某涡轮转子叶片新型冷却结构设计及试验验证  

A New Cooling Structure Design of Turbine Blade and Experiment Verification

作　　者：郝旭生 薛树林 李亚雄 孙德芹 杨卫华[3] HAO Xu-sheng;XUE Shu-lin;LI Ya-xiong;SUN De-qin;YANG Wei-hua(Aecc Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Provincial Key Laboratory of Small and Medium sized Aircraft Engine Impeller Machinery,Zhuzhou 412002,China;School of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002 [3]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《山东工业技术》2024年第6期3-8,共6页Journal of Shandong Industrial Technology

基　　金：国家自然科学基金(52304142)。

摘　　要：针对某航空发动机涡轮转子叶片,本文设计了一种新型冷却结构,进行了中温中压条件下冷却效果试验,并与采用成熟冷却结构的叶片冷却效果进行了对比。结果表明:新型冷却结构的平均冷却效果能够满足实际工作状态下叶片冷却设计要求。在流量比0.02至0.046范围内,相同流量比下,其平均冷却效果高于某成熟冷却结构,在发动机设计点状态,其平均冷效较成熟冷却结构提高约10.5%,且各冷却单元尺寸满足铸造和机加工艺要求,设计方案合理可行,本文结果可以为转子叶片冷却结构设计提供参考。A new cooling structure was designed for a turbine blade of an aeroengine.The cooling effect test piece was designed and tested under medium temperature and medium pressure,and the cooling effect was compared with that of the turbine blade with mature cooling structure.The results show that the average cooling effect of the new cooling structure can meet the cooling design requirement of the blade under the actual working condition.In the range of flow ratio from 0.02 to 0.046,the average cooling effect is higher than that of the mature cooling structure under the same flow ratio.At the engine design point,the average cooling effect is about 10.5%higher than the mature cooling structure,and the sizes of various cooling units meet the requirements of casting and machining,the design scheme is reasonable and feasible.The results can provide reference for the design of turbine blade cooling structure.

关 键 词：航空发动机 涡轮转子叶片 冷却结构 冷却效果 试验验证 

分 类 号：TK124[动力工程及工程热物理—工程热物理]