Seal assembly for aircraft engine
A seal assembly for an aircraft engine includes a first seal having an upstream end exposed to a first pressure area, and a downstream end exposed to a second pressure area, the first seal at least partially defining an intermediate pressure area and a chamber being fluidly connected to the second pressure area and to the intermediate pressure area through passages defined in the first seal, the chamber allowing for a mixing of a first portion of a stream of air with air from the second pressure area, and a second seal connected to the first seal, the second seal biasing the first portion of the stream of air toward the passages, and allowing a second portion of the stream of air from flowing therethrough toward the second pressure area. A method of flowing air through an aircraft seal assembly is also described.
1. A seal assembly for an aircraft engine, comprising:
a first seal extending in a spacing defined in a radial direction between first and second components of the aircraft engine, the first seal connected to the first component and having an upstream end exposed to a first pressure area, and a downstream end exposed to a second pressure area, the first seal allowing a stream of air from flowing in an axial direction from the upstream end of the first seal into the spacing toward the downstream end of the first seal, the first seal at least partially defining an intermediate pressure area and a chamber for receiving a first portion of the stream of air, the chamber being fluidly connected to the second pressure area and to the intermediate pressure area through passages defined in the first seal upstream of the downstream end of the first seal, the chamber allowing for a mixing of the first portion of the stream of air with air from the second pressure area; and
a second seal connected to the first seal, the second seal located in the spacing upstream of the downstream end of the first seal, and downstream of the intermediate pressure area, the second seal biasing the first portion of the stream of air toward the passages, and allowing a second portion of the stream of air from flowing through the second seal toward the second pressure area.
2. The seal assembly of claim 1 , wherein the first pressure area is a higher pressure area, the second pressure area is a lower pressure area, and the intermediate pressure area has a pressure intermediate the first and second pressure areas.
3. The seal assembly of claim 2 , wherein the second portion of the stream of air flows through the second seal, through the downstream end of the first seal and to the second pressure area.
4. The seal assembly of claim 1 , wherein the seal assembly provides for axial and radial displacements between first and second components.
5. The seal assembly of claim 1 , wherein the first seal is formed as a labyrinth seal having a plurality of fins, and each fin of the plurality of fins is pointing towards the second component.
6. The seal assembly of claim 5 , wherein the second seal includes at least one of a rope seal and a brush seal, and the second seal is located between adjacent fins of the plurality of fins.
7. The seal assembly of claim 5 , wherein each fin of the plurality of fins is inclined toward the upstream end of the first seal.
8. The seal assembly of claim 1 , wherein the passages are angled relative to the radial direction in a plane orthogonal to the axial direction.
9. The seal assembly of claim 1 , wherein each one of the passages defines a passage axis, and the passage axes are located on a same radially extending plane.
10. The seal assembly of claim 1 , further comprising a radially extending protrusion connected to the downstream end of the first seal.
11. The seal assembly of claim 10 , wherein the protrusion extends between the chamber and a discharge channel defined between the first and second components.
12. The seal assembly of claim 1 , wherein the first seal, the second seal, the first component and the second component are rotatable at a same speed.
13. The seal assembly of claim 12 , wherein the first portion of the stream of air flowing out of the passages has a speed that is different from the speed of the first seal, the second seal, the first component and the second component.
14. The seal assembly of claim 1 , wherein the first component is a disc in a compressor section of the aircraft engine.
15. The seal assembly of claim 1 , wherein the second component is a shaft extending at least partially in a compressor section of the aircraft engine.