Turbine blade with multiple trailing edge cooling slots

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

Reexamination Certificate

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Details

C416S09600A

Reexamination Certificate

active

08079813

ABSTRACT:
A cooling system for a turbine airfoil of a turbine engine has a multiple suction side cooling slots extending from a front edge on the suction side to the center of the trailing edge or even to the pressure side of the center line and a pressure side cooling slot curving to a pressure side outlet forward of the trailing edge and having a front pressure side lip that is aligned with or forward of the front edge of the suction side cooling slots. The suction side cooling slots receive cooling flow from the pressure side cooling slots through a boundary layer bleed valve, which is also aligned with or rearward of the pressure side lip. The cooling system may also combine double impingement cooling with these features. The cooling system minimizes shear mixing, reduces hot spots and can reduce the trailing edge thickness, resulting in more efficient stage performance and extended operational life.

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