THE TEMPERATURE FIELD OF A TURBINE BLADE WITH TRANSVERSE AIR COOLING,

Abstract

The cross section of a turbine blade with a deflector in a uniform gas flow is examined. The cooling air, entering near the root section within the deflector, passes through the slits at the leading edge of the deflector. It then breaks into branches and flows through transverse channels over concave and convex surfaces. Air consumption for cooling the back edge and trough is noted along the blade length. The stagnation temperature of the gas in the boundary layer over the profile and the blade temperature over the wall thickness are considered. The balance equations for a blade element and the air flowing past the element are equated.

Document Details

Document Type
Technical Report
Publication Date
Aug 20, 1969
Accession Number
AD0700582

Entities

People

  • I. S. Lyubchenko

Organizations

  • National Air and Space Intelligence Center

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Deflectors
  • Equations
  • Flow
  • Gas Flow
  • Layers
  • Leading Edges
  • Stagnation Temperature
  • Thickness
  • Transverse
  • Turbine Blades
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Optical Physics and Photonics.