| 摘要 |
A gas turbine engine (10) comprising a rotor (30) and a stator (32) which define first, second and third cavities (52, 54, 56); the rotor (30) and stator (32) define a seal (60) therebetween and which is located for sealing between the second and third cavities (54, 56), the rotor (30) comprises an aperture (70) through which a gas flow (72) passes from the first cavity (52) to the second cavity (54) characterised in that the seal (60) comprises a deflector (74) that extends axially over at least a portion of the aperture (74) to deflect at least a part of the gas towards the rotor (30). |
