- 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...
Expand abstract - Publisher copy:
- 10.1115/1.1575253
-
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- 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
- Copyright date:
- 2003
Journal article
An investigation on turbine tip and shroud heat transfer
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