Abstract: An alloy comprising rhodium, aluminum, and chromium, wherein a microstructure of the alloy comprises a face-centered-cubic phase and a B2-structured phase and is essentially free of an L12-structured phase at temperatures greater than about 1000° C., and a gas turbine engine component comprising the alloy.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises one of germanium and silicon, and one of chromium, titanium, gold, aluminum, palladium, platinum, and nickel. This abstract is submitted in compliance with 37 C.F.R. 1.72(b) with the understanding that it will not be used to interpret or limit the scope of or meaning of the claims.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined at a bonded region to the first piece by a diffusion bond. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite. The second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The diffusion bond is formed from a first metallic element disposed on a first surface of the first piece and a second metallic element disposed on at least one of the first surface and a second surface of the second piece, the second surface contacting the first surface, wherein the first and second metal form a composition having a melting temperature less than about 1400° C. This abstract is submitted in compliance with 37 C.F.R. 1.

Abstract: An alloy comprising rhodium, aluminum, and chromium, wherein a microstructure of the alloy comprises a face-centered-cubic phase and a B2-structured phase and is essentially free of an L12-structured phase at temperatures greater than about 1000° C., and a gas turbine engine component comprising the alloy.

Abstract: An alloy and repair material comprising the alloy, articles comprising the alloy and repair material, and methods for repairing articles including provision of the alloy as repair material are described, with the alloy comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of the alloy is essentially free of an L12-structured phase at temperatures greater than about 1000° C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.

Abstract: A niobium-silicide refractory metal intermetallic composite adapted for use in a turbine component. The niobium-silicide refractory metal intermetallic composite comprises: between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; between about 16 atomic percent and about 22 atomic percent silicon; between about 7 atomic percent and about 14 atomic percent chromium; from about 1.5 atomic percent to about 3 atomic percent tin; and a balance of niobium. The niobium silicide refractory intermetallic composite contains a tetragonal phase, which comprises a volume fraction from 0.35 to 0.5 of the niobium silicide refractory intermetallic composite, and a hexagonal M3Si5 silicide phase (wherein M is at least one of Nb and Hf) which comprises a volume fraction comprises less than 0.25 of the niobium silicide refractory intermetallic composite.

Abstract: An environmentally resistant coating comprising silicon, titanium, chromium, and a balance of niobium and molybdenum for turbine components formed from molybdenum silicide-based composites. The turbine component may further include a thermal barrier coating disposed upon an outer surface of the environmentally resistant coating comprising zirconia, stabilized zirconia, zircon, mullite, and combinations thereof. The molybdenum silicide-based composite turbine component coated with the environmentally resistant coating and thermal barrier coating is resistant to oxidation at temperatures in the range from about 2000° F. to about 2600° F. and to pesting at temperatures in the range from about 1000° F. to about 1800° F.

Abstract: An environmentally resistant coating for improving the oxidation resistance of a niobium-based refractory metal intermetallic composite (Nb-based RMIC) at high temperatures, the environmentally resistant coating comprising silicon, titanium, chromium, and niobium. The invention includes a turbine system having turbine components comprising at least one Nb-based RMIC, the environmentally resistant coating disposed on a surface of the Nb-based RMIC, and a thermal barrier coating disposed on an outer surface of the environmentally resistant coating. Methods of making a turbine component having the environmentally resistant coating and coating a Nb-based RMIC substrate with the environmentally resistant coating are also disclosed.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece is a semi-solid braze that comprises a first component and a second component.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises one of germanium and silicon, and one of chromium, titanium, gold, aluminum, palladium, platinum, and nickel. This abstract is submitted in compliance with 37 C.F.R. 1.72(b) with the understanding that it will not be used to interpret or limit the scope of or meaning of the claims.

Abstract: A barrier coating is disclosed, containing about 15 atom % to about 95 atom % chromium; and about 5 atom % to about 60 atom % of at least one of rhenium, tungsten, and ruthenium. Nickel, cobalt, iron, and aluminum may also be present. The barrier coating can be disposed between a metal substrate (e.g., a superalloy) and an oxidation-resistant coating, preventing the substantial diffusion of various elements at elevated service temperatures. A ceramic overcoat (e.g., based on zirconia) can be applied over the oxidation-resistant coating. Related methods for applying protective coatings to metal substrates are also described.

