Ceramic composite vane with metallic substructure

• US 6,514,046 B1
• Filed: 09/29/2000
• Issued: 02/04/2003
• Est. Priority Date: 09/29/2000
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Thompson, Daniel G., Taut, Christine, Carelli, Eric V., Lane, Jay E., Morrison, Jay A., Campbell, Christian X., Merrill, Gary B.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Kershteyn, Igor
• Application Number:
  US09/677,044
• Time in Patent Office: 858 Days
• Field of Search: 416/97.R, 416/96.A, 416/229.A, 416/241.B, 415/209, 415/210, 415/191, 415/115, 415/200
• US Class Current: 416/229.00A
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/611 Coating
• CPC Class Codes: F05D 2300/612 Foam

Abstract

A vane assembly for a turbine assembly includes an inner endcap, an outer endcap, and a body. The body includes a metallic core assembly, a ceramic shell assembly and a support assembly. The metallic core assembly is coupled to the inner and outer endcaps and bears most of the mechanical loads, including aerodynamic loads. The ceramic shell bears substantially all of the thermal stress placed on the vane assembly. The support assembly is disposed between the metallic core assembly and said ceramic shell assembly and is coupled to the metallic core assembly.

Claims

1. A vane assembly for a turbine assembly comprising:

an inner endcap;

an outer endcap;

a body;

said body comprises;

a metallic core assembly which is coupled to said inner endcap and said outer endcap;

a ceramic shell assembly;

a support assembly coupled to said metallic core assembly; and

said support assembly being disposed between said metallic core assembly and said ceramic shell assembly and adapted to transmit substantially all aerodynamic loads from said shell assembly to said core assembly during operation.

2. The vane assembly of claim 1, wherein said support assembly is one or more of the structures selected from the group consisting of:

a compliant layer, hard contact points and a biasing means.

3. The vane assembly of claim 2, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

4. The vane assembly of claim 3, wherein said inner layer is a ceramic matrix composite.

5. The vane assembly of claim 4, wherein:

said metallic core assembly comprises a frame forming at least one main cooling passage.

6. The vane assembly of claim 5, wherein:

said frame includes a plurality of connecting passages that are in fluid communication with both said at least one main passage and said support assembly.

7. The vane assembly of claim 6, wherein:

said support assembly hard contact points includes a plurality of ribs; and

said support assembly includes a plurality of strips of a compliant material disposed between said ribs.

8. The vane assembly of claim 3, wherein said biasing means is a plurality of leaf springs.

9. The vane assembly of claim 8, wherein:

said body has a high pressure side and a low pressure side; and

said plurality of leaf springs is disposed between said metallic core assembly and said ceramic shell assembly adjacent to said low pressure side and a plurality of ribs is disposed between said metallic core assembly and said ceramic shell assembly adjacent to said high pressure side.

10. The vane assembly of claim 3, wherein said outer layer is an insulating ceramic.

11. The vane assembly of claim 10, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

19. The vane assembly of claim 1, wherein said support assembly is a plurality of leaf springs.

20. The vane assembly of claim 19, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

21. The vane assembly of claim 20, wherein said inner layer is a ceramic matrix composite.

22. The vane assembly of claim 21, wherein said outer layer is an insulating ceramic.

23. The vane assembly of claim 22, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

24. The vane assembly of claim 23, wherein:

said metallic core assembly comprises a frame forming at least one main cooling passage.

25. The vane assembly of claim 24, wherein:

said frame assembly includes a plurality of connecting passages that are in fluid communication with both said at least one main cooling passage and said support assembly.

26. The vane assembly of claim 1 wherein said support assembly comprises a plurality of hard contact points and wherein said plurality hard contact points include a plurality of ribs extending from said ceramic shell assembly towards said metallic core assembly.

12. A vane assembly for a turbine assembly comprising:

an inner endcap;

an outer endcap;

a body;

said body comprises;

a metallic core assembly which is coupled to said inner endcap and said outer endcap;

a ceramic shell assembly;

a support assembly coupled to said metallic core assembly; and

said support assembly being a layer of a compliant material, wherein said compliant material includes a plurality of cooling passages therethrough being in fluid communication with said ceramic shell assembly.

13. The vane assembly of claim 12, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

14. The vane assembly of claim 13, wherein said inner layer is a ceramic matrix composite.

15. The vane assembly of claim 14, wherein said outer layer is an insulating ceramic.

16. The vane assembly of claim 15, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

17. The vane assembly of claim 14, wherein said metallic core assembly comprises a frame forming at least one main cooling passage.

