Journal article
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
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Authors
Bibliographic Details
- Journal:
- American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI
- Volume:
- 3 B
- Pages:
- 1063-1072
- Publication date:
- 2002-01-01
- DOI:
- Source identifiers:
-
328978
Item Description
- Language:
- English
- Pubs id:
-
pubs:328978
- UUID:
-
uuid:3f453283-c1af-4cbe-90bc-4a5cd1c34ba9
- Local pid:
- pubs:328978
- Deposit date:
- 2013-11-16
Terms of use
- Copyright date:
- 2002
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