一种低速风洞大流量进气道试验系统研制  

Development of a Large Mass Flow Inlet Test System in Low Speed Wind Tunnel

作　　者：唐滨滨 李长坤[1] TANG Bin-bin;LI Chang-kun(The 3rd Aerodynamic Research and Test Department,AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院气动研究与试验三部,黑龙江哈尔滨150001

出　　处：《推进技术》2018年第12期2839-2844,共6页Journal of Propulsion Technology

摘　　要：为了提高FL-8风洞进气道试验能力,结合该风洞特点,在不破坏原有进气道试验系统前提下,研制了一路大流量进气道试验系统,采用直线形式布置在风洞中心,引射混合气体扩压减速后排入风洞扩散段内。该系统可实现进气道流场模拟、性能测量、流量控制与测量。为了验证该系统性能,在FL-8风洞进行试验验证了引射器的引射能力,排气对风洞流场的影响以及流量的控制与测量精度。该系统测量精度高,流量测量精度达到0.3%以上引射能力强,排气对风洞流场影响小,可模拟单路流量2.8kg/s,较原FL-8进气道试验能力提高50%以上,并且与原FL-8进气道试验系统结合使用,可实现三路进气道同时模拟。A large mass flow inlet test system was developed in the FL-8 wind tunnel to improve its test ability. According to the condition,the system was set in the center of the wind tunnel and ejected mixed air into the diffusion section without destroying the original one. The system can perform all kinds of inlet test functions including inlet flow field simulation,performance measurement,flow control and measurement. In order to verify the performance of the system,a test was carried out. Results show that the system has high measurement accuracy,ejection ability and exhaust air has little influence on the wind tunnel flow field. The flow measurement accuracy achieve 0.3% and the inlet test system achieves maximum 2.8kg/s,which leads to a 50% capacity increase and can carry out three inlet test simultaneously.

关 键 词：进气道 风洞试验 大流量 引射 性能测量 

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] V211.753