Abstract: An environmentally resistant coating comprising silicon, titanium, chromium, and a balance of niobium and molybdenum for turbine components formed from molybdenum silicide-based composites. The turbine component may further include a thermal barrier coating disposed upon an outer surface of the environmentally resistant coating comprising zirconia, stabilized zirconia, zircon, mullite, and combinations thereof. The molybdenum silicide-based composite turbine component coated with the environmentally resistant coating and thermal barrier coating is resistant to oxidation at temperatures in the range from about 2000° F. to about 2600° F. and to pesting at temperatures in the range from about 1000° F. to about 1800° F.

Abstract: An environmentally resistant coating for improving the oxidation resistance of a niobium-based refractory metal intermetallic composite (Nb-based RMIC) at high temperatures, the environmentallly resistant coating comprising silicon, titanium, chromium, and niobium. The invention includes a turbine system having turbine components comprising at least one Nb-based RMIC, the environmentally resistant coating disposed on a surface of the Nb-based RMIC, and a thermal barrier coating disposed on an outer surface of the environmentally resistant coating. Methods of making a turbine component having the environmentally resistant coating and coating a Nb-based RMIC substrate with the environmentally resistant coating are also disclosed.

Abstract: An article, such as an airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises a first metallic element and a second metallic element, wherein the first metallic element is one of titanium, palladium, zirconium, niobium, and hafnium, and wherein the second metallic element is one of titanium, palladium, zirconium, niobium, hafnium, aluminum, chromium, vanadium, platinum, gold, iron, nickel, and cobalt, the first metallic element being different from the second metallic element.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined at a bonded region to the first piece by a diffusion bond. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite. The second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The diffusion bond is formed from a first metallic element disposed on a first surface of the first piece and a second metallic element disposed on at least one of the first surface and a second surface of the second piece, the second surface contacting the first surface, wherein the first and second metal form a composition having a melting temperature less than about 1400° C. This abstract is submitted in compliance with 37 C.F.R. 1.

Abstract: An oxidation-resistant coating is described, formed of an alloy containing: about 40 to about 50 atom % aluminum and about 0.5 atom % to about 3 atom % tantalum; with a balance of nickel; cobalt, iron, or combinations thereof. The coating may also include chromium and a precious metal, as well as other components, such as zirconium or molybdenum. A method for applying the oxidation-resistant coating to a substrate is also described. The substrate can be formed of superalloy material, e.g., a turbine engine component. Related articles are also disclosed.

Abstract: An environmentally resistant coating comprising silicon, titanium, chromium, and a balance of niobium and molybdenum for turbine components formed from molybdenum silicide-based composites. The turbine component may further include a thermal barrier coating disposed upon an outer surface of the environmentally resistant coating comprising zirconia, stabilized zirconia, zircon, mullite, and combinations thereof. The molybdenum silicide-based composite turbine component coated with the environmentally resistant coating and thermal barrier coating is resistant to oxidation at temperatures in the range from about 2000° F. to about 2600° F. and to pesting at temperatures in the range from about 1000° F. to about 1800° F.

Abstract: A niobium-silicide refractory metal intermetallic composite having enhanced material characteristics, such as oxidation resistance, creep resistance, and toughness, and turbine components made therefrom.

Abstract: A niobium-silicide refractory metal intermetallic composite adapted for use in a turbine component. The niobium-silicide refractory metal intermetallic composite comprises: between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; up to about 7 atomic percent tantalum; between about 16 atomic percent and about 22 atomic percent silicon; up to about 6 atomic percent germanium; up to about 5 atomic percent boron; between about 7 atomic percent and about 14 atomic percent chromium; up to about 4 atomic percent iron; up to about 4 atomic percent aluminum; up to about 3 atomic percent tin; up to about 3 atomic percent tungsten; up to about 3 atomic percent molybdenum; and a balance of niobium.

Abstract: A refractory metal intermetallic composition comprising titanium (Ti), hafnium (Hf), silicon (Si), aluminum (Al), chromium (Cr), germanium (Ge), tin (Sn), iron (Fe), and a balance of niobium (Nb) for use in composite structures having applications in turbine components.