Accession Number : ADD012218

Title :   Self-Retained Platform Cooling Plate for Turbine Vane.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Finger,Stephen N

Report Date : 13 Nov 1985

Pagination or Media Count : 13

Abstract : A turbine stator vane assembly for gas turbine or turbojet engines has an improved structure for retention of a cooling impingement plate. Two inwardly directed flanges are added to the wall-like extensions extending from the bottom of the platform upon which the vane is mounted. The cooling impingment plate is resiliently snapped into place between pin fins on the bottom of the platform and the flanges. (Author)

Descriptors :   *PATENT APPLICATIONS, *COOLING, *TURBINE STATORS, ASSEMBLY, BOTTOM, FINS, FLANGES, GAS TURBINES, PINS, PLATFORMS, TURBINE BLADES, TURBOJET ENGINES

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE