高温燃气流风洞非稳态运行过程实验和数值模拟研究  

Experimental and Numerical Research on Unsteady Operation Process of High Temperature Gas Flow Wind Tunnel

作　　者：曹知红 费一尘 周越梅[1] 李红亮[1] 田宁[1] CAO Zhi-hong;FEI Yi-chen;ZHOU Yue-mei;Li Hong-liang;TIAN Ning(Beijing Institute of Space Long March Vehicle,Beijing 100076,China)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《推进技术》2022年第7期380-388,共9页Journal of Propulsion Technology

摘　　要：针对热考核用高温燃气流风洞运行过程中的非稳态过程开展研究,采用风洞实验与数值计算相结合的方法研究了风洞整体起动、扩压器背压抬升、关机三种过程中喷管、实验舱和扩压器内瞬态流动特性。通过数值计算能较好地复现上述瞬态现象,借助数值计算能合理地解释试验现象产生的原因,且捕捉到实验中无法观测到的现象,评估得到该风洞扩压器的抗反压裕度在10kPa以上。因此,数值方法是研究大型燃气风洞瞬态流动特性最重要的辅助手段。该研究可为类似风洞运行调试提供借鉴,并为风洞实际运行提供数据支撑。The unsteady operation process of high temperature gas flow wind tunnel for thermal assessment was studied.The transient flow characteristics in the nozzle,the test cabin and the diffuser during the whole wind tunnel starting,the back pressure lifting of the diffuser and the shutdown of the wind tunnel were studied by experiment and numerical calculation.The transient phenomena mentioned above can be reproduced well by numerical calculation,and the causes of the test phenomena can be reasonably explained by numerical calculation,and the phenomenon that cannot be observed in the experiment can be captured.The anti-back pressure margin of the wind tunnel diffuser is estimated to be more than 10kPa.Therefore,the numerical calculation method is crucial auxiliary method to study the transient flow characteristics of large gas wind tunnels.The research provides reference for the operation and debugging of the similar wind tunnel,and provides data support for the actual operation of the wind tunnel.

关 键 词：非稳态运行过程 风洞起动 风洞关机 扩压器 背压 

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]