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�������պ����ѧѧ�� 2011, Vol. 37 Issue (11) :1404-1409    DOI:
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������, �˺���, ����, �콣��*
�������պ����ѧ ���շ��������������ص�ʵ����, ���� 100191
Experiments of combined heat transfer in leading of blades at rotating state
Gu Zhenpeng, Deng Hongwu, Tao Zhi, Zhu Jianqin*
National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

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Abstract�� Transient experiment was performed to study the heat transfer characteristic of impingement cooling with outflow film in the leading of turbine blades at rotating state. And, the effect of Coriolis forces and centrifugal forces on combined heat transfer effectiveness was discussed. The Reynolds number based on the inlet velocity of the impinging jet and hole diameter is 4 000. The Rotation number is from 0 to 0.139. Experiments' results show that the heat transfer effectiveness decreases with the Rotation number increasing. The average Nusselt number on the impingement face decreases 33%, and the average Nusselt number on the pressure face and the suction face decreases 20.5% and 7.5%, respectively. The effect of Coriolis forces enhance the spreading rate of the jet flow, which is mostly factor that result in heat transfer characteristic down. The effect of Coriolis forces together with centrifugal forces arouses the difference of heat transfer on pressure face and suction face at rotating state, and the average Nusselt number on the suction surface was larger than that on the pressure surface. The presence of the film holes changes the flow structure and gathers head the heat transfer effectiveness of films'border area.
Keywords�� impinging   film   heat transfer   transient experiment     
Received 2010-07-06;
About author: ������(1985-),��,�ӱ�������,˶ʿ��,0123abcd88@sina.com.
������, �˺���, ����, �콣��.��ת״̬��ҶƬǰԵ���ϻ���ʵ��[J]  �������պ����ѧѧ��, 2011,V37(11): 1404-1409
Gu Zhenpeng, Deng Hongwu, Tao Zhi, Zhu Jianqin.Experiments of combined heat transfer in leading of blades at rotating state[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(11): 1404-1409
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