Use of high temperature insulation for ceramic matrix composites in gas turbines

• US 6,197,424 B1
• Filed: 03/27/1998
• Issued: 03/06/2001
• Est. Priority Date: 03/27/1998
• Status: Expired due to Term

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Merrill, Gary Brian, Ludeman, Evan McNeil, Morrison, Jay Alan, Lane, Jay Edgar
• Primary Examiner(s): Speer, Timothy M.
• Assistant Examiner(s): YOUNG, BRYANT L
• Application Number:
  US09/049,369
• Time in Patent Office: 1,075 Days
• Field of Search: 428/402, 428/469, 428/472, 428/701, 428/937, 148/537, 106/691, 415/170.1, 415/171.1, 415/173.1, 415/200, 416/241.R, 416/241.B, 501/80
• US Class Current: 428/402
• CPC Class Codes: C04B 14/30 Oxides other than silica ferrites C04B14/363
• CPC Class Codes: C04B 14/301 porous or hollow
• CPC Class Codes: C04B 2111/00482 Coating or impregnation materials
• CPC Class Codes: C04B 2111/28 Fire resistance, i.e. materials resistant to accidental fires or high temperatures
• CPC Class Codes: C04B 28/344 the phosphate binder being present in the starting composition solely as one or more phosphates
• CPC Class Codes: C04B 38/0038 by superficial sintering or bonding of particulate matter
• CPC Class Codes: C04B 38/08 by adding porous substances
• CPC Class Codes: F01D 11/12 using a rubstrip, e.g. erodible. deformable or resiliently-biased part
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 428/2982 Particulate matter [e.g., sphere, flake, etc.]

Abstract

A ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere and the arrangement of spheres is such that the composition is dimensionally stable and chemically stable at a temperature of approximately 1600° C. A stationary vane of a gas turbine comprising the composition of the present invention bonded to the outer surface of the vane is provided. A combustor comprising the composition bonded to the inner surface of the combustor is provided. A transition duct comprising the insulating coating bonded to the inner surface of the transition is provided. Because of abradable properties of the composition, a gas turbine blade tip seal comprising the composition also is provided. The composition is bonded to the inside surface of a shroud so that a blade tip carves grooves in the composition so as to create a customized seal for the turbine blade tip.

Claims

1. A dimensionally stable ceramic insulating composition for insulating components of a gas turbine made of ceramic matrix composites, the composition comprising:

a plurality of hollow oxide-based spheres of various dimensions;

a phosphate binder; and

at least one oxide filler powder, whereby said phosphate binder partially fills gaps between said spheres and said at least one filler powder;

said spheres being situated in said phosphate binder and said at least one filler powder such that each sphere is in contact with several other spheres, said composition being stable at temperatures up to approximately 1600°

C.

3. A stationary vane of a gas turbine, the vane made of ceramic matrix composites, having an outer surface exposed to hot gas flow of the turbine, and comprising the composition of claim 1 bonded to the outer surface of said vane.

4. The stationary vane of claim 3, wherein the vane without the composition has a temperature capability of approximately 1200°

C. and the vane with the composition is stable at a maximum coating temperature greater than 1300°

C.

5. The stationary vane of claim 4, further comprising an adhesive for bonding the composition to said outer surface of said vane.

6. A combustor of a gas turbine, the combustor made of ceramic matrix composites, having a combustion flame, having an outer surface exposed to the combustion flame, and comprising the composition of claim 1 bonded to the inner surface of said combustor.

7. The combustor of claim 6, wherein the combustor without the composition has a temperature capability of approximately 1200°

C. and the combustor with the composition is stable at a maximum coating temperature up to approximately 1600°

C.

8. The combustor of claim 7, further comprising an adhesive for bonding the composition to said inner surface of said combustor.

9. A transition duct of a gas turbine, the transition duct made of ceramic matrix composites, having an inner surface exposed to combustor exhaust gases, and comprising the composition of claim 1 bonded to the inner surface of said transition duct.

10. The transition duct of claim 9, wherein the transition duct without the composition has a temperature capability of approximately 1200°

C. and the transition duct with the composition is stable at a maximum coating temperature up to approximately 1600°

C.

11. The transition duct of claim 10 further comprising an adhesive for bonding the composition to said inner surface of said transition duct.

15. The composition of claim 1, wherein the size and weight percentage of the spheres are effective such that each sphere is in contact with at least three other spheres.

16. The composition of claim 1, wherein the size and weight percentage of the spheres are effective such that each sphere is in contact with at least four other spheres.

17. The composition of claim 1, having a coefficient of thermal expansion close to that of the ceramic matrix composites.

2. A dimensionally stable ceramic abradable composition for sealing blade tips of a gas turbine made of ceramic matrix composites, wherein the blade tips rotate within a shroud of the turbine, the shroud being made of ceramic matrix composites, the composition comprising:

a plurality of hollow oxide-based spheres of various dimensions;

a phosphate binder; and

at least one oxide filler powder, whereby said phosphate binder partially fills gaps between said spheres and said at least one filler powder;

said spheres being situated in said phosphate binder and said at least one filler powder such that each sphere is in contact with several other spheres, said composition being stable at temperatures up to approximately 1600°

C.

12. A gas turbine blade tip seal comprising:

a turbine blade tip;

an inner surface of a shroud within which said blade tip rotates, the shroud being made of ceramic matrix composites; and

the composition of claim 2 bonded to said inside surface of the shroud so that said blade tip carves grooves in the composition so as to create a customized seal for the turbine blade tip.

13. The blade tip seal of claim 12, wherein the shroud without the composition has a temperature capability of approximately 1200°

C. and the shroud with the composition is stable at a maximum coating temperature up to approximately 1600°

C.

14. The blade tip seal of claim 13 further comprising an adhesive for bonding the composition to said inner surface of said shroud.

18. The composition of claim 2, wherein the size and weight percentage of the spheres are effective such that each sphere is in contact with at least three other spheres.

19. The composition of claim 2, wherein the size and weight percentage of the spheres are effective such that each sphere is in contact with at least four other spheres.

20. The composition of claim 2, having a coefficient of thermal expansion close to that of the ceramic matrix composites.