CFD Predictions of Pulsed Film Cooling Heat Flux On a Turbine Blade Leading Edge

Abstract

A computational study was conducted to determine how leading edge film cooling performance is affected by pulsing the coolant flow. Time resolved adiabatic effectiveness and heat transfer coefficient are used to calculate the temporally averaged, spatially resolved net heat flux reduction for several pulsing scenarios. Net heat flux is generally increased by pulsing the film coolant, with greater degradation for higher pulsation amplitudes relative to the average blowing ratio.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 2010
Accession Number
ADA522117

Entities

People

  • James L. Rutledge
  • Paul I. King
  • Richard Rivir

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Amplitude
  • Boundary Layer
  • Coefficients
  • Cooling
  • Film Cooling
  • Fluid Flow
  • Frequency
  • Governments
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Leading Edges
  • Turbine Blades
  • Turbines
  • United States

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.