TURBINE COMPONENT ASSEMBLY

• US 20180363497A1
• Filed: 06/15/2017
• Published: 12/20/2018
• Est. Priority Date: 06/15/2017
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: TAXACHER, Glenn Curtis, BADDING, Bruce, ROBERTS, III, Herbert Chidsey
• Granted Patent: US 10,711,637 B2
• Time in Patent Office: Days
• CPC Class Codes: C04B 2237/12 Metallic interlayers
• CPC Class Codes: C04B 2237/38 Fiber or whisker reinforced
• CPC Class Codes: C04B 2237/385 Carbon or carbon composite
• CPC Class Codes: C04B 2237/40 Metallic
• CPC Class Codes: C04B 2237/406 Iron, e.g. steel
• CPC Class Codes: C04B 2237/84 Joining of a first substrate with a second substrate at least partially inside the first substrate, where the bonding area is at the inside of the first substrate, e.g. one tube inside another tube
• CPC Class Codes: C04B 37/021 in a direct manner, e.g. direct copper bonding [DCB]
• CPC Class Codes: C04B 37/026 consisting of metals or metal salts
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2220/30 in turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2300/172 Copper alloys
• CPC Class Codes: F05D 2300/173 Aluminium alloys, e.g. AlCuMgPb
• CPC Class Codes: F05D 2300/6012 Woven fabrics
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components

Abstract

A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

Claims

1. A turbine component assembly, comprising:

a first component arranged to be disposed adjacent to a hot gas path, the first component including a ceramic matrix composite (CMC) composition;

a second component adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component; and

an interface shield disposed on a contact region of the first component, the interface shield directly contacting the second component.

2. The turbine component assembly of claim 1, wherein the interface shield includes a higher wear resistance than the first component and the second component alone.

3. The turbine component assembly of claim 1, wherein the interface shield includes a higher damping capability than the first component and the second component alone.

4. The turbine component assembly of claim 1, wherein the interface shield includes a material composition selected from the group consisting of cobalt alloys, CoCrNiWC systems, cobalt L-605, STELLITE 720 ULTRAFLEX, STELLITE 6, STELLITE 6B, STELLITE 6K, STELLITE 21, TRIBALLOY T-400, TRIBALLOY T-400C, TRIBALLOY T-800, X-40, X-45, FSX-414, copper alloys, MONEL alloys, MONEL 400, MONEL 401, MONEL 404, MONEL K-500, MONEL 405, aluminum bronzes, INCONEL 625, INCONEL 718, INCONEL 738, and combinations thereof.

5. The turbine component assembly of claim 1, wherein the CMC composition of the first component is selected from the group consisting of aluminum oxide-fiber-reinforced aluminum oxides (Ox/Ox), carbon-fiber-reinforced silicon carbides (C/SiC), silicon-carbide-fiber-reinforced silicon carbides (SiC/SiC), carbon-fiber-reinforced silicon nitrides (C/Si₃N₄), silicon-carbide-fiber-reinforced silicon nitrides (SiC/Si₃N₄), and combinations thereof.

6. The turbine component assembly of claim 1, wherein the second component includes a material composition selected from the group consisting of iron alloys, steels, stainless steels, carbon steels, nickel alloys, superalloys, nickel-based superalloys, INCONEL 718, INCONEL 738, INCONEL X-750, René

41, cobalt-based superalloys, cobalt L-605, and combinations thereof.

7. The turbine component assembly of claim 1, wherein the interface shield is co-cast on the first component.

8. The turbine component assembly of claim 1, wherein the interface shield is bonded to the first component.

9. The turbine component assembly of claim 1, wherein the interface shield is removably secured to the first component.

10. The turbine component assembly of claim 1, wherein the turbine component assembly is a shroud assembly, the first component is an inner shroud, and the second component is an outer shroud.

11. The turbine component assembly of claim 10, wherein the contact region is a hook region of the inner shroud.

12. The turbine component assembly of claim 11, wherein the interface shield is an interface clip having a u-shaped cross-section sized to contact the hook region with a first surface, a second surface, and a third surface.

13. The turbine component assembly of claim 1, wherein the turbine component assembly is a nozzle assembly, the first component is a nozzle end wall, and the second component is a nozzle outer wall.

14. The turbine component assembly of claim 1, wherein the turbine component assembly is a combustor, the first component is a combustor liner, the second component is a combustor case.

15. The turbine component assembly of claim 1, wherein the interface shield reduces thermal binding relative to a comparative assembly not including the interface shield.

16. The turbine component assembly of claim 1, wherein the interface shield reduces wear of the first component relative to a comparative assembly not including the interface shield.

17. The turbine component assembly of claim 1, further including a plurality of interface shields disposed on a plurality of contact regions of the first component and directly contacting the second component.

18. The turbine component assembly of claim 1, wherein the interface shield is free of spring coils, elastomers, and woven metal meshes.

19. The turbine component assembly of claim 1, wherein the interface shield includes a hard wear surface coating directly contacting the second component.

20. The turbine component assembly of claim 19, wherein the hard wear surface coating is selected from the group consisting of STELLITE 720 ULTRAFLEX, STELLITE 6, STELLITE 6B, STELLITE 6K, STELLITE 21, TRIBALLOY T-400, TRIBALLOY T-400C, TRIBALLOY T-800, X-40, X-45, FSX-414, copper alloys, MONEL alloys, MONEL 400, MONEL 401, MONEL 404, MONEL K-500, MONEL 405, aluminum bronzes, INCONEL 625, INCONEL 718, INCONEL 738, and combinations thereof.