Film cooling of the gas turbine endwall by discrete-hole injection

M. Y. Jabbarl, K. C. Marston, E. R.G. Eckert, R. J. Goldstein

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

1 Scopus citations

Abstract

Film cooling performance for injection through discrete holes in the endwall of a turbine blade is investigated. The effectiveness is measured at sixty locations in the region covered by injection. Three nominal blowing rates, two density ratios, and two approaching flow Reynolds numbers are examined. Analysis of the data reveals that even sixty locations are insufficient for the determination of the field of film cooling effectiveness with its strong local variations. Visualization of the traces of the coolant jets on the endwall surface, using ammonium-diazo-paper, provides useful qualitative information for the interpretation of the measurements, revealing the paths and interaction of the jets which change with blowing rate and density ratio.

Original languageEnglish (US)
Title of host publicationHeat Transfer; Electric Power; Industrial and Cogeneration
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878866
DOIs
StatePublished - 1994
EventASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, GT 1994 - The Hague, Netherlands
Duration: Jun 13 1994Jun 16 1994

Publication series

NameProceedings of the ASME Turbo Expo
Volume4

Other

OtherASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, GT 1994
Country/TerritoryNetherlands
CityThe Hague
Period6/13/946/16/94

Bibliographical note

Publisher Copyright:
© 1994 by ASME.

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