Measurements in the transition region of a turbine blade profile under compressible conditions
The suction surface of a linear transonic turbine cascade was experimentally investigated. The transition region was measured by utilizing hot film anemometry and the cascade was instrumented with an array of Senflex nickel heated hot film sensors. To determine the boundary layer edge Mach number di...
| Main Authors: | , |
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| Format: | Journal article |
| Language: | English |
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2005
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| _version_ | 1797056589094453248 |
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| author | Walsh, E Davies, M |
| author_facet | Walsh, E Davies, M |
| author_sort | Walsh, E |
| collection | OXFORD |
| description | The suction surface of a linear transonic turbine cascade was experimentally investigated. The transition region was measured by utilizing hot film anemometry and the cascade was instrumented with an array of Senflex nickel heated hot film sensors. To determine the boundary layer edge Mach number distribution for the compressible test cases, pressure measurements were obtained in the settling chamber and at a number of locations on the suction surface. The results show that the introduction of correlations to include the effect of Mach number for transition onset, resulted in better agreement with the measurements. |
| first_indexed | 2024-03-06T19:24:43Z |
| format | Journal article |
| id | oxford-uuid:1b4f2361-45c9-4367-87af-012812d00f66 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-06T19:24:43Z |
| publishDate | 2005 |
| record_format | dspace |
| spelling | oxford-uuid:1b4f2361-45c9-4367-87af-012812d00f662022-03-26T10:59:41ZMeasurements in the transition region of a turbine blade profile under compressible conditionsJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:1b4f2361-45c9-4367-87af-012812d00f66EnglishSymplectic Elements at Oxford2005Walsh, EDavies, MThe suction surface of a linear transonic turbine cascade was experimentally investigated. The transition region was measured by utilizing hot film anemometry and the cascade was instrumented with an array of Senflex nickel heated hot film sensors. To determine the boundary layer edge Mach number distribution for the compressible test cases, pressure measurements were obtained in the settling chamber and at a number of locations on the suction surface. The results show that the introduction of correlations to include the effect of Mach number for transition onset, resulted in better agreement with the measurements. |
| spellingShingle | Walsh, E Davies, M Measurements in the transition region of a turbine blade profile under compressible conditions |
| title | Measurements in the transition region of a turbine blade profile under compressible conditions |
| title_full | Measurements in the transition region of a turbine blade profile under compressible conditions |
| title_fullStr | Measurements in the transition region of a turbine blade profile under compressible conditions |
| title_full_unstemmed | Measurements in the transition region of a turbine blade profile under compressible conditions |
| title_short | Measurements in the transition region of a turbine blade profile under compressible conditions |
| title_sort | measurements in the transition region of a turbine blade profile under compressible conditions |
| work_keys_str_mv | AT walshe measurementsinthetransitionregionofaturbinebladeprofileundercompressibleconditions AT daviesm measurementsinthetransitionregionofaturbinebladeprofileundercompressibleconditions |