turbine industry, and other industries have been trying to develop new high temperature alloys, including niobium alloys. As new industrial applications are developed utilizing niobium alloys, the need arises for improvements in alloy composition and properties, especially resistance to oxidation at high temperatures.
According to one embodiment of the present invention, a niobium alloy composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about 1 atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, and niobium is provided.
According to another embodiment of the present invention, a niobium alloy composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about I atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, between about 0 atomic % and about 2 atomic % of boron, between about 0 atomic % and about 2 atomic % of tin, and niobium is provided.
According to yet another embodiment of the present invention, a turbine system is provided. The turbine system comprises a turbine casing, and a plurality of rotor blades disposed inside the turbine casing, wherein the turbine casing, the rotor blades, and/or other components comprise a composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about 1 atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, and niobium.
According to the present invention, the niobium alloy compositions, and systems utilizing the niobium alloy composition is advantageous, especially in the ability to withstand oxidation and cracking caused by oxidation. These and additional objects and advantages provided by the niobium alloy compositions of the present invention will be more fully understood in view of the following detailed description.
The following detailed description of specific embodiments of the present invention can be best understood when read in conjunction with the drawings enclosed herewith. The drawing sheets include:
a is a micrograph of a non-Mo containing Nb alloy after heat treatment at 1500° C., according to one or more embodiments of the present invention.
b is a micrograph of a Mo containing Nb alloy after heat treatment at 1500° C., according to one or more embodiments of the present invention.
c is a micrograph of another Mo containing Nb alloy after heat treatment at 1500° C., according to one or more embodiments of the present invention.
d is a micrograph of yet another Mo containing Nb alloy after heat treatment at 1500° C., according to one or more embodiments of the present invention.
a is a micrograph of a non-Mo containing Nb alloy oxidized for 24 hours at 800° C., according to one or more embodiments of the present invention.
b is a micrograph of a Mo containing Nb alloy oxidized for 24 hours at 800° C., according to one or more embodiments of the present invention.
a is a micrograph of a non-Mo containing Nb alloy oxidized for 24 hours at 1200° C., according to one or more embodiments of the present invention.
b is a micrograph of a Mo containing Nb alloy oxidized for 24 hours at 1200° C., according to one or more embodiments of the present invention.
The present application is directed to niobium alloy compositions generally, and specifically to high temperature niobium alloy compositions operable to withstand oxidation. According to one embodiment, a niobium alloy composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about 1 atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, and niobium.
Table 1 below lists numerous experimental alloys in accordance with the present invention.
In accordance with further embodiments of the present invention, the niobium alloy composition may comprise a niobium containing body centered cubic (bcc) solid solution phase, and may also comprise a silicide phase characterized by a substantially uniform distribution of fine Nb5Si3 particles and a tetragonal crystal structure. The silicide phase also comprises Ti, Hf, Mo and any other alloying elements present in the alloy. A hexagonal structure may negatively impact the creep resistance of the alloys, thus a tetragonal crystal structure is preferred. The silicide phase comprises a tetragonal crystal structure defined by a base dimension a and height dimension c. Referring generally to
In another embodiment, the niobium alloy composition defines a substantially eutectic mixture. The eutectic mixture is operable to produce fine, uniform silicide particles. The silicide phase may be distributed as particles in the bcc solid solution phase. Moreover, the eutectic mixture may also reduce the amount of thermo-mechanical processing of the alloy. Because the eutectic mixture, by definition, has the lowest possible melting point of any Nb alloy composition with these elements, the casting of the alloys may be easier due to narrower freezing ranges in alloys close to the eutectic compositions. Consequently, casting defects may be minimized.
In further embodiments, the niobium alloy composition may be operable to substantially reduce oxidation at temperatures ranging from between about 600° C. to about 1500° C. Oxidation poses problems for alloys at high temperatures. During high temperature exposure in an oxidizing environment, oxygen diffuses, dissolves and precipitates in the bcc solid solution phase. In addition, it has been found that during oxidation at temperatures below about 1200° C., precipitation of the oxide leads to cracking of the silicide phase. The niobium alloy composition of the present invention is operable to combat oxidation, due to its alloy composition, specifically through the addition of Mo to the alloy. For example, the addition of Mo may increase the thermodynamic activity of oxygen in the alloy and may also decrease the solubility of oxygen in the alloy. In addition, Mo additions to Nb may decrease the diffusivity of oxygen in Nb solid solution, and consequently decrease the oxide thickness in the alloy. In one embodiment as shown generally in
In a further embodiment, the presence of fine Nb5Si3 particles in the silicide phase 25, as shown in
For oxidation at 800° C. as shown in
In further embodiments of the present invention, the body centered cubic solid solution comprises a lattice constant value that is less than a lattice constant for a body centered cubic solid solution phase in a non-Mo containing alloy. Furthermore, the tetragonal crystal structure comprises lower a dimension values and higher c dimension values as compared to a and c dimension values for a silicide phase in a non-Mo containing alloy. Table 3 below provides a comparison of the a and c values (in (Å) angstroms) for E29 (non-Mo containing alloy) and E30 (Mo containing alloy).
According to another embodiment of the present invention, a niobium alloy composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about 1 atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, between about 0 atomic % and about 2 atomic % of boron, between about 0 atomic % and about 2 atomic % of tin, and niobium.
According to yet another embodiment of the present invention, a turbine system is provided. The turbine system comprises a turbine casing, and a plurality of rotor blades disposed inside the turbine casing, wherein the turbine casing, the rotor blades, and/or other components comprise a composition comprising between about 10 atomic % and about 30 atomic % of titanium, between about 7 atomic % and about 20 atomic % of silicon, between about 5 atomic % and about 20 atomic % of molybdenum, between about 2 atomic % and about 10 atomic % of chromium, between about 2 atomic % and about 10 atomic % of aluminum, between about 3 atomic % and about 7 atomic % of zirconium, between about 1 atomic % and about 7 atomic % of carbon, between about 1 atomic % and about 6 atomic % of hafnium, and niobium.
In further embodiments, the composition of the turbine system may be defined by a plurality of phases including a niobium containing body centered cubic solid solution phase, and a silicide phase characterized by a substantially uniform distribution of fine Nb5Si3 particles and a tetragonal crystal structure. The composition is operable to substantially reduce cracking due to oxidation at temperatures ranging from between about 600° C. to about 1500° C.
The niobium alloy may be produced by any method known to one of ordinary skill in the art. In one embodiment, the alloys were prepared by argon inert gas arc melting of the component elements.
These niobium alloy compositions may be used in a wide variety of high temperature structural applications, including aircraft engines, rocket propulsion and hypersonic vehicles by providing higher operational efficiency of turbine engines. Other commercial applications include the use of niobium alloys in land-based gas turbine engines, heat exchangers and energy conversion systems.
It is noted that terms like “specifically,” “preferably,” “commonly,” and “typically” are not utilized herein to limit the scope of the claimed invention or to imply that certain features are critical, essential, or even important to the structure or ftunction of the claimed invention. Rather, these terms are merely intended to highlight alternative or additional features that may or may not be utilized in a particular embodiment of the present invention. It is also noted that terms like “substantially” and “about” are utilized herein to represent the inherent degree of uncertainty that may be attributed to any quantitative comparison, value, measurement, or other representation.
Having described the invention in detail and by reference to specific embodiments thereof, it will be apparent that modifications and variations are possible without departing from the scope of the invention defined in the appended claims. More specifically, although some aspects of the present invention are identified herein as preferred or particularly advantageous, it is contemplated that the present invention is not necessarily limited to these preferred aspects of the invention.