涡扇动力模拟短舱反推力校准试验技术

为满足大飞机的反推力风洞试验需求,中国空气动力研究与发展中心发展了涡扇动力模拟短舱反推力校准试验技术。在FL-12风洞建立了反推力校准试验平台,利用推力天平测量反推力短舱实际推力,通过空气桥减少高压供气管路对天平测量影响,通过安装在短舱进口和喷口之间的隔板解决短舱进排气对风洞气流的诱导及反向喷流被短舱重新吸入的问题。发展了反推力校准试验方法和试验数据修正方法。为验证反推力校准试验技术可靠性,分别在FL-12风洞和FL-13风洞开展了某型号反推力校准试验和全机反推力风洞试验,试验结果表明:随排气压比增大,反推力短舱流量和速度的计算值与标定值之间的差异逐渐减小；校准试验精度优于0.5%,满足反推力风洞试验对校准试验的精度要求。 

Reverse thrust calibration test technology of turbofan nacelle simulator

To meet the demand of reverse thrust wind tunnel tests for large aircraft, a kind of reverse thrust calibration test technology of turbofan nacelle simulator was developed in China Aerodynamics Research and Development Center. The reverse thrust calibration test platform was constructed in FL-12 low speed wind tunnel. Thrust of the nacelle was measured by the thrust balance. Air-line bridges were used to reduce the impact of air-line tube on the balance. In order to eliminate effects of induction of inlet and exhaust flow of the nacelle on wind tunnel flow and prevent the potentially dangerous re-ingestion of reverse exhaust flow, the wind tunnel test section was blocked by a plate between the inlet and outlet of the nacelle. A reverse thrust calibration test method and a test result correcting method were developed. In ordered to verify reliability of the reverse thrust calibration test technology, a reverse thrust calibration test of a turbine simulator nacelle and a full model reverse thrust wind tunnel test were conducted in FL-12 and FL-13 low speed wind tunnel respectively. The test results indicated that, with the increase of nozzle pressure ratio, the differences between calculation and calibration of mass flow and velocity of the reverse thrust nacelle decreased gradually; the calibration test accuracy was better than 0.5%, which can meet the accuracy need of reverse thrust wind tunnel test.