Seal support feature for brush seals

Patent metadata

Field	Value
Publication number	US-11028712-B2
Application number	US-201916366860-A
Country	US
Kind code	B2
Filing date	Mar 27, 2019
Priority date	Mar 27, 2019
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal. The second seal may include a seal support extending radially therefrom which mechanically supports the first seal during engine operation.

First claim

What is claimed is:

1. A seal assembly of a gas turbine engine, comprising:
a first engine component including a flange, the first engine component disposed between a first airflow path and a second airflow path;
a first seal disposed between the first airflow path and the flange; and
a second seal disposed between the first airflow path and the second airflow path, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal,
wherein the first engine component comprises a seal support;
the first seal is disposed on the seal support; and
the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support.

2. The seal assembly of claim 1 , wherein the first airflow path is at a pressure greater than a pressure of the second airflow path.

3. The seal assembly of claim 2 , wherein the first seal and the second seal are disposed in a third airflow path between the first airflow path and the second airflow path.

4. The seal assembly of claim 3 , wherein the first seal comprises a “W” seal.

5. The seal assembly of claim 4 , wherein the second seal comprises a brush seal.

6. The seal assembly of claim 3 , further comprising a second engine component disposed between the first airflow path and the second airflow path, wherein the third airflow path is disposed between the first engine component and the second engine component.

7. The seal assembly of claim 6 , wherein the first engine component comprises a blade outer air seal and the second engine component comprises a stator vane.

8. The seal assembly of claim 5 , wherein the first seal is mechanically supported by the radially outer surface of the second seal support.

9. A turbine section of a gas turbine engine, comprising:
a stator vane;
a blade outer air seal adjacent to the stator vane;
a first seal disposed between the stator vane and the blade outer air seal; and
a second seal disposed between the stator vane and the blade outer air seal, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal during engine operation,
wherein the blade outer air seal comprises a seal support extending toward the stator vane;
the first seal is disposed on the seal support; and
the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support.

10. The turbine section of claim 9 , wherein the blade outer air seal comprises a flange extending toward the stator vane.

11. The turbine section of claim 10 , wherein the second seal is disposed on the flange.

12. The turbine section of claim 9 , wherein the first seal comprises a “W” seal.

13. The turbine section of claim 12 , wherein the second seal includes a brush seal.

14. A gas turbine engine, comprising:
a turbine section or a compressor section including a stator vane;
a blade outer air seal adjacent to the stator vane;
a first seal disposed between the stator vane and the blade outer air seal; and
a second seal disposed between the stator vane and the blade outer air seal, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal during engine operation,
wherein the blade outer air seal comprises a seal support extending toward the stator vane, the first seal disposed on the seal support, and the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support.

15. The gas turbine engine of claim 14 , wherein the first seal and the second seal are disposed between a first airflow path and a second airflow path and wherein the first airflow path is at a pressure greater than a pressure of the second airflow path.

16. The gas turbine engine of claim 15 , wherein the first seal comprises a “W” seal and the second seal includes a brush seal.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Tyler Terence P
• Mclaughlin Brian C

Classifications

• F05D2240/55

  Seals · CPC title

• F01D11/08

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/56

  Brush seals · CPC title

• F05D2240/11

  Shroud seal segments · CPC title