| 摘要 |
A gas turbine airfoil ( 1 ) with a pressure sidewall and a suction sidewall ( 6 ) comprises several internal cooling passages, through which cooling air flows, and several film cooling holes ( 7 ) that extend from the internal cooling passages to the outer surface ( 11 ) of the suction sidewall ( 6 ). According to the invention the film cooling holes ( 7 ) are oriented in the radial outward direction as well as toward the trailing edge of the airfoil ( 1 ). They each comprise a diffused section with sidewalls that are diffused in the radial outward direction, in the radial inward direction as well as toward downstream direction. Cooling air flowing through the diffused film cooling hole ( 7 ) onto the outer surface ( 6 ) of the airfoil ( 1 ) forms an air curtain preventing plugging of the film cooling hole by particles entrained in the hot gas flow.
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