VEIL COOLING OF RADIAL-FLOW TURBINES,

Abstract

This suppliement presents results obtained in limited tests with 1500F turbine gas inlet temperature. The position of the cooling jet with respect to the disk of the wheel was found to be an important parameter in veil cooling. When the flow of the issuing cooling jet is at the surface of the disk, it provides a high temperature gradient for heat transfer, but it does not induce any considerable mixing with the main gas stream, and thus does not promote a high heat transfer. When the cooling jet is directed at a slight distance from the surface of the disk, there is more cooling gas mixing with the main gas stream, and the effect of this spacing required investigation to provide a sound basis for higher temperature tests of veil cooling effects. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 24, 1964
Accession Number
AD0430571

Entities

People

  • M. Branger

Tags

DTIC Thesaurus Topics

  • Flow
  • Heat Transfer
  • High Temperature
  • Isotherms
  • Radial Flow
  • Radial Turbines
  • Temperature Gradients
  • Turbines

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster