Wake Interaction Effects on the Transition Process on Turbine Blades

Abstract

The unsteady behavior of a 2-d gas turbine rotor blade boundary layer was observed using wide bandwidth surface heat transfer thin film gauges. The tests were conducted in a compression heated short duration wind tunnel cascade at realistic gas turbine aero/thermo-dynamic conditions. Wake passage effects were generated using a rotating set of upstream bars. The unsteadiness of the wake and shock interactions were observed through the effects on temporally and spatially accurate heat transfer measurements. Keywords: Gas turbine rotor blades; Thin film gauges; Wind tunnel tests; Two dimensional; Cascade structures; Gas turbine heat transfer; Boundary layer transition; Unsteady wake interactions; Great Britain.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1989
Accession Number
ADA214492

Entities

People

  • J. E. Lagraff
  • R. W. Ainsworth

Organizations

  • University of Oxford

Tags

Communities of Interest

  • Advanced Electronics
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Transition
  • Flow Fields
  • Flow Visualization
  • Gas Turbines
  • Heat Transfer
  • Instrumentation
  • Measurement
  • Thin Films
  • Three Dimensional
  • Turbine Blades
  • Turbines
  • Turbomachinery
  • Two Dimensional
  • Wind
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.