Seal support feature for brush seals
AssigneeRaytheon Technologies Corporation
InventorsTerence P. Tyler, Brian C. McLaughlin
Life of this patent
Estimating the term…
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.
Claims16
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.
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.
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.
Dependencies are inferred from the claim text.