基于校准箱的低速风洞一体式喷流试验技术  

Integrated jet-effects testing technique based on calibration tank in low-speed wind tunnel

作　　者：胡卜元[1] 巫朝君[1] 吴福章[1] 章荣平[1] 刘忠华[1] HU Buyuan;WU Chaojun;WU Fuzhang;ZHANG Rongping;LIU Zhonghua(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》2021年第6期1137-1144,共8页Journal of Aerospace Power

摘　　要：为满足大型涡扇动力飞机的喷流试验需求,发展了基于校准箱的低速风洞一体式喷流试验技术。该技术的原理是将试验模型与喷流模拟器融合为一体进行喷流试验,风洞天平同时测量模型的气动力和喷流模拟器的推力,推力通过校准箱校准后从风洞天平测量试验数据中扣除。详细介绍了推力校准及扣除技术、空气桥技术、流量、落压比精确控制技术。为验证该试验技术可靠性,分别在校准箱和FL-13风洞开展了某飞机推力校准试验和全机喷流风洞试验,试验结果表明:推力校准精度优于0.24%,全机喷流试验的阻力系数重复性精度达到0.000 3,满足喷流风洞试验的精度要求。To meet the demand of jet-effects test of large turbine fan aircraft, a kind of integrated jet-effects testing technique based on calibration tank was developed. The testing model and jet simulators were integrated according to the principle of the technique. Aerodynamic forces and thrust were both measured by wind tunnel balance. Thrust was calibrated in calibration tank and deducted from the testing data measured by wind tunnel balance. Techniques such as thrust calibration and deduction, air bridge, mass flow rate and nozzle pressure ratio controlling were introduced. In order to verify the reliability of integrated jet-effects testing technique, a thrust calibration test and a full model jet-effects wind tunnel test were conducted in the calibration tank and FL-13 low speed wind tunnel respectively. The test results indicated that, the calibration testing accuracy of thrust was better than 0.24%, and the repeatability testing accuracy of drag coefficient was 0.000 3, which can meet the accuracy need of jet-effects wind tunnel test.

关 键 词：喷流影响 一体式试验技术 校准箱 空气桥 流量、落压比控制 

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]