Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer
A closely combined experimental and computational fluid dynamics (CFD) study on a transonic blade tip aerothermal performance at engine representative Mach and Reynolds numbers (Mexit=1,Reexit=1.27×106) is presented here and its companion paper (Part II). The present paper considers surface heat-tra...
| Main Authors: | , , , , |
|---|---|
| Format: | Journal article |
| Language: | English |
| Published: |
2011
|
| _version_ | 1826262332869705728 |
|---|---|
| author | Zhang, Q O'Dowd, DO He, L Oldfield, M Ligrani, P |
| author_facet | Zhang, Q O'Dowd, DO He, L Oldfield, M Ligrani, P |
| author_sort | Zhang, Q |
| collection | OXFORD |
| description | A closely combined experimental and computational fluid dynamics (CFD) study on a transonic blade tip aerothermal performance at engine representative Mach and Reynolds numbers (Mexit=1,Reexit=1.27×106) is presented here and its companion paper (Part II). The present paper considers surface heat-transfer distributions on tip surfaces and on suction and pressure-side surfaces (near-tip region). Spatially resolved surface heat-transfer data are measured using infrared thermography and transient techniques within the Oxford University high speed linear cascade research facility. The Rolls-Royce PLC HYDRA suite is employed for numerical predictions for the same tip configuration and flow conditions. The CFD results are generally in good agreement with experimental data and show that the flow over a large portion of the blade tip is supersonic for all three tip gaps investigated. Mach numbers within the tip gap become lower as the tip gap decreases. For the flow regions near the leading edge of the tip gap, surface Nusselt numbers decrease as the tip gap decreases. Opposite trends are observed for the trailing edge region. Several "hot spot" features on blade tip surfaces are attributed to enhanced turbulence thermal diffusion in local regions. Other surface heat-transfer variations are attributed to flow variations induced by shock waves. Flow structure and surface heat-transfer variations are also investigated numerically when a moving casing is present. The inclusion of moving casing leads to notable changes to flow structural characteristics and associated surface heat-transfer variations. However, significant portions of the tip leakage flow remain transonic with clearly identifiable shock wave structures. © 2011 American Society of Mechanical Engineers. |
| first_indexed | 2024-03-06T19:34:46Z |
| format | Journal article |
| id | oxford-uuid:1ea8d734-37d2-4293-bcdb-23b6e7f03e34 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-06T19:34:46Z |
| publishDate | 2011 |
| record_format | dspace |
| spelling | oxford-uuid:1ea8d734-37d2-4293-bcdb-23b6e7f03e342022-03-26T11:17:38ZTransonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat TransferJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:1ea8d734-37d2-4293-bcdb-23b6e7f03e34EnglishSymplectic Elements at Oxford2011Zhang, QO'Dowd, DOHe, LOldfield, MLigrani, PA closely combined experimental and computational fluid dynamics (CFD) study on a transonic blade tip aerothermal performance at engine representative Mach and Reynolds numbers (Mexit=1,Reexit=1.27×106) is presented here and its companion paper (Part II). The present paper considers surface heat-transfer distributions on tip surfaces and on suction and pressure-side surfaces (near-tip region). Spatially resolved surface heat-transfer data are measured using infrared thermography and transient techniques within the Oxford University high speed linear cascade research facility. The Rolls-Royce PLC HYDRA suite is employed for numerical predictions for the same tip configuration and flow conditions. The CFD results are generally in good agreement with experimental data and show that the flow over a large portion of the blade tip is supersonic for all three tip gaps investigated. Mach numbers within the tip gap become lower as the tip gap decreases. For the flow regions near the leading edge of the tip gap, surface Nusselt numbers decrease as the tip gap decreases. Opposite trends are observed for the trailing edge region. Several "hot spot" features on blade tip surfaces are attributed to enhanced turbulence thermal diffusion in local regions. Other surface heat-transfer variations are attributed to flow variations induced by shock waves. Flow structure and surface heat-transfer variations are also investigated numerically when a moving casing is present. The inclusion of moving casing leads to notable changes to flow structural characteristics and associated surface heat-transfer variations. However, significant portions of the tip leakage flow remain transonic with clearly identifiable shock wave structures. © 2011 American Society of Mechanical Engineers. |
| spellingShingle | Zhang, Q O'Dowd, DO He, L Oldfield, M Ligrani, P Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title | Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title_full | Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title_fullStr | Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title_full_unstemmed | Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title_short | Transonic Turbine Blade Tip Aerothermal Performance With Different Tip Gaps-Part I: Tip Heat Transfer |
| title_sort | transonic turbine blade tip aerothermal performance with different tip gaps part i tip heat transfer |
| work_keys_str_mv | AT zhangq transonicturbinebladetipaerothermalperformancewithdifferenttipgapspartitipheattransfer AT odowddo transonicturbinebladetipaerothermalperformancewithdifferenttipgapspartitipheattransfer AT hel transonicturbinebladetipaerothermalperformancewithdifferenttipgapspartitipheattransfer AT oldfieldm transonicturbinebladetipaerothermalperformancewithdifferenttipgapspartitipheattransfer AT ligranip transonicturbinebladetipaerothermalperformancewithdifferenttipgapspartitipheattransfer |