Self-Retained Platform Cooling Plate for Turbine Vane.

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)

Document Details

Document Type
Technical Report
Publication Date
Nov 13, 1985
Accession Number
ADD012218

Entities

People

  • Stephen N. Finger

Organizations

  • United States Department of the Air Force

Tags

DTIC Thesaurus Topics

  • Assembly
  • Energy Generators
  • Energy Systems
  • Engines
  • Gas Turbines
  • Generators
  • Heat Engines
  • Heat Transfer Devices
  • Internal Combustion Engines
  • Jet Aircraft
  • Jet Engines
  • Mechanical Equipment
  • Platforms
  • Turbine Components
  • Turbine Stators
  • Turbines
  • Turbojet Engines

Fields of Study

  • Engineering

Readers

  • Combustion and Flow Dynamics.
  • Electrical Engineering