Seal assembly for aircraft engine

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.