Numerical Simulation Study on Cooling Characteristics of a New Type of Film Hole

作     者：GUO Chunhai WANG Bin KANG Zhenya ZHANG Wenwu ZHENG Huilong GUO Chunhai;WANG Bin;KANG Zhenya;ZHANG Wenwu;ZHENG Huilong

作者机构：Ningbo Institute of Materials Technology and EngineeringChinese Academy of SciencesNingbo 315201China Institute of Engineering ThermophysicsChinese Academy of SciencesBeijing 100190China 

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

年 卷 期：2021年第30卷第1期

页      面：210-219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] 0825[工学-航空宇航科学与技术] 

基　　金：supported by Key Deployment Projects of the Chinese Academy of Sciences(ZDRW-CN2019-01) National Defense Basic Scientific Research Program(JCKY2016130B203) National Natural Science Foundation of China(U1609208) 

主　　题：film cooling shaped hole numerical simulation optimal design cooling efficiency 

摘      要：A new type of film cooling hole with micro groove structure is presented in this *** on the finite volume method and the Realizable k-εmodel,the film cooling process of the hole in a flat plate structure is *** surface temperature distribution and film cooling effect of different film cooling holes were *** effects of micro-groove structure on wall attachment and cooling efficiency of jet were *** results show that under the same conditions,the transverse coverage width and overall protective area of the new micro-groove holes are larger than those of the ordinary cylindrical holes and special-shaped *** with ordinary holes,the new micro-groove holes can better form the film covering on the surface and enhance the overall film cooling efficiency of the *** example,when the blowing ratio M=1.5,the effective coverage ratio of micro-groove holes is 1.5 times the dustpan holes and is 8 times the traditional cylindrical *** provides reference data and experience rules for the optimization and selection of advanced cooling structure of high performance aero-gas engine hot-end components.