| 摘要 |
Film coolant passages through the wall of a hollow airfoil for a gas turbine engine are oriented to direct coolant fluid therefrom at a substantial acute angle to the downstream direction and at a shallow angle to the surface of the airfoil. Each passage includes a metering portion at its inlet end and a four sided diffusing portion at its outlet end. The diffusing portion includes a pair of adjoining surfaces which are both parallel to a central axis of the passage, and another pair of adjoining surfaces which diverge from the central axis, the diverging pair of surfaces being located on the downstream side of the passage. With this configuration the coolant completely fills the diffusing section and exits as a wide film of coolant within the boundary layer downstream of the passage outlet.
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