| 摘要 |
A turbine airfoil, such as a blade, having a leading edge cooling circuit for cooling the leading edge of the airfoil, and a separate serpentine cooling circuit for cooling the remaining portion of the airfoil. The serpentine circuit includes a first leg connecting a plurality of discharge holes for cooling the trailing edge of the airfoil, and a third leg connected to a plurality of film cooling holes to cool the pressure side wall of the airfoil. A suction side wall compartment is connected to the third leg of the serpentine circuit through a plurality of metering holes, the suction side compartment supplying a plurality of film cooling holes to cool the suction side wall of the airfoil. The compartment can be one long compartment or a plurality of separate compartment each connected by a metering hole to the third leg. The metering holes allow for an increased flow through velocity of the cooling fluid in the third leg and therefore a higher heat transfer coefficient to promote cooling of the airfoil.
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