Research on Cooling Effectiveness in Stepped Slot Film Cooling Vane

作     者：LI Yulong WU Hong ZHOU Feng RONG Chengjun 

作者机构：National Key Laboratory of Science and Technology on Aero-Engine Aero-ThermodynamicsBeihang University 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2016年第25卷第3期

页      面：273-279页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 

基　　金：supported by funds form National natural science foundation of China(Grant No.50976008) 

主　　题：Film cooling Cooling effectiveness Blowing ratio Pressure loss 

摘      要：As one of the most important developments in air cooling technology for hot parts of the aero-engine, film cool- ing technology has been widely used. Film cooling hole structure exists mainly in areas that have high temperature, uneven cooling effectiveness issues when in actual use. The first stage turbine vanes of the aero-engine consume the largest portion of cooling air, thereby the research on reducing the amount of cooling air has the greatest potential. A new stopped slot film cooling vane with a high cooling effectiveness and a high cooling uniformity was researched initially. Through numerical methods, the affecting factors of the cooling effectiveness of a vane with the stepped slot film cooling structure were researched. This paper focuses on the cooling effectiveness and the pressure loss in different blowing ratio conditions, then the most reasonable and scientific structure parameter can be obtained by analyzing the results. The results show that 1.0 mm is the optimum slot width and 10.0 is the most reasonable blowing ratio. Under this condition, the vane achieved the best cooling result and the highest cooling effectiveness, and also retained a low pressure loss.