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An investigation on turbine tip and shroud heat transfer

Abstract:

Detailed experimental investigations have been performed to measure the heat transfer and static pressure distributions on the rotor tip and rotor casing of a gas turbine stage with a shroud-less rotor blade. The turbine stage was a modern high pressure Rolls-Royce aero-engine design with stage pressure ratio of 3.2 and nozzle guide vane (ngv) Reynolds number of 2.54E6. Measurements have been taken with and without inlet temperature distortion to the stage. The measurements were taken in the ...

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Publisher copy:
10.1115/GT2002-30554

Authors


Journal:
American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI
Volume:
3 B
Pages:
1063-1072
Publication date:
2002
DOI:
URN:
uuid:3f453283-c1af-4cbe-90bc-4a5cd1c34ba9
Source identifiers:
328978
Local pid:
pubs:328978
Language:
English

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