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US-12624426-B2 - High entropy alloy

US12624426B2US 12624426 B2US12624426 B2US 12624426B2US-12624426-B2

Abstract

An alloy comprising by weight percent: 16.0-26.0 Cr; 23.0-34.0 Mo; 21.0-31.0 Ta; 0.50-3.5 Ti; and 17.0-27.0 V.

Inventors

  • Kenneth D. Smith
  • John A. Sharon
  • Ryan M. Deacon
  • Soumalya Sarkar

Assignees

  • RAYTHEON TECHNOLOGIES CORPORATION

Dates

Publication Date
20260512
Application Date
20230605

Claims (20)

  1. 1 . An alloy comprising by weight percent: 19.25-23.25 Cr; 27.10-31.10 Mo; 24.25-28.25 Ta; 0.5-2.25 Ti; 15-24.15 V; and no more than 5.0 Zr, if any.
  2. 2 . The alloy of claim 1 comprising by weight percent: no more than 4.5 Zr, if any; and 0.5-5.0 said Ti and Zr combined.
  3. 3 . The alloy of claim 2 further comprising: no more than 4.0 Nb, if any; no more than 4.0 W, if any; no more than 4.0 Al, if any; no more than 3.0 all other elements individually, if any; and no more than 6.0 all other elements, if any, combined.
  4. 4 . The alloy of claim 1 comprising by weight percent: 20.25-22.25 Cr; 28.10-30.10 Mo; 25.25-27.25 Ta; 0.75-1.75 Ti; and 21.15-23.15 V.
  5. 5 . The alloy of claim 1 comprising in weight percent: 20.25-22.25 Cr; 28.10-30.10 Mo: 25.25-27.25 Ta; 0.75-1.75 Ti; and 21.15-23.15 V.
  6. 6 . The alloy of claim 5 further comprising: no more than 1.0 all other elements individually, if any; and no more than 3.0 all other elements, if any, combined.
  7. 7 . The alloy of claim 1 wherein by weight percent: (Mo+Ta) is 45.0-80.0; and (Cr/V) is 0.25-1.6.
  8. 8 . The alloy of claim 1 further comprising: no more than 4.0 Nb, if any; no more than 4.0 W, if any; no more than 4.0 Al, if any; no more than 3.0 all other elements individually, if any; and no more than 6.0 all other elements, if any, combined.
  9. 9 . The alloy of claim 1 further comprising: no more than 1.0 all other elements individually, if any; and no more than 3.0 all other elements, if any, combined.
  10. 10 . The alloy of claim 1 consisting essentially of: said Cr; said Mo; said Ta; said V; said Ti, if any; said Zr, if any; up to 2.0 weight percent each Y and Si, if any; and up to 0.50 weight percent each B, C, O, and N, if any.
  11. 11 . The alloy of claim 1 having at least one of: a density of 8.80 to 9.10 grams per cubic centimeter; a 1300° C. yield point of at least 500 MPa; and a melting point of at least 1600° C.
  12. 12 . The alloy of claim 1 having a BCC structure.
  13. 13 . The alloy of claim 1 as a coated substrate having a coating comprising one or more: silicide-based coatings; zirconia-yttria based coatings; rare-earth oxide coatings; and mixtures thereof.
  14. 14 . A gas turbine engine component comprising: a substrate comprising: 4.8-26.0 Cr; 21.75-41.0 Mo; 21.0-50.0 Ta; 6.0-27.0 V; no more than 18.0 Ti, if any; and no more than 5.0 Zr, if any; and a coating.
  15. 15 . The gas turbine engine component of claim 14 wherein: the component is a hot section component.
  16. 16 . The gas turbine engine component of claim 15 wherein the component is selected from the group consisting of: blades, vanes, blade outer air seals; combustor shell pieces, combustor heat shield pieces, combustor fuel nozzles, and combustor fuel nozzle guides.
  17. 17 . A coated substrate having: a substrate comprising: 4.8-26.0 Cr; 21.75-41.0 Mo; 21.0-50.0 Ta; 6.0-27.0 V; no more than 18.0 Ti, if any; and no more than 5.0 Zr, if any; and a coating comprising one or more: silicide-based coatings; zirconia-yttria based coatings; rare-earth oxide coatings; and mixtures thereof.
  18. 18 . The coated substrate of claim 17 wherein: the coated substrate is a hot section component.
  19. 19 . The coated substrate of claim 18 wherein the component is selected from the group consisting of: blades, vanes, blade outer air seals; combustor shell pieces, combustor heat shield pieces, combustor fuel nozzles, and combustor fuel nozzle guides.
