| 摘要 |
An internal fluid cooling system for a gas turbine aerofoil ( 2 ) comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage ( 50,52,54 & 48,56,58 ) in the interior of the aerofoil ( 2 ). The cooling fluid-in particular air-is supplied to an inlet end ( 22,24 ) of each passage ( 50,52,54 & 48,56,58 ) and exhausted through a multiplicity of discharge holes ( 60,62,64,68 ) to provide tip, leading edge, trailing edge and surface film cooling. The inlet end ( 22 ) of a first serpentine passage ( 50,52,54 ) is positioned close to the leading edge ( 26 ) and flows rearwards while the inlet end ( 24 ) of the second serpentine passage ( 48,56,58 ) is positioned close to the trailing edge ( 28 ) and flows forwards. These serpentine passages are disposed side-by-side, one adjacent the pressure surface ( 14 ) and the other adjacent the suction surface ( 16 ) on opposite sides of a main load carrying member ( 30 ) which comprises a major part of the internal structure ( 30,36,38,40,42,44 ) of the aerofoil ( 2 ).
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