A Comparison of Film Cooling Techniques in a High Speed, True Scale, Fully Cooled Turbine Vane Ring

Abstract

An effort was undertaken to understand the impact of different film cooling configurations in a true scale turbine vane for three proprietary airfoil designs. The measurements for this study were taken at the United States Air Force Turbine Research Facility (TRF). The TRF enabled heat transfer data to be obtained on full scale turbine hardware under realistic engine conditions. The surface heat flux of the turbine blades was analyzed using the impulse response method. The overall effectiveness was compared between airfoil types at 60% span over varying streamwise locations on both suction and pressure surfaces. Using an approximated massflow, a comparison of the overall effectiveness with respect to massflow rate could be made between airfoils at three different airfoil locations. The shaped hole and slot cooling configurations were found to have higher average overall effectiveness for lower massflow rates than the multiple hole configuration based on the conditions tested.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2007
Accession Number
ADA470649

Entities

People

  • Michael J. Umholtz

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics
  • Human Systems

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Film Cooling
  • Gas Turbines
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Measurement
  • Research Facilities
  • Specific Heat
  • Test Facilities
  • Turbine Blades
  • Turbine Components
  • Turbines
  • Turbomachinery
  • Turbulent Mixing
  • United States

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Trauma or Military Medicine
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).