Φ1.2m高超声速风洞引射系统设计与性能试验  

Ejector system design and performance test of Φ1.2m hypersonic wind tunnel

作　　者：马利川[1] 王铁进[1] 崔春[1] 黄景博[1] 孙勇堂[1] 黄炳修[1] 石运军 MA Lichuan;WANG Tiejin;CUI Chun;HUANG Jingbo;SUN Yongtang;HUANG Bingxiu;SHI Yunjun(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2022年第5期1-7,共7页Journal of Experiments in Fluid Mechanics

摘　　要：针对大型高超声速风洞总增压比高、抽吸范围宽、多级参数匹配等要求,开展了Φ1.2 m高超声速风洞多级引射器系统设计计算与抽吸试验研究。通过对无风洞主气流时第一、二、三级引射器的单级性能调试和多级组合性能调试,获得了三级多喷管中心引射器不同工作参数组合的抽吸性能,试验段静压最低达660 Pa。据此,总结得到了多级引射器高效运行的参数匹配原则。有风洞主气流时的引射系数试验结果与理论计算结果吻合较好,验证了多级多喷管引射器气动设计方法的可行性。设计结果可靠,可为高超声速风洞或其他地面气动试验设备的多级引射器系统设计与运行提供技术参考。Aiming at the problems such as high pressurization ratio,wide suction range and multi-stage parameter matching in large hypersonic wind tunnel,this paper carried out the design calculation and suction test of the multi-stage ejector system in Φ1.2 m hypersonic wind tunnel.Through single stage performance debugging and multistage combination performance debugging of the first,second and third stage ejector without wind tunnel main flow,the suction performance of three stage multi nozzle central ejector with different working parameters is obtained.The minimum static pressure in the test section is 660 Pa without the main flow.And the parameter matching principle of efficient operation of the multi-stage ejector is analyzed and summarized.The test results of the ejector coefficient with the main airflow in the wind tunnel are in good agreement with the theoretical calculation values,which verifies the feasibility of the aerodynamic design method for the multistage multi-nozzle ejector.The design results are reliable,which can provide technical reference for the design of the multistage ejector system in the hypersonic wind tunnel or other ground aerodynamic test equipment.

关 键 词：高超声速风洞 多级引射器 多喷管 性能试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]