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以某型航空发动机低压涡轮导向叶片局部结构设计为研究对象,研发了1种复合倾斜冲击冷却的结构形式,介绍了复合倾斜角度冲击冷却结构设计特点,并进行了流动特性和温度场的计算分析,计算分析和壁温测试表明:复合倾斜冲击冷却方式能以较小的冷气流量对壁面形成了较好的冷却效果;对叶片上缘板表面形成了均匀冲击冷却的效果,发动机台架试车也验证了该冷却结构的性能和可靠性。
Based on the partial structure design of aeroengine low-pressure turbine guide vane, a composite inclined impact cooling structure was developed. The design features of compound inclined-angle impingement cooling structure were introduced. The flow characteristics and temperature field calculation were analyzed The results of calculation and wall temperature test show that the composite inclined impact cooling method can form a better cooling effect on the wall surface with a smaller flow of cold air and a uniform impact cooling effect on the surface of the upper edge of the blade. The performance and reliability of the cooling structure were verified.