民用航空涡轮发动机短舱高速风洞试验
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摘要
为了获取三种不同型面的民用航空涡轮发动机短舱气动特性,开展了高速风洞试验与数值仿真研究,获取了短舱的压力分布及内流特性,并对比分析了风洞试验数据与仿真结果。结果表明:随着流量系数减小及攻角增加,短舱上唇口外流出现分离;随着流量系数增大,短舱内流下侧出现分离;采用的CFD方法在无分离情况下静压分布与试验结果吻合,但随着流量系数的减小,CFD结果先于试验出现了气流分离。
Research of three different civil aviation turbine engine nacelle profiles by high speed wind tunnel test and numerical simulation method was finished,and the static pressure distribution and induct performance of nacelle were obtained.By comparing the result of wind tunnel test with the numerical simulation,it showed that nacelle upside cowl would have separation when the mass flow rates reduced or the attack angle increased;the induct of downside would have separation when the mass flow rates increased;the numerical simulation result of static pressure distribution coincided with the wind tunnel result when there was no separation,but when mass flow rate reduced,the CFD results were separated before the test.
Research of three different civil aviation turbine engine nacelle profiles by high speed wind tunnel test and numerical simulation method was finished,and the static pressure distribution and induct performance of nacelle were obtained.By comparing the result of wind tunnel test with the numerical simulation,it showed that nacelle upside cowl would have separation when the mass flow rates reduced or the attack angle increased;the induct of downside would have separation when the mass flow rates increased;the numerical simulation result of static pressure distribution coincided with the wind tunnel result when there was no separation,but when mass flow rate reduced,the CFD results were separated before the test.
引文
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[13]刘凯礼,谭兆光,杨士普,等.民用飞机大涵道比发动机短舱的阻力特性分析[C]∥中国力学大会2013论文集.北京:中国力学学会,2013:297-303.
[14]刘凯礼,孙一峰,钟园,等.民用飞机进气道的侧风畸变研究[J].航空动力学报,2015,32(2):289-296.LIU Kaili,SUN Yifeng,ZHONG Yuan,et al.Study on cross-wind distortion of civil aircraft inlet[J].Journal of Aerospace Power,2015,32(2):289-296.(in Chinese)
[15]姬昌睿,刘凯礼,张鹏飞,等.外物损伤对民用飞机短舱内/外流气动特性的影[J].航空学报,2015,36(3):772-781.JI Changrui,LIU Kaili,ZHANG Pengfei,et al.Influence of external object damage on inflow/outflow aerodynamic characteristics of civil aircraft nacelle[J].Acta Aeronautica et Astronautica Sinica,2015,36(3):772-781.(in Chinese)
[16]闫海津,杜玺,谭廉华.发动机短舱侧风工况数值模拟与分析[C]∥第七届中国航空学会青年科技论坛文集.北京:中国科学技术出版社,2016:522-526.
[17]刘浩,李博,王成,等.滑跑条件下短舱进气道地面涡数值仿真[J].航空动力学报,2018,33(7):1657-1664.LIU Hao,LI Bo,WANG Cheng,et al.Ground vortices numerical simulation of nacelle inlet at cross-wind conditions[J].Journal of Aerospace Power,2018,33(7):1657-1664.(in Chinese)
[18]陈晶晶,吴亚东,田杰,等.侧风条件下进气道流场及地面吸入涡特征研究[J].航空动力学报,2019,34(1):228-237.CHEN Jingjing,WU Yadong,TIAN Jie,et al.Research on the inlet flow field and ground vortex under crosswind condition[J].Journal of Aerospace Power,2019,34(1):228-237.(in Chinese)
[2]SEDDON J,GOLDSMITH E L.Intake aerodynamics[M].Reston,VA:AIAA Education Series,1999.
[3]HODDER B K.An investigation of engine influence on inlet performance[R].NASA CR-166136,1981.
[4]MOTYCKA D,WELLING S,LEWIS-SMITH F.Comparison of model and full scale inlet distortions for subsonic commercial transport inlets[R].San Diego,CA:Aircraft Design Systems and Operations Meeting,1984.
