变密度平面叶栅风洞的设计与实现  

Design and actualization of the variable density plane cascade wind tunnel

作　　者：魏巍 马护生 周晓刚[2] 吴军强[3] 彭强[4] 任泽斌[4] WEI Wei;MA Husheng;ZHOU Xiaogang;WU Junqiang;PENG Qiang;REN Zebin(Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;High Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所,绵阳621000 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000 [3]中国空气动力研究与发展中心,绵阳621000 [4]中国空气动力研究与发展中心设备设计与测试技术研究所,绵阳621000

出　　处：《实验流体力学》2022年第5期24-33,共10页Journal of Experiments in Fluid Mechanics

摘　　要：为满足先进涡扇发动机对变雷诺数平面叶栅试验的需求,设计了亚/跨/超声速来流高效变换、雷诺数和马赫数独立调节、压气机和涡轮平面叶栅试验为一体、换热与冷却试验能力兼具的变密度平面叶栅风洞,提出了风洞的总体设计方案。文章详细介绍了风洞引射器、半柔壁喷管及试验舱等部件设计问题,分析了流场调试及典型叶栅试验结果。调试结果表明:采用的部件设计技术实现了变密度平面叶栅风洞的主要功能,试验雷诺数可低至3.1×105 m_(–1),具备开展低雷诺数平面叶栅试验的能力。风洞流场调试结果满足《低速风洞和高速风洞流场品质要求》(GJB 1179A—2012),为研究亚/跨/超声速压气机和涡轮叶栅低雷诺数流动问题提供了重要试验平台。In order to meet the need of the variable Reynolds number plane cascade tests for the advanced turbofan engine,the variable density plane cascade wind tunnel was designed to change the subsonic,transonic and supersonic flow efficiently,adjust the Mach number(Ma)and Reynolds number(Re)independently,combine the compressor and turbine cascade tests and possess the ability of heat transfer or cooling experiments.The general design project of the wind tunnel was put forward,and the ejector,the flexible nozzle as well as the test chamber design problems were introduced in details.The results of the flow field debugging and the typical cascade tests were analysed.The research reveals that the design technologies of the components satisfy the main functions of the variable density plane cascade wind tunnel.The Reynolds number can be as low as 3.1×105 m–1 so that the low Reynolds number experiments can be made easyly with the facility.The flow field debugging results satisfy the National military standard GJB 1179A—2012 of the specification for flow quality of high and low speed wind tunnels.It provides a key test platform for the study of the transonic,supersonic Mach number and low Reynolds number flow problems of the compressor and turbine cascades.

关 键 词：平面叶栅 风洞 叶轮机 雷诺数 马赫数 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]