Metal treatment – Stock – Vanadium – niobum – or tantalum base
Reexamination Certificate
2000-08-24
2002-06-25
Yee, Deborah (Department: 1742)
Metal treatment
Stock
Vanadium, niobum, or tantalum base
C420S425000, C420S426000
Reexamination Certificate
active
06409848
ABSTRACT:
BACKGROUND OF THE INVENTION
The invention relates to multiphase Nb-silicide in-situ composites having improved creep performance. In particular, the invention relates to multiphase Nb-silicide based composites having a certain ratio of niobium (Nb), hafnium (Hf), and titanium (Ti).
Traditionally, turbine components have been often formed from nickel-(Ni) based superalloys materials. These Ni-based superalloys have been used for turbines and turbine components, such as but not limited to, jet engine turbines, land-based turbines, marine-based turbines, and other high temperature turbine environments. The applications of these Ni-based superalloy turbine components may be limited by the high temperatures associated with turbine component operations. Surface temperatures during operation of turbine components can approach temperatures up to and above 1150° C., which are approximately 85% of the melting temperatures of the Ni-based superalloy. Therefore, these temperatures can limit the applications of Ni-based superalloys as the high temperatures may adversely influence the Ni-based superalloy's strength, oxidation resistance, and creep resistance. Further, other intrinsic Ni-based superalloy properties at these high temperatures, such as but not limited to, fracture toughness, high-temperature strength, oxidation resistance, and other mechanical properties, may prevent further applications.
In order to overcome the above-noted deficiencies of the Ni-based superalloys, niobium-(Nb) and molybdenum-(Mo) modified Nb-silicide based composite materials have been investigated for turbine component applications. Niobium has been used to form refractory metal intermetallic composites (hereinafter referred to as “RMIC”s), which include, but are not limited to, Nb-based refractory metal intermetallic composites. RMICs, such as but not limited to Nb-silicide based composites, possess potentially high operating temperatures, for example, but not limited to, those temperatures encountered in turbine component applications. These RMICs have higher melting temperatures that Ni-based superalloys, and thus may find beneficial applications in turbine components. For example, some RMICs may have melting temperatures in excess of 1700° C., which would be desirable in a turbine component application. See M. R. Jackson et al., “High-Temperature Refractory Metal-Intermetallic Composites”, Journal of Materials, January 1996 (pp. 39-44).
RMIC mechanical properties, such as, fracture toughness, high-temperature strength, and oxidation resistance are also enhanced compared to Ni-based superalloys. However, Nb-based refractory metal intermetallic composites may possess poor creep resistance at elevated temperatures, which would be undesirable in turbine components. This creep performance may be due to the existence of an additional hP16 hexagonal phase, which is present in Nb-based composites.
Thus, there is a need for improved high temperature alloys for turbine component applications. Therefore, another need exists to provide a Nb-based material for high temperature applications, in which the Nb-based material can find use in high temperature applications with enhanced creep resistance.
BRIEF SUMMARY OF THE INVENTION
One aspect of the present invention provides a multiphase niobium-based silicide composite that exhibits creep resistance at temperatures equal to or greater than 1150° C. The niobium-based silicide composite comprises at least silicon (Si) hafnium (Hf), titanium (Ti), and niobium (Nb). The concentration ratio of Nb:(Hf+Ti) is equal to or greater than about 1.4 and the niobium-based silicide composite comprises at least silicon (Si), hafnium (Hf), titanium (Ti), and niobium (Nb), wherein a concentration ratio of Nb:(Hf+Ti) is equal to or greater than about 1.4 and the niobium-based silicide composite exhibits a creep rate less than about 5×10
−8
s
−1
at temperatures up to about 1200° C. and at a stress of about 200 MPa.
Another aspect of the invention provides a multiphase niobium-based silicide composite that exhibits high temperature creep resistance at temperatures up to about 1200° C. The niobium-based silicide composite comprises, in atomic percent, up to about 25% titanium (Ti), silicon (Si) in a range from about 10% to about 22%, at least about 4% hafnium (Hf), and a balance niobium (Nb).
A further aspect of the invention provides a method for forming a multiphase niobium-based silicide composite. The composite exhibits creep resistance at elevated temperatures. The method of forming the composite comprises providing silicon (Si), hafnium (Hf), titanium (Ti) and niobium (Nb), and optionally tantalum (Ta), germanium (Ge), iron (Fe), boron (B), molybdenum (Mo), aluminum (Al), chromium (Cr), and tungsten (W). A ratio of Nb:(Hf+Ti) is equal to or greater than about 1.4.
Another aspect of the invention provides a turbine component comprising, in atomic percent, 7.5% hafnium (Hf), 16% silicon (Si), 21% titanium (Ti), and a balance niobium (Nb).
Still another aspect of the invention provides a turbine component comprising, in atomic percent, 8% hafnium (Hf), 16% silicon (Si), 21% titanium (Ti), and a balance niobium (Nb).
In a further aspect of the invention provides a turbine component comprising, in atomic percent, 3% molybdenum (Mo), 8% hafnium (Hf), 16% silicon (Si), 25% titanium (Ti), and a balance niobium (Nb).
An additional aspect of the invention provides a turbine component, in atomic percent, 9% molybdenum (Mo), 8% hafnium (Hf), 16% silicon (Si), 25% titanium (Ti), and a balance niobium (Nb).
REFERENCES:
patent: 5393487 (1995-02-01), Matway et al.
patent: 5741376 (1998-04-01), Subramanian et al.
patent: 5833773 (1998-11-01), Bewlay et al.
patent: 5932033 (1999-08-01), Jackson et al.
patent: 5942055 (1999-08-01), Jackson et al.
M. R. Jackson, et al, High-Temperature Refractory Metal-Intermetallic Composites,Journal of Metals, Jan., 1996.
B. P. Bewlay, et al., Refractory Metal-Intermetallic In-Situ Composites for Aircraft Engines, Reprinted fromJOM, vol. 49, No. 8, Aug., 1997, pp. 44-45; p. 67.
B. P. Bewlay, et al., Evidence for the Existence of Hf5Si3,Journal of Phase Equilibria, vol. 20, No. 2, 1999.
B. P. Bewlay, et al., Processing High-Temperature Refractory-Metal Silicide In-Situ Composites, Reprinted fromJOM, vol. 51, No. 4, Apr., 1999, pp. 32-36.
P. R. Subramanian, et al., Compressive Creep Bahavior of Nb5Si3,Scripta Metallurgica et Materialia, vol. 32, No. 8, pp. 1227-1232, 1995.
B. P. Bewlay, et al., The Nb-Ti-Si Ternary Phase Diagram: Evaluation of Liquid-Solid Phase Equilibria in Nb-and Ti-Rich Alloys,Journal of Phase Equilibria, vol. 18, No. 3, 1997.
B. P. Bewlay, et al, The Nb-Hf-Si Ternary phase Diagram: Liquid-Solid Phase Equilibria in Nb-0 and Hf-rich Alloys,z. Metallkd, 90, 1999.
B. P. Bewlay, et al., The Nb-Ti-Si Ternary Phase Diagram: Determination of Solid-State Phase Equilibria in Nb-and Ti-Rich Alloys,Journal of Phase Equilibria, vol. 19, No. 6, 1998.
Bewlay Bernard Patrick
Jackson Melvin Robert
Diconza Paul J.
General Electric Company
Ingraham Donald S.
Yee Deborah
LandOfFree
Creep resistant Nb-silicide based multiphase composites does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Creep resistant Nb-silicide based multiphase composites, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Creep resistant Nb-silicide based multiphase composites will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2917939