低速风洞进气道试验柱形分布式引射器优化设计  

Design and optimization of columniform distributed ejector for low speed wind tunnel inlet test

作　　者：巫朝君[1] 徐彬彬 张为卓[1] 汤伟[1] 李圆[1] WU Chaojun;XU Binbin;ZHANG Weizuo;TANG Wei;LI Yuan(Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心低速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2020年第12期2482-2488,共7页Journal of Aerospace Power

摘　　要：为适应低速风洞发动机进气道试验的大流量模拟的迫切需要,介绍了适用于4 m量级低速风洞的柱形分布式引射器的设计方案。通过ANSYS-CFX软件采用有限体积法对引射器内流场进行了数值模拟,重点优化了引射器的引射面积比、离散的喷嘴分布方式和喷嘴出口设计点总压、马赫数等参数。综合考虑引射器在风洞中的使用条件限制和吸入流量技术指标要求,完成了引射器设计。优化后的引射器方案解决了小体积、大吸入流量需求之间的矛盾。在FL-14风洞的验证试验表明,优化后引射器的最大吸入流量达到9.07 kg/s,满足4 m量级低速风洞进气道试验大流量模拟需求。In order to meet the urgent requirement of large flow simulation in low speed wind tunnel for engine inlet test,a design scheme of columniform distributed ejector for 4 m-scale low speed wind tunnel was proposed.The internal flow filed of ejector was simulated by ANSYS-CFX software using the finite volume method.The design parameters were optimized,including the ejecting area rate,discrete distribution of nozzles and the design point total pressure and Mach numbers of nozzle outlet.The improved design of ejector met the limited condition in wind tunnel and the acquirement of large mass flow,and solved the contradiction of small size and large mass flow.The experiment in FL-14 wind tunnel indicated that the max absorbing mass flow rate of improved ejector can reach 9.07 kg/s,fulfilling the large mass flow needs of inlet test in 4 m-scale low speed wind tunnel.

关 键 词：进气道 流量模拟 风洞试验 引射器 优化设计 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]