[5]MOTYCKA D L.Reynolds number and fan/inlet coupling effects on subsonic transport inlet distortion[J].Journal of Propulsion and Power,2015,1(3):229-234.
[6]LARKIN M J,SCHWIEGER P S.Ultra-high bypass nacelle aerodynamics-inlet f1ow-through high angle of attack distortion test[R].NASA CR-189149,1992.
[7]SHMILOVICH H,ARVIN M.Calculation of transonic flows with separation past arbitrary inlets at incidence[J].AIAA Journal,1990,28(4):601-609.
[8]CHOU D C,HWANG D P,SALARI K,et al.Boundary layer transition effects on flow separation around V/STOL engine inlets at high,incidence[R].Reno,Nevada:22th Aerospace Sciences Meeting,1984.
[9]CHOU D C,LUIDENS R W,STOCKMAN N O.Prediction of boundary-layer flow separation in V/STOL engine inlets[J].Journal of Aircraft,1978,15(8):474-481.
[10]CHOU D C,BAEK J H,LUIDEN R W,et al.Scale effects on turbulent boundary layer development and flow separation around V/STOL inlets at high incidence[R].St.Louis,MO:19th Aerospace Sciences Meeting,1981.
[11]张兆,陶洋,黄国川.发动机短舱溢流阻力的数值拟研究[J].航空学报,2011,32(3):547-553.ZHANG Zhao,TAO Yang,HUANG Guochuan.Numerical simulation research of spillage drag of engine nacelle[J].Acta Aeronautica et Astronautica Sinica,2011,32(3):547-553.(in Chinese)
[12]魏小峰,戚学锋,王鹏.民用飞机进气道气动设计的评估方法[J].科技信息,2012(28):373-374.WEI Xiaofeng,QI Xuefeng,WANG Peng.Assessment method for aerodynamic design of civil aircraft inlet[J].Science and Technology Information,2012(28):373-374.(in Chinese)
[13]刘凯礼,谭兆光,杨士普,等.民用飞机大涵道比发动机短舱的阻力特性分析[C]∥中国力学大会2013论文集.北京:中国力学学会,2013:297-303.
[14]刘凯礼,孙一峰,钟园,等.民用飞机进气道的侧风畸变研究[J].航空动力学报,2015,32(2):289-296.LIU Kaili,SUN Yifeng,ZHONG Yuan,et al.Study on cross-wind distortion of civil aircraft inlet[J].Journal of Aerospace Power,2015,32(2):289-296.(in Chinese)
[15]姬昌睿,刘凯礼,张鹏飞,等.外物损伤对民用飞机短舱内/外流气动特性的影[J].航空学报,2015,36(3):772-781.JI Changrui,LIU Kaili,ZHANG Pengfei,et al.Influence of external object damage on inflow/outflow aerodynamic characteristics of civil aircraft nacelle[J].Acta Aeronautica et Astronautica Sinica,2015,36(3):772-781.(in Chinese)
[16]闫海津,杜玺,谭廉华.发动机短舱侧风工况数值模拟与分析[C]∥第七届中国航空学会青年科技论坛文集.北京:中国科学技术出版社,2016:522-526.
[17]刘浩,李博,王成,等.滑跑条件下短舱进气道地面涡数值仿真[J].航空动力学报,2018,33(7):1657-1664.LIU Hao,LI Bo,WANG Cheng,et al.Ground vortices numerical simulation of nacelle inlet at cross-wind conditions[J].Journal of Aerospace Power,2018,33(7):1657-1664.(in Chinese)
[18]陈晶晶,吴亚东,田杰,等.侧风条件下进气道流场及地面吸入涡特征研究[J].航空动力学报,2019,34(1):228-237.CHEN Jingjing,WU Yadong,TIAN Jie,et al.Research on the inlet flow field and ground vortex under crosswind condition[J].Journal of Aerospace Power,2019,34(1):228-237.(in Chinese)