TRANSONIC TURBINE BLADE TIP AERO-THERMAL PERFORMANCE WITH DIFFERENT TIP GAPS: PART I - TIP HEAT TRANSFER

TRANSONIC TURBINE BLADE TIP AERO-THERMAL PERFORMANCE WITH DIFFERENT TIP GAPS: PART I - TIP HEAT TRANSFER

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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...

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Библиографические подробности
Главные авторы:	Zhang, Q, O'Dowd, DO, He, L, Oldfield, M, Ligrani, P, ASME
Формат:	Conference item
Опубликовано:	2010

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