Accession Number:

ADA522117

Title:

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

Descriptive Note:

Journal article (postprint)

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH TURBINE ENGINE DIV

Report Date:

2010-04-01

Pagination or Media Count:

13.0

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.

Subject Categories:

  • Aircraft
  • Fluid Mechanics
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE