突片作用下气膜冷却对流传热特性的试验研究

Experimental study on convective heat transfer characteristics of film cooling with tab

College of Energy and Power Engineering, Nanjing University of Astonautics and Aeronautics, Nanjing 210016, China

摘要: 为了研究突片对气膜冷却的影响规律,设计了3种不同堵塞比的等边三角形突片,并对其对气膜冷却特性的影响规律进行了实验研究。研究结果表明,与无突片的气膜冷却相比,突片的存在提高了对流换热系数,在吹风比0.5⁰.78时,堵塞比为0.1时气膜冷却对流传热系数最高;当吹风比为1.22¹.5时,堵塞比为0.27时气膜冷却对流传热系数最高。但突片的存在也增大了气流在气膜孔中的流动阻力。
- 航空、航天推进系统 /
- 突片 /
- 对流传热 /
- 气膜冷却
Abstract: In order to study the effect of tab on film cooling,three kinds of test pieces with different geometrical parameters were designed,and the heat transfer characteristics of them were experimentally studied.The results show that the convective heat transfer coefficient of film cooling with tab is better than that without the tab.While the area ratio is 0.1,the convective heat transfer coefficient of film cooling is the best at the blow ratio of 0.5⁰.78;while the area ratio is 0.27,the convective heat transfer coefficient gets its maximum value at the blow ratio of 1.22¹.5.However,because of the existence of tabs,the flow friction loss in the film hole will be increased.
- aerospace propulsion system /
- tab /
- convective heat transfer /
- film cooling

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