摘要
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。
Take local structure of low pressure turbine guide vane for an engine as the research object, a combined oblique impact structure form was developed. The design characteristics of combined oblique impact cooling structure were introduced and the flow characteristics and temperature field were calculated and anylzed. The analysis results and wall-temperature test results show that the cooling structure can have better wall cooling effect with less cooling air flow, and has uniform impact cooling effect on the surface of the upper side plate of vane. The performance and reliability of the cooling structure also are validated by the engine bench test.
出处
《航空发动机》
2012年第5期43-46,共4页
Aeroengine
