| 摘要 |
An aerofoil 20 for a gas turbine engine includes a root portion 22, a tip portion 24 located radially outwardly of the root portion 22, leading and trailing edges 26, 28 extending between the root portion 22 and the tip portion 24 and an internal cooling passage 34. The aerofoil 20 includes a plurality of cooling fluid discharge apertures 36 extending between the root portion 22 and the tip portion 24 in a trailing edge region 28a to discharge cooling fluid from the internal cooling passage 34 to an outer surface 31 of the aerofoil in the trailing edge region 28a and thereby provide a cooling film in the trailing edge region 28a. The cooling fluid discharge apertures 36 are arranged so that the flow rate of the cooling fluid discharged from the internal cooling passage 34 to the outer surface trailing edge region 28a varies between the root portion 22 and the tip portion 24.
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