TURBINE BLADE HAVING TRANSPIRATION STRIP COOLING AND METHOD OF MANUFACTURE

Abstract

A gas turbine engine turbine blade and method of manufacture includes an airfoil having pressure and suction sides joined together at leading and trailing edges. The airfoil further includes a supply channel for receiving compressed air, and has an elongate recess disposed in at least one of the pressure and suction sides which is separated from the supply channel by a partition. The partition includes a plurality of spaced apart flow metering holes disposed in flow communication with the supply channel. A transpiration strip is fixedly joined to the airfoil in the recess and spaced from the partition to define a plenum for receiving the compressed air from the metering holes. The transpiration strip is pervious for channeling the compressed air from the plenum in a blanket of film cooling boundary layer air therefrom.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1DAVID M. KERCHER

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