TRANSONIC TURBINE BLADE TIP AERO-THERMAL PERFORMANCE WITH DIFFERENT TIP GAPS: PART I - TIP HEAT TRANSFER
A closely combined experimental and CFD study on a transonic blade tip aero-thermal performance at engine representative Mach and Reynolds numbers (Mexit=1, Reexit=1.27x106) is presented in this and its companion paper (Part II). The present paper considers surface heat transfer distributions on tip...
| Автори: | , , , , , |
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| Формат: | Conference item |
| Опубліковано: |
2010
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