Seal assembly for turbine engine component

Patent metadata

Field	Value
Publication number	US-10808562-B2
Application number	US-201916254694-A
Country	US
Kind code	B2
Filing date	Jan 23, 2019
Priority date	Sep 9, 2015
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. A seal assembly for a gas turbine engine comprising:
a housing mountable to an engine static structure;
a seal carrier secured to the housing and configured to be selectively biased from the housing;
a wedge seal secured to the seal carrier, wherein the wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing, and wherein the wedge seal is separate and distinct from the seal carrier;
wherein the wedge seal spans across a gap defined by opposed mate faces of the adjacent blade outer air seals; and
wherein the seal carrier defines a spring cavity receiving a spring that is configured to bias the seal carrier away from the housing.

2. The seal assembly as recited in claim 1 , wherein the wedge seal defines a first engagement surface and a second engagement surface joined at an apex.

3. The seal assembly as recited in claim 1 , wherein the wedge seal defines a first engagement surface and a second engagement surface joined at an apex that faces away from the housing.

4. The seal assembly as recited in claim 2 , further comprising an insulation member arranged between the wedge seal and the housing.

5. The seal assembly as recited in claim 4 , wherein the insulation member is a thermal barrier coating deposited on the wedge seal.

6. A seal assembly for a gas turbine engine comprising:
a housing mountable to an engine static structure:
a seal carrier secured to the housing and configured to be selectively biased from the housing;
a wedge seal secured to the seal carrier, wherein the wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing, and wherein the wedge seal is separate and distinct from the seal carrier; and
an insulation member arranged between the wedge seal and the housing.

7. The seal assembly as recited in claim 6 , wherein the insulation member is a thermal barrier coating deposited on surfaces of the wedge seal.

8. A gas turbine engine comprising:
a section defining a core flow path along an engine axis;
at least one set of components arranged about the engine axis to define a core flow path, the at least one set of components comprising:
a first component defining a first sealing surface adjacent to a first mate face; and
a second component defining a second sealing surface adjacent to a second mate face, the first and second mate faces spaced apart to define a gap; and
a seal assembly comprising:
a housing;
a seal carrier secured to the housing and configured to be selectively biased from the housing; and
a wedge seal secured to the seal carrier, wherein the wedge seal abuts against at least one of the first and second sealing surfaces and self-centers in response to movement of the seal carrier relative to the housing, and wherein the wedge seal is separate and distinct from the seal carrier;

wherein the first component is mounded to a first support structure, the second component is mounted to a second, different support structure moveable relative to the first support structure, and the housing is coupled to at least one of the first and second support structures; and
wherein the housing includes a support member selectively received in a slot defined by the first support structure.

9. The gas turbine engine as recited in claim 8 , wherein the section is a turbine section, and each of the first and second components is a blade outer air seal (BOAS).

10. The gas turbine engine as recited in claim 9 , wherein the wedge seal spans across the gap.

11. The gas turbine engine as recited in claim 10 , wherein the wedge seal defines a first engagement surface and a second engagement surface joined at an apex, and the first engagement surface abuts against the first sealing surface and the second engagement surface abuts against the second sealing surface in response to movement of the seal carrier.

12. The gas turbine engine as recited in claim 11 , wherein the apex is positioned in the gap, and the first and second sealing surfaces slope towards the corresponding first and second mate faces.

13. The gas turbine engine as recited in claim 10 , wherein the seal assembly includes a spring configured to bias the seal carrier away from the housing in response to movement of the first component relative to the first support structure.

14. The gas turbine engine as recited in claim 10 , wherein the seal carrier is moveable relative to the housing in response to movement of at least one of the first and second components in a circumferential direction relative to the engine axis.

15. The gas turbine engine as recited in claim 8 , wherein the section is a turbine section.

16. The gas turbine engine as recited in claim 15 , wherein each of the first and second components is one of an airfoil, a blade outer air seal (BOAS), and a combustor panel.

17. The gas turbine engine as recited in claim 8 , wherein each of the first and second components is one of an airfoil, a blade outer air seal (BOAS), and a combustor panel.

18. The gas turbine engine as recited in claim 14 , further comprising a spring that is configured to bias the seal carrier away from the housing.

19. The gas turbine engine as recited in claim 12 , wherein the seal carrier defines a spring cavity receiving a spring that is configured to bias the seal carrier away from the housing.

20. The gas turbine engine as recited in claim 15 , wherein the seal carrier defines a spring cavity receiving a spring that is configured to bias the seal carrier away from the housing.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Mccaffrey Michael G

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2260/52

  involving springs · CPC title

• F16J15/061

  with positioning means (F16J15/0831 takes precedence) · CPC title

• F23R3/002

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

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title