Self-Retained Platform Cooling Plate for Turbine Vane.
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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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
- Jet and Gas Turbine Engines