  20. 20 . An alloy comprising by weight percent: 4.8-26.0 Cr; 21.75-41.0 Mo; 21.0-50.0 Ta; 6.0-27.0 V; no more than 18.0 Ti, if any; and no more than 5.0 Zr, if any, the alloy having at least one of: a density of 8.80 to 9.10 grams per cubic centimeter; a 1300° C. yield point of at least 500 MPa; and a melting point of at least 1600° C.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS Benefit is claimed of U.S. Patent Application No. 63/348,976, filed Jun. 3, 2022, and entitled “High Entropy Alloy” and U.S. Patent Application No. 63/348,981, filed Jun. 3, 2022, and entitled “High Entropy Alloy”, the disclosures of which are incorporated by reference herein in their entireties as if set forth at length. BACKGROUND The disclosure relates to gas turbine engines. More particularly, the disclosure relates to high entropy alloys. Gas turbine engines (used in propulsion and power applications and broadly inclusive of turbojets, turboprops, turbofans, turbo shafts, industrial gas turbines, and the like) are subject to ever increasing thermal requirements in their hot sections (combustors, turbine sections, exhaust nozzles, and the like). Sequential generations of typically nickel-based superalloys have been developed in various compositions for rotating components (e.g., blades and disks either separate or integral) and static components (e.g., combustor panels, blade outer air seals, vanes, and the like). Additionally, to address the increasing thermal demands, various ceramics and ceramic matrix composite compositions have been proposed. United States Patent Application Publication 20200261980 A1, Mironet, et al., published Aug. 20, 2020, and entitled “METHOD FOR IDENTIFYING AND FORMING VIABLE HIGH ENTROPY ALLOYS VIA ADDITIVE MANUFACTURING”, discloses HEA processing methods. United States Patent Application Publication 20220112608 A1, Tang, et al., published Apr. 14, 2022, and entitled “ENVIRONMENTAL BARRIER COATING”, (the '608 publication), the disclosure of which is incorporated by reference herein in its entirety as if set forth at length, discloses a coating system for HEA. The example coating system has an underlying diffusion barrier atop the substrate, a bondcoat atop the diffusion barrier, and a ceramic top coat. SUMMARY One aspect of the disclosure involves an alloy comprising by weight percent: 16.0-26.0 Cr; 23.0-34.0 Mo; 21.0-31.0 Ta; 0.50-3.5 Ti; and 17.0-27.0 V. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in weight percent: 19.25-23.25 Cr; 27.10-31.10 Mo; 24.25-28.25 Ta; 0.5-2.25 Ti; and 20.15-24.15 V. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in weight percent: 20.25-22.25 Cr; 28.10-30.10 Mo; 25.25-27.25 Ta; 0.75-1.75 Ti; and 21.15-23.15 V. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in weight percent: no more than 4.0 Nb, if any; no more than 4.0 Zr, if any; no more than 4.0 W, if any; no more than 4.0 Al, if any; and no more than 6.0 all other elements, if any, combined. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in weight percent: no more than 3.0 all other elements individually, if any; and no more than 6.0 all other elements, if any, combined. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in weight percent: no more than 1.0 all other elements individually, if any; and no more than 3.0 all other elements, if any, combined. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy consists essentially of: said Cr; said Mo; said Ta; said V; said Ti; up to 2.0 weight percent each Y and Si, if any; and up to 0.50 weight percent each B, C, O, and N, if any. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy comprises in atomic percent: 31 Cr; 23 Mo; 11 Ta; 2 Ti; and 33 V. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy has at least one of: a density of 8.80 to 9.10 grams per cubic centimeter; a 1300° C. yield point of at least 500 MPa; and a melting point of at least 1600° C. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy has a BCC structure. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the alloy is a coated substrate having a coating comprising one or more: silicide-based coatings; zirconia-yttria based coatings; rare-earth oxide coatings; and mixtures thereof. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, a gas turbine engine component includes the alloy and further comprising: a coating. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the gas turbine engine component is a hot section component. In a further embodiment of any of the foregoing embodiments, additionally and/or alternatively, the gas turbine engine component is selected from the group consisting of: blades, vanes, blade outer air seals; combustor shell pieces,