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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 shroudless 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 Q...

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Publisher copy:
10.1115/1.1575253

Authors


Journal:
Journal of Turbomachinery
Volume:
125
Issue:
3
Pages:
513-520
Publication date:
2003-07-05
DOI:
ISSN:
0889-504X
URN:
uuid:6990e07f-1eb5-446a-8195-850bd39b9f92
Source identifiers:
328976
Local pid:
pubs:328976
Language:
English

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