Support assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10385712-B2
Application number	US-201514719569-A
Country	US
Kind code	B2
Filing date	May 22, 2015
Priority date	May 22, 2015
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A seal assembly for a gas turbine engine includes a first member including a first seal land for contacting a first structure. A second member includes a second seal land for contacting a second structure and a third seal land for contacting a third structure. The first member and the second member form a pivotable connection.

First claim

What is claimed is:

1. A seal assembly for a gas turbine engine comprising:
a first member including a first seal land for contacting a first structure; and
a second member including a second seal land for contacting a second structure and a third seal land for contacting a third structure, wherein the first member and the second member form a pivotable connection, wherein the pivotable connection includes a male portion on one of the first member and the second member received within a female portion on the other of the first member and the second member and wherein the pivotable connection is spring loaded.

2. The assembly of claim 1 , wherein at least one of the first member and the second member includes at least one passage extending through a body portion.

3. The assembly of claim 1 , wherein the first member and the second member each form a circumferential ring, the first seal land is located on a first radial side of the second seal land and the third seal land is located on a second radial side of the second seal land opposite the first radial side.

4. The assembly of claim 1 , wherein the first seal land is located on a first end of the first member and the second seal land and the third seal land are located on opposite ends of the second member and the first seal land and the third seal land face a common axial direction.

5. The assembly of claim 1 , wherein the first member and the second member each form a circumferential ring extending about a central longitudinal axis and the first seal land and the third seal land are on a first axial side of the seal assembly and the second seal land is on a second opposite axial side of the seal assembly.

6. The assembly of claim 1 , wherein the second seal land is located on the female portion of the pivotable connection.

7. A gas turbine engine comprising:
a first structure;
a second structure spaced from the first structure;
a third structure aligned on the same side as the first structure with the first structure; and
a seal including:
a first member including a first seal land for contacting a first structure; and
a second member including a second seal land for contacting a second structure and a third seal land for contacting a third structure, wherein the first member and the second member form a pivotable connection.

8. The gas turbine engine of claim 7 , wherein the first structure, the second structure, and the third structure include one of a vane, a blade outer air seal, a gas turbine engine static structure, a gas turbine engine case, or a cover plate for a control ring for a gas turbine engine and the first member is spaced from the third structure.

9. The gas turbine engine of claim 8 , wherein the pivotable connection includes a male portion on the first member received within a female portion on the second member and the second seal land is located on the female portion.

10. The gas turbine engine of claim 9 , wherein the pivotable connection is spring loaded for providing a biasing force between the first structure, the second structure, and the third structure.

11. The gas turbine engine of claim 7 , wherein at least one of the first member and the second member includes at least one passage extending through a body portion.

12. The gas turbine engine of claim 7 , wherein the first member and the second member each form a circumferential ring, the first seal land is located on a first radial side of the second seal land and the third seal land is located on a second radial side of the second seal land opposite the first radial side.

13. The gas turbine engine of claim 7 , wherein the first seal land is located on a distal end of the first member and the second seal land and the third seal land are located on opposite ends of the second member, the first structure includes a first seal land contact surface contacting the first seal land, the third structure includes a third seal land contact surface and the first seal land contact surface and the third seal land contact surface face a common axial direction.

14. The gas turbine engine of claim 7 , wherein the first structure is axially aligned with the third structure on a upstream side of the seal relative to a central longitudinal axis of the gas turbine engine, the second structure is downstream of the seal relative to the central longitudinal axis of the gas turbine engine, and first structure and the third structure, the first structure includes a first seal land contact surface contacting the first seal land, the third structure includes a third seal land contact surface and the first seal land contact surface and the third seal land contact surface face a common axial direction.

15. The gas turbine engine of claim 7 , wherein the first member and the second member each form a circumferential ring extending about a central longitudinal axis of the gas turbine engine and the first seal land and the third seal land are on a first axial side of the seal relative to the central longitudinal axis of the gas turbine engine and the second seal land is on a second opposite axial side of the seal relative to the central longitudinal axis of the gas turbine engine, and the first seal land is located on a first radial side of the second seal land and the third seal land is located on a second radially side of the second seal land opposite the first radial side, and the first structure includes a first seal land contact surface contacting the first seal land, the third structure includes a third seal land contact surface and the first seal land contact surface and the third seal land contact surface face a common axial direction.

16. A method of sealing and/or stabilizing gas turbine engine components comprising:
engaging a first structure with a first seal land on a first member of a seal;
engaging a second structure with a second seal land on a second member of the seal;
engaging a third structure with a third seal land on the second member of the seal, wherein the first member is attached to the second member with a pivotable connection.

17. The method of claim 16 , further comprising applying a biasing force between the first structure, the second structure, and the third structure with the pivotable connection and the first member is spaced from the third structure.

18. The method of claim 16 , further comprising directing cooling fluid through passages in at least one of the first member and the second member.

19. The method of claim 16 , further comprising pivoting the first member relative to the second member and the pivotable connection includes a male portion on the first member received within a female portion on the second member and the second seal land is located on the female portion.

Assignees

• United Technologies Corp

Inventors

• Jenkins Decari S
• Miller Andrew S

Classifications

• F16J15/104

  characterised by structure · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2230/60

  Assembly methods · CPC title