Deflection mitigation structure for combustion system

Patent metadata

Field	Value
Publication number	US-11149692-B2
Application number	US-201816006151-A
Country	US
Kind code	B2
Filing date	Jun 12, 2018
Priority date	Jun 12, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A combustion section for a gas turbine engine including an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material defines a second heat transfer coefficient less than the first heat transfer coefficient.

First claim

What is claimed is:

1. A combustion section for a gas turbine engine, the combustion section comprising:
a combustor and a combustor casing, the combustor casing defined by an outer casing radially outward from an inner casing;
the combustor defined by an inner liner disposed radially inward from the outer casing and an outer liner disposed radially between the outer casing and the inner line; and, an inner casing extending at least partially radially inward from the outer casing such that the combustor is at least partially radially enclosed between the inner casing and the outer casing, the inner casing comprising a first material having a first heat transfer coefficient, wherein a second material is extended at least partially over an outer diameter of the first material such that the second material is disposed radially between the first material and the inner liner, the second material spaced apart from the inner liner, and further wherein the second material defines a second heat transfer coefficient less than the first heat transfer coefficient.

2. The combustion section of claim 1 , wherein the second material comprises a thermal barrier coating.

3. The combustion section of claim 2 , wherein the second material comprises a yttria-stabilized zirconia thermal barrier coating.

4. The combustion section of claim 1 , wherein the second material comprises a nickel-based alloy.

5. The combustion section of claim 1 , wherein the second material comprises a honeycomb structure.

6. The combustion section of claim 1 , wherein a third layer is defined between the first material and the second material.

7. The combustion section of claim 6 , wherein the third layer comprises a bonding material directly on the outer diameter of the inner casing.

8. The combustion section of claim 7 , wherein the third layer comprises Ni and Al.

9. The combustion section of claim 8 , wherein the third layer comprises NiCRAlY.

10. The combustion section of claim 6 , wherein the third layer defines a gas cavity between the first material and the second material.

11. The combustion section of claim 1 , wherein the first material is a metal or metal alloy.

12. The combustion section of claim 1 , wherein the second material is directly on the outer diameter of the inner casing.

13. A method for reducing a thermal gradient between an inner casing of a combustion section having a combustor and a combustor casing, the combustor casing defined by an outer casing radially outward from the inner casing, the method comprising:
forming a second material over an outer diameter of a first material defining the inner casing and having a first heat transfer coefficient, wherein the second material defines a second heat transfer coefficient less than the first heat transfer coefficient, wherein the combustor is defined by an inner liner disposed radially inward from the outer casing and an outer liner disposed radially between the outer casing and the inner liner, wherein the inner casing extends at least partially radially inward from the outer casing such that the combustor is at least partially radially enclosed between the inner casing and the outer casing, and wherein the second material is spaced apart from the inner liner.

14. The method of claim 13 , wherein the second material comprises a thermal barrier coating.

15. The method of claim 13 , wherein the second material comprises a honeycomb structure.

16. The method of claim 13 , further comprising:
forming a third layer between the first material and the second material, wherein the third layer contacts the outer diameter of the first material.

17. The method of claim 16 , further comprising:
applying a bonding material directly on the outer diameter of the inner casing.

18. The method of claim 17 , wherein the third layer that is applied directly to the outer diameter of the inner casing comprises Ni and Al.

19. The method of claim 17 , wherein the third layer is applied directly to the outer diameter of the inner casing defining the first material as a metal or metal alloy.

20. The method of claim 16 , wherein the third layer defines a gas cavity between the first material and the second material.

Assignees

• Gen Electric

Inventors

• Venzon Anthony Joseph
• Payne Jeremy Kevin
• Patel Narendra Kumar

Classifications

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2300/175

  Superalloys · CPC title

• F02K9/64 Primary

  having cooling arrangements · CPC title