气冷涡轮叶片综合冷却特性实验研究  

Experimental Investigation on Integrated Cooling Characteristics of Air Cooled Turbine Blade

作　　者：魏景涛 钟博 刘阳鹏 杨卫华[1] WEI Jingtao;ZHONG Bo;LIU Yangpeng;YANG Weihua(College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;R&D Center Dept, AECC Commercial Aircraft Engine Co. , Ltd. , Shanghai 200241, China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航发商用航空发动机有限责任公司设计研发中心,上海200241

出　　处：《重庆理工大学学报（自然科学）》2021年第9期278-286,共9页Journal of Chongqing University of Technology：Natural Science

基　　金：国家自然科学基金项目(51276088)。

摘　　要：为了研究流动参数对气冷涡轮叶片综合冷却效果的影响,在短周期叶栅实验通道中采用红外与热电偶结合的测温技术测量了静止条件下叶片表面的温度分布,详细分析了实验叶栅在主次流流量比为0.04~0.08、叶栅入口雷诺数为65000~160000及主流温度分别为555 K、614 K条件下的叶片综合冷却效果。结果表明:内部换热和外部冷却共同影响了叶片外表面温度分布,在叶顶和前缘处热负荷最大;实验条件下,无论是前缘,还是压力面和吸力面,主次流流量比能带来更好的综合冷却效果,主次流流量比由0.04增加至0.08使叶片表面高温区面积减少明显,为冷却效果带来的增益为49%,叶栅入口雷诺数的增大冷却效果增加较小,雷诺数由65000增加至160000使冷却效果增加4.94%,增大主流入口温度使综合冷却效果略有降低。In order to study the influence of flow parameters on integrated cooling effect of air-cooled turbine blades,the temperature distribution on blade surface at rest was measured by infrared and thermocouple temperature measurement technology in the experimental channel of short period cascade.The integrated cooling effect of experimental cascade was analyzed in detail under the conditions that the primary and secondary flow ratio was in the range of 0.04~0.08,the Reynolds number at inlet of cascade range from 65000 to 160000,and the mainstream temperature was 555K and 614K.The results show that both internal heat transfer and external cooling affect the temperature distribution of the outer surface of blade,and the heat load at the top and front edge of blade was the largest.Under experimental conditions,no matter the front edge,pressure surface and suction surface,increasing the ratio of primary and secondary flow and cascade drop pressure can bring better integrated cooling effect.The increase of the ratio of primary and secondary flow from 0.04 to 0.08 can reduce the area of high temperature area on the blade surface obviously,resulting in a gain of 49%for the cooling effect.The increase of Reynolds number in cascade inlet can increase the cooling effect slightly,and the increase of the Reynolds number from 65000 to 160000 can increase the cooling effect by 4.94%.The increase of inlet mainstream temperature can decrease the comprehensive cooling effect slightly.

关 键 词：航空发动机 涡轮叶片 红外修正 温度分布 综合冷却效果 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]