An experimental study of compressibility effects on the film cooling effectiveness using PSP and PIV techniques

Wenwu Zhou, Blake Johnson, Hui Hu

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

An experimental study was performed to examine effects of compressibility on film cooling effectiveness for coolant flowing from cylindrical holes in a flat plate. The incoming flow Mach number was set at 0.07, 0.30, 0.50 and 0.70. The Pressure Sensitive Paint (PSP) technique, which is based on a mass transfer analogy, was used to map the adiabatic film cooling effectiveness distribution on the surface of interest. The high-resolution PSP measurement result showed that there was marginal enhancement of film cooling performance for higher Mach number flow comparing to the Ma=0.07 case. A high-resolution Particle Image Velocimetry (PIV) system was also used to conduct detailed flow field measurements to uncover the underlying physics of film cooling in the high speed flow, which showed similar flow field measurement results at M=0.4 for both Ma=0.07 and 0.30 cases, but slightly different ensemble-averaged velocity distribution was found for M=1.25 case.

Original languageEnglish (US)
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
StatePublished - 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Publication series

Name53rd AIAA Aerospace Sciences Meeting

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period1/5/151/9/15

ASJC Scopus subject areas

  • Aerospace Engineering

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