Turbine blade having transpiration strip cooling and method of m

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416231R, 415115, F01D 518

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active

056904738

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.

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R.J. Goldstein et al, "Film-Cooling Effectiveness with Injection Through a Porous Section," 29 Nov.-4 Dec. 1964, ASME 64-WA/HT-30, pp. 1-11.
J. Starkenberg, "Boundary Layer Transition on a Film-Cooled Slender Cone," 20-22 Jan. 1975, AIAA Paper 75-194, pp. cover, 1-10.

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