某发动机喷管构件高温载荷测量
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摘要
T4拉杆是某发动机喷管单元的关键承力部件,高温条件下喷管载荷是否满足要求,是考核喷管单元结构完整性的关键。利用热固耦合有限元方法分析了机械载荷、温度梯度、材料参数对T4拉杆应变的影响规律。利用高温应变计对T4拉杆开展了高温载荷测量台架试验,改进形成了高温应变计粘贴及装机改装工艺流程,推导建立了载荷标定方程扩展方法,建立了包含载荷标定试验、温度修正试验、数据处理方法等在内的高温载荷测量方法。试验表明,不同T4拉杆之间温度—热输出应变变化趋势和数值差异明显;T4拉杆载荷误差最大值为0.27 kN,实测最大拉力为设计载荷的62.1%,最大压力为设计载荷值的58.46%,T4拉杆结构强度设计满足使用需求。
T4 link is the critical load-bearing component for nozzle element of a certain engine. Whether the nozzle load meets the requirements or not at high temperature is the key factor in the structural integrity of the nozzle unit. It's analyzed that strain response of the T4 link was resulted from mechanical load, thermal gradient and material parameter using the thermo-solid coupling method. The T4 link load at high temperature was measured with the high temperature strain gauge on bed test. The process for bonding and assembling the high temperature strain gauge was developed. the equation extension method of the load calibration was deduced, the measurement method containing load calibration, thermal correction, and date processing for the high temperature load were established. The aero-engine bed test shows that the variation tendency and value of the thermal-output strains vary much between T4 links. The maximum error for T4 link is 0.27 kN, the maximum measured tension is 62.1% of the designed load value, the maximum pressure is 58.46% of the designed load value, and the structural strength design of T4 link meets the operating requirements.
T4 link is the critical load-bearing component for nozzle element of a certain engine. Whether the nozzle load meets the requirements or not at high temperature is the key factor in the structural integrity of the nozzle unit. It's analyzed that strain response of the T4 link was resulted from mechanical load, thermal gradient and material parameter using the thermo-solid coupling method. The T4 link load at high temperature was measured with the high temperature strain gauge on bed test. The process for bonding and assembling the high temperature strain gauge was developed. the equation extension method of the load calibration was deduced, the measurement method containing load calibration, thermal correction, and date processing for the high temperature load were established. The aero-engine bed test shows that the variation tendency and value of the thermal-output strains vary much between T4 links. The maximum error for T4 link is 0.27 kN, the maximum measured tension is 62.1% of the designed load value, the maximum pressure is 58.46% of the designed load value, and the structural strength design of T4 link meets the operating requirements.
引文
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[2] 戴军,黄春峰,毛茂华,等.航空发动机高温应变测量技术方法研究[J].测控技术,2014,33(S):123-129.DAI Jun,HUANG ChunFeng,MAO MaoHua,et al.Research on high temperature strain measurement technology of aero-engine[J].Measurement & Control Technology,2014,33(S):123-129 (In Chinese).
[3] 雷晓波,雷蒂远,郝晓乐,等.飞行载荷模式识别方法的研究及应用[J].应用力学学报,2018,35(2):241-247.LEI XiaoBo,LEI DiYuan,HAO XiaoLe,et al.Study and application of flight load pattern recognition methods[J].Chinese Jounal of Applied Mechanics,2018,35(2):241-247 (In Chinese).
[4] 雷晓波,文敏,雷蒂远,等.利用Pearson-Ⅲ分布预测某飞机法向过载极值[J].机械强度,2018,40(1):106-110.LEI XiaoBo,WEN Min,LEI DiYuan,et al.Prediction of aircraft normal overload extreme value based on Pearson-Ⅲ distribution [J].Journal of Mechanical Strength,2018,40(1):106-110 (In Chinese).
[5] Lei Jihfen.High temperature static strain meansurement with an electrical resistance strain gages[R].AIAA-92-5039,1992.
[6] Lei Jihfen.High-Temperature extensometry and PdCr temperature-compensated wire resistance strain gages compared[R].NASA Lewis Research Center,2000:112-121.
[7] Piazza Anthony.High-temperature sensor applications for ground testing of C-17 engine[R].NASA Dryden Flight Research Center,2007:56-62.
[8] Anthony Piazza,Lpance W Richards,Larry Hudson.High-temperature strain sensing for aerospace application[C].Summer WRSGC,2008:209-218.
[9] 吴东,陈德江,周玮,等.高热环境下前缘结构高温应变测量[J].实验流体力学,2016,30(3):92-97.WU Dong,CHEN DeJiang,ZHOU Wei,et al.High temperature strain measurement of the front edgestructure in high thermal environment[J].Journal of Experiments in Fluid Mechanics,2016,30(3):92-97 (In Chinese).
[10] 张佳明,王文瑞,聂帅.高温电阻应变片特性参数标定实验研究[J].中国测试,2014,40(5):25-28.ZHANG JiaMing,WANG WenRui,NIE Shuai.Research and calibration experiment of characteristic parameters of high temperature resistance strain gauges[J].China Measurement & Test,2014,40(5):25-28(In Chinese).
[11] 王文瑞,张佳明,聂帅.高温应变接触式测量精度影响因素研究[J].固体火箭技术,2015,38(3):439-444.ZHANG JiaMing,WANG WenRui,ZHANG JiaMing,NIE Shuai.Simulation and experiment on influence factor of contact high temperature strain measurement accuracy[J].Journal of Solid Rocket Technology,2015,38(3):439-444 (In Chinese).
[12] 罗金玲,周丹,康宏琳,等.典型气动问题试验方法研究的综述[J].空气动力学学报,2014,32(5):600-609.LUO JinLing,ZHOU Dan,KANG HongLin,et al.Summarization of experimental methods associated with typical aerodynamic issues[J].Acta Aerodynamic Ainica,2014,32(5):600-609 (In Chinese).
[13] 尹福炎.瞬态加热条件下高温应变计测量误差的修正方法[J].强度与环境,2005,32(1):37-41.YIN FuYan.Correction technique for high temperature strain gauge under transient heating conditions[R].Structure Environment Engineering,2005,32(1):37-41 (In Chinese).
[14] 李丽霞,蒋军亮,郝庆瑞,等.某种高温合金550℃高温应变测试[J].应用力学学报,2015,32(3):378-383.LI LiXia,JIANG JunLiang,HAO QingRui,et al.Thermal strain test of high temperature alloy at 550℃[J].Chinese Jounal of Applied Mechanics,2015,32(3):378-383 (In Chinese).
[15] 雷晓波,李密,张强,等.航空发动机推力直接测量飞行试验[J].航空动力学报,2018,33(7):1613-1638.LEI XiaoBo,LI Mi,ZHANG Qiang,et al.Direct thrust measurement flight test of aero-engine[J].Journal of Aerospace Power,2018,33(7):1631-1638 (In Chinese).
[16] 雷晓波,张强,文敏,等.航空发动机安装节推力测量技术与试验研究[J].航空学报,2017,38(12):121190-1-8.LEI XiaoBo,ZHANG Qiang,Wen Min,et al.Study of mount thrust measurement technique and tests of aero-engine[J].Acta Aeronautica et Astronautica Sinica,2017,38(12):121190-1-8 (In Chinese).
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