密集型气膜出流内部冷气侧换热特性实验研究
The Interior Heat Transfer Characteristics of Gas Turbine Blade Due to Sparse Film Cooling Holes
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摘要: 航空发动机涡轮叶片前缘大多采用密集型气膜冷却技术。针对这种复合冷却方式中密集型气膜出流的无冲击冷却内部换热特性进行了大量实验研究,得出了气膜出流与来流密流比、来流雷诺数以及出流开孔面积比对换热特性的影响,并在实验参数范围内整理出了换热准则关系式。其结果及准则关系式对叶片的结构设计具有直接的指导意义。Abstract: The film cooling technique is one of the useful cooling methods.At present,the sparse film cooling technique is alaiays employed for the midchord region of gas turbine blade in aeroengine,and the impingement cooling technique is also used at the same time.So the interior heat transfer characteristics about an inner side of blade due to sparse film cooling holes have become a very complicated and interesting problem.In this paper,the heat transfer characteristics have been investigated experimentally whether there is impingement cooling fluid or not.Through lots of experimental data,the effect of flow parameters and geometric parameters on heat transfer characteristics has been studied.Besides that,the correlation equation for the interior heat transfer characteristics to the parameters is finally formulated,and the comparison shows that the correlation results are in good agreement with the experimental data.
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Key words:
- aerospace propulsion system /
- film cooling /
- heat transfer /
- turbine blade /
- aircraft engine /
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