| 摘要 |
A seal arrangement (39) provided between a static component (44) and a rotating component (46). The arrangement preferably takes the form of an interstage seal for a gas turbine engine, comprising: first and second seal members (45, 48) carried by respective said components and arranged concentrically about the rotational axis of the rotating component (46). The first seal member (45) has a plurality of radially directed seal fins (47) extending towards the second member (48) and a substantially radially directed flow outlet (49) to direct cooling air (F) through the first member (45). The second member (48) has a radial projection (51) at one end of its axial length, the projection extending towards the first member (45) at a position between the flow outlet (49) and said seal fins (47), alternatively the flow outlet (49) is adjacent a seal fin (55) which is configured so as to be concave towards the flow outlet (49).
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