System for thermally isolating a turbine shroud

Patent metadata

Field	Value
Publication number	US-9945242-B2
Application number	US-201514708336-A
Country	US
Kind code	B2
Filing date	May 11, 2015
Priority date	May 11, 2015
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.

First claim

What is claimed is:

1. A system for thermally isolating a turbine shroud of a turbine shroud assembly, the system comprising:
a shroud support having an inner surface;
the turbine shroud connected to the shroud support via a retaining pin, the turbine shroud having a hot side surface radially spaced from a back side surface, wherein the back side surface is oriented towards the inner surface of the shroud support, wherein at least a portion of the back side surface is curved; and
a coating disposed along the back side surface of the turbine shroud, wherein the coating regulates heat transfer via conduction or radiation from the back side surface of the turbine shroud to the shroud support, the coating further comprising;
a first coating material covering a first portion of the back side surface; and
a second coating material covering a second portion of the back side surface,
wherein the first coating material is a different coating material from the second coating material, and
wherein the curved back side surface portion receives the retaining pin.

2. The system as in claim 1 , wherein the turbine shroud is formed from a ceramic matrix composite material,
wherein the first coating material covers a first radially outward facing portion of the back side surface, and
wherein the second coating material covers a second radially outward facing portion of the back side surface.

3. The system as in claim 1 , wherein at least a portion of the coating has an emissivity value that is less than an emissivity value of the turbine shroud,
wherein the first coating material covers a first axially forward facing portion of the back side surface, and
wherein the second coating material covers a second axially forward facing portion of the back side surface.

4. The system as in claim 3 , wherein the first coating material has an emissivity value of greater than 0 and less than 0.7.

5. The system as in claim 4 , wherein the second coating material has an emissivity value of between 0.3 and 0.7.

6. The system as in claim 5 , wherein at least a portion of the coating comprises a multi-layer environmental barrier coating, wherein at least one layer of the environmental barrier coating is porous, and
wherein the at least one layer of porous environmental barrier coating has a density between 50% and 90%.

7. The system as in claim 6 , wherein the shroud support is formed from a metal alloy, and
wherein the at least one layer of porous environmental barrier coating has a density between 65% and 80%.

8. The system as in claim 1 , wherein the turbine shroud is formed from a ceramic matrix composite material having an emissivity value of 0.8,
wherein the first coating material covers a first axially aft facing portion of the back side surface, and
wherein the second coating material covers a second axially aft facing portion of the back side surface.

9. The system as in claim 1 , wherein the first coating material is disposed along a portion of the back side surface that is not immediately adjacent to or in contact with the inner surface of the turbine shroud support and the second coating material is disposed along a portion of the back side surface that is immediately adjacent or in contact with the inner surface of the turbine shroud support.

10. The system as in claim 1 , further comprising a seal that engages with a portion of the coating and with the inner surface of the shroud support, wherein the portion of the coating engaged with the seal regulates conductive heat transfer from the back side surface of the turbine shroud to the seal.

11. The system as in claim 1 , wherein a portion of the back side surface is in contact with the inner surface of the turbine shroud support via a portion of the coating, and
wherein the first coating material further comprises a thermal paint.

12. The system as in claim 1 , wherein the turbine shroud further includes a leading edge portion and a trailing edge portion, wherein at least a portion of the coating is disposed along at least one of the leading edge portion or the trailing edge portion.

13. The system as in claim 12 , wherein at least a portion of the coating has an emissivity value that is less than an emissivity value of the turbine shroud.

14. The system as in claim 13 , wherein at least a portion of the coating has an emissivity value of greater than 0 and less than 0.7.

15. The system as in claim 12 , wherein the turbine shroud is formed from a ceramic matrix composite material.

16. The system as in claim 15 , wherein the ceramic matrix composite material has an emissivity value of between 0.6 and 0.8.

17. The system as in claim 12 , wherein the first coating material is disposed along a portion of the back side surface that is not immediately adjacent to or in contact with the inner surface of the turbine shroud support and the second coating material is disposed along a portion of the back side surface that is immediately adjacent or in contact with the inner surface of the turbine shroud support.

18. The system as in claim 12 , further comprising a seal that engages with a portion of the coating and with the inner surface of the shroud support, wherein the portion of the coating engaged with the seal regulates conductive heat transfer from the back side surface of the turbine shroud to the seal.

19. The system as in claim 12 , wherein a portion of the back side surface is in contact with the inner surface of the turbine shroud support via a portion of the coating, wherein the portion of the coating engaged with the inner surface comprises a multi-layer environmental barrier coating, wherein at least one layer of the environmental barrier coating is porous, and
wherein the multi-layer environmental barrier coating is a 5-layer environmental barrier coating.

20. A gas turbine engine, comprising:
a compressor;
a combustion section;
a turbine section having a turbine shroud assembly that circumscribes a row of turbine rotor blades; and
a system for thermally isolating a turbine shroud of the turbine shroud assembly, the system comprising:
a shroud support having an inner surface;
the turbine shroud connected to the shroud support via a retaining pin, the turbine shroud being formed from a ceramic matrix composite material, the turbine shroud having a hot side surface radially spaced from a back side surface, wherein at least a portion of the back side surface is oriented towards the inner surface of the shroud support, wherein at least a portion of the back side surface is curved; and
a coating disposed on the back side surface of the turbine shroud, wherein the coating regulates heat transfer via conduction or radiation from the back side surface of the turbine shroud to the shroud support, the coating further comprising;
a first coating material covering a first portion of the back side surface; and
a second coating material covering a second portion of the back side surface,
wherein the first coating material is a different coating material from the second coating material, and
wherein the curved back side surface portion receives the retaining pin.

Assignees

• Gen Electric

Inventors

• Tura Christopher Paul
• Fitzpatrick Dylan James

Classifications

• F01D25/08

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2300/5024

  Heat conductivity · CPC title

• C04B41/52

  Multiple coating or impregnating {multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation} · CPC title

• F05D2220/32

  in gas turbines · CPC title