Wake Interaction Effects on the Transition Process on Turbine Blades.

Abstract

Wide bandwidth (100 kHz) heat transfer instrumentation was used to make detailed time resolved measurements on a two dimensional gas turbine rotor cascade blade surface under the influence of simulated unsteady wake and shock passing events. The instrumentation was capable of detecting and tracking naturally occurring transitional turbulent spots confirming the classical model of boundary layer transition. In addition instantaneous large excursions in the surface heat transfer were observed as the simulated wake shock structure from a transonic nozzle guide wave passed over the rotor cascade. The transitional behavior of the blade boundary layer was seen to depend primarily on free stream turbulence and Reynolds number and, away from the direct interaction region, to be relatively unaffected by the wake/shock induced disturbances. Keywords: Gas Turbine Heat Transfer; Unsteady Wake Interactions; Boundary Layer Transition.

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Document Details

Document Type
Technical Report
Publication Date
Oct 30, 1986
Accession Number
ADA177094

Entities

Organizations

  • University of Oxford

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Transition
  • Convection
  • Digital Data
  • Equations
  • Flow Visualization
  • Fluid Flow
  • Gas Turbines
  • Heat Transfer
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Steady Flow
  • Turbine Blades
  • Turbines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.