| 摘要 |
There is described a seal assembly (210) for a gas turbine engine comprising: a first seal (212) having a sealing passage which defines a flow path trajectory for leakage air, the first seal (212) for partitioning a first pressure area (216) to a lower pressure area; a second seal (214) located along the line of the flow path trajectory of the first seal (212), the second seal (214) for partitioning a second pressure area (234) and the lower pressure area; a deflection member (236) located between the first seal (212) and second seal (214), and in the trajectory of the flow path from the first seal (212). |
