Patent ID: 9638052
Date: 2017-05-02
CPC Classifications: F01D,F04D,F05D,F16J

Claim:
1. A seal assembly between static and rotating parts of a gas turbine engine comprising: a first seal formed as a labyrinth seal having one or more fins extending between the stator and rotor to a seating interlace which defines a sealing passage and a flow path trajectory for leakage air exiting the seal along an exit flow path, the labyrinth seal for partitioning a first pressure area and a lower pressure area; a second seal located along a line of the flow path trajectory of the first seal, the second seal for partitioning a second pressure area and the lower pressure area; a first deflection member downstream of the labyrinth seal relative to the leakage air exiting the first seal and extending between the rotor and stator, the first deflection member being located between the first seal and the second seal, and traversing the exit flow path from the first seal, wherein the separation between the deflection member and opposing static part or rotating part is greater than a separation of the sealing interface.