18. The vane assembly of claim 17, wherein said frame assembly includes a plurality of connecting passages that are in fluid communication with both said at least one main cooling passage and said support assembly.

27. A turbine comprising:

a casing;

a cooling system; and

a plurality of vane assemblies comprising;

an inner endcap;

an outer endcap;

a body;

said body comprises;

a metallic core assembly which is coupled to said inner endcap and said outer endcap;

a ceramic shell assembly;

a support assembly coupled to said metallic core assembly; and

said support assembly being disposed between said metallic core assembly and said ceramic shell assembly and adapted to transmit substantially all aerodynamic loads from said shell assembly to said core assembly during operation.

28. The turbine of claim 27, wherein said support assembly is one or more of the structures selected from the group consisting of:

a compliant layer, hard contact points and a biasing means.

29. The turbine of claim 28, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

30. The turbine of claim 29, wherein said inner layer is a ceramic matrix composite.

31. The turbine of claim 29, wherein said outer layer is an insulating ceramic.

32. The turbine of claim 31, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

33. The turbine of claim 31, wherein:

said metallic core assembly comprises a frame forming at least one main cooling passage.

34. The turbine of claim 33, wherein:

said frame includes a plurality of connecting passages that are in fluid communication with both said at least one main passage and said support assembly.

35. The turbine of claim 34, wherein:

said support assembly hard contact points includes a plurality of ribs; and

said support assembly includes a plurality of strips of a compliant material disposed between said ribs.

36. The turbine of claim 29, wherein said biasing means is a plurality of leaf springs.

37. The turbine of claim 36, wherein:

said body has a high pressure side and a low pressure side; and

said plurality of leaf springs is disposed between said metallic core assembly and said ceramic shell assembly adjacent to said low pressure side and a plurality of ribs is disposed between said metallic core assembly and said ceramic shell assembly adjacent to said high pressure side.

38. The turbine of claim 28, wherein said support assembly is a layer of a compliant material.

46. The turbine of claim 27, wherein said support assembly is a plurality of leaf springs.

47. The turbine of claim 46, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

48. The turbine of claim 47, wherein said inner layer is a ceramic matrix composite.

49. The turbine of claim 48, wherein said outer layer is an insulating ceramic.

50. The turbine of claim 49, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

51. The turbine of claim 50, wherein:

said metallic core assembly comprises a frame forming at least one main cooling passage.

52. The turbine of claim 51, wherein:

said frame assembly includes a plurality of connecting passages that are in fluid communication with both said at least one main cooling passage and said support assembly.

39. A turbine comprising:

a casing;

a cooling system; and

a plurality of vane assemblies comprising;

an inner endcap;

an outer endcap;

a body;

said body comprises;

a metallic core assembly which is coupled to said inner endcap and said outer endcap;

a ceramic shell assembly;

a support assembly coupled to said metallic core assembly; and

said support assembly disposed between said metallic core assembly and said ceramic shell assembly, wherein said support assembly is a layer of a compliant material, wherein said compliant material includes a plurality of cooling passages therethrough being in fluid communication with said ceramic shell assembly.

40. The turbine of claim 39, wherein said ceramic shell assembly comprises an inner layer of ceramic material and an outer layer of ceramic material.

41. The turbine of claim 40, wherein said inner layer is a ceramic matrix composite.

42. The turbine of claim 41, wherein said outer layer is an insulating ceramic.

43. The turbine of claim 42, wherein said outer layer is ceramic insulation comprising hollow ceramic spheres.

44. The turbine of claim 41, wherein said metallic core assembly comprises a frame forming at least one main cooling passage.

45. The turbine of claim 44, wherein said frame assembly includes a plurality of connecting passages that are in fluid communication with both said at least one main cooling passage and said support assembly.

53. A turbine assembly comprising:

a casing;

a cooling system; and

a plurality of vane assemblies comprising;

an inner endcap;

an outer endcap;

a body;

said body comprises;

a metallic core assembly which is coupled to said inner endcap and said outer endcap;

a ceramic shell assembly;

a support assembly coupled to said ceramic shell assembly;

said support assembly being disposed between said metallic core assembly and said ceramic shell assembly and adapted to transmit substantially all aerodynamic loads from said shell assembly to said core assembly during operation; and

said support assembly comprises a plurality of hard contact points.

54. The turbine assembly of claim 53 wherein said plurality hard contact points include a plurality of ribs extending from said ceramic shell assembly towards said metallic core assembly.