An investigation on turbine tip and shroud heat transfer
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 pres...
| Main Authors: | , |
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| Format: | Journal article |
| Language: | English |
| Published: |
2002
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| _version_ | 1797064445332029440 |
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| author | Chana, K Jones, T |
| author_facet | Chana, K Jones, T |
| author_sort | Chana, K |
| collection | OXFORD |
| description | 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 QinetiQ Isentropic Light Piston Facility and aerodynamic and heat transfer measurements are presented from the rotor tip and casing region. A simple two-dimensional model is presented to estimate the heat transfer rate to the rotor tip and casing region as a function of Reynolds number along the gap. |
| first_indexed | 2024-03-06T21:14:24Z |
| format | Journal article |
| id | oxford-uuid:3f453283-c1af-4cbe-90bc-4a5cd1c34ba9 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-06T21:14:24Z |
| publishDate | 2002 |
| record_format | dspace |
| spelling | oxford-uuid:3f453283-c1af-4cbe-90bc-4a5cd1c34ba92022-03-26T14:31:01ZAn investigation on turbine tip and shroud heat transferJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:3f453283-c1af-4cbe-90bc-4a5cd1c34ba9EnglishSymplectic Elements at Oxford2002Chana, KJones, TDetailed 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 QinetiQ Isentropic Light Piston Facility and aerodynamic and heat transfer measurements are presented from the rotor tip and casing region. A simple two-dimensional model is presented to estimate the heat transfer rate to the rotor tip and casing region as a function of Reynolds number along the gap. |
| spellingShingle | Chana, K Jones, T An investigation on turbine tip and shroud heat transfer |
| title | An investigation on turbine tip and shroud heat transfer |
| title_full | An investigation on turbine tip and shroud heat transfer |
| title_fullStr | An investigation on turbine tip and shroud heat transfer |
| title_full_unstemmed | An investigation on turbine tip and shroud heat transfer |
| title_short | An investigation on turbine tip and shroud heat transfer |
| title_sort | investigation on turbine tip and shroud heat transfer |
| work_keys_str_mv | AT chanak aninvestigationonturbinetipandshroudheattransfer AT jonest aninvestigationonturbinetipandshroudheattransfer AT chanak investigationonturbinetipandshroudheattransfer AT jonest investigationonturbinetipandshroudheattransfer |