| 摘要 |
An aerofoil (20) for a gas turbine engine (8), the aerofoil (20) comprises a leading edge (54) and a trailing edge (56), pressure and suction surfaces and defines therebetween an internal passage (36) for the flow of cooling fluid therethrough. A particle deflector means (60) is disposed within the passage to deflect particles within a cooling fluid flow away from a region (58) of the aerofoil (20) susceptible to particle build up and subsequent blockage, such as a cooling passage for a shroud of a blade. |
