真实进气条件下发动机气动稳定性计算方法
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摘要
基于平行压气机理论,采用非定常、二维、无黏的积分型欧拉方程,以蒸汽吸入试验中产生的温度和压力组合畸变为边界条件,开展真实进气条件下温度和压力组合畸变对发动机影响的计算方法研究。在保证畸变强度、高温区范围、低压区范围等特征不变的前提下,对畸变图谱进行规则化等效转换,同时协调温度和压力畸变图谱,使两者可以进行相互叠加计算。结果表明:当周向子发动机数量大于2时,子发动机数量对计算结果影响不大;组合畸变对风扇、压气机压比影响规律与单独的压力畸变相同;与试验的推力损失对比显示,对畸变图谱进行等效规则化转换,可以用于真实组合畸变的计算。
Based on the theory of parallel compressor,the calculation method of the influence of actual combined distortion on the engine was studied with the temperature and pressure distortion generated by the steam suction as boundary conditions.The unsteady two-dimensional inviscid integral Euler's equations were used.While the distortion intensity,the high temperature range,and the low pressure range were kept the same,the regularized equivalent conversion of the distortion contour maps was performed.And the temperature and pressure distortion contour maps were coordinated,so that these two could be superimposed on each other.Results showed that when the number of circumferential sub-engines was greater than 2,the number of sub-engines had little effect on the calculation results.The influence of combined distortion on the fan and compressor pressure ratio was the same as the single pressure distortion.Compared with the experimental thrust loss,the equivalent regularization transformation of the distortion map can be used for the calculation of the actual combined distortion.
Based on the theory of parallel compressor,the calculation method of the influence of actual combined distortion on the engine was studied with the temperature and pressure distortion generated by the steam suction as boundary conditions.The unsteady two-dimensional inviscid integral Euler's equations were used.While the distortion intensity,the high temperature range,and the low pressure range were kept the same,the regularized equivalent conversion of the distortion contour maps was performed.And the temperature and pressure distortion contour maps were coordinated,so that these two could be superimposed on each other.Results showed that when the number of circumferential sub-engines was greater than 2,the number of sub-engines had little effect on the calculation results.The influence of combined distortion on the fan and compressor pressure ratio was the same as the single pressure distortion.Compared with the experimental thrust loss,the equivalent regularization transformation of the distortion map can be used for the calculation of the actual combined distortion.
引文
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[3]TOMASSETTI N R,MINK G R.Steam ingestion by aircraft gas turbine engines[R].Bordentown,NJ,US:National Conference on Environmental Effects on Aircraft and Propulsion Systems,1968.
[4]RUDEY R A.The effect of steam ingestion on transonic rotor stall margin[R].San Diego,CA,US:Propulsion Joint Specialist Conference,1970.
[5]KLEPPER J,HALE A,DAVIS M.A numerical investigation of the effects of steam ingestion on compression system performance[J].ASME Paper GT2004-54190,2004.
[6]BRUNNER M D.Experimental and computational investigation of flow in a transonic compressor inlet[D].Monterey,California:Naval Postgraduate School,2005.
[7]BOCHETTE N J.Computational analysis of flow through a transonic compressor rotor[D].Monterey,California:Naval Postgraduate School,2005.
[8]ZARRO S E.Steady-state and transient measurements within a compressor rotor during steam-induced stall at transonic operational speeds[D].Monterey,California:Naval Postgraduate School,2006.
[9]HEDGES C R.Computational fluid dynamic model of steam ingestion into a transonic compressor[D].Monterey,California:Naval Postgraduate School,2009.
[10]谢业平,刘永泉,张志学,等.空气中逸散水蒸汽传热及相变过程的行为研究[J].航空动力学报,2018,33(9):2058-2066.XIE Yeping,LIU Yongquan,ZHANG Zhixue,et al.Heat transfer and condensation of overflow steam in air[J].Journal of Aerospace Power,2018,33(9):2058-2066.(in Chinese)
[11]王鹏,蔡元虎,王占学,等.进气畸变对发动机压缩系统稳定性影响的数值模拟[J].流体机械,2006,34(8):15-19.WANG Peng,CAI Yuanhu,WANG Zhanxue,et al.Effect of pressure and temperature distortion on turbine engine stability[J].Fluid Machinery,2006,34(8):15-19.(in Chinese)
[12]赵运生,胡骏,屠宝锋,等.进气畸变对涡扇发动机稳定性及性能影响[J].航空动力学报,2013,28(6):1298-1304.ZHAO Yunsheng,HU Jun,TU Baofeng,et al.Inlet distortion's effects on stability and performance of turbofan engine[J].Journal of Aerospace Power,2013,28(6):1298-1304.(in Chinese)
[13]乔渭阳,蔡元虎,陈玉春.进气畸变对压缩系统稳定性影响的数值模拟[J].推进技术,2001,22(4):307-310.QIAO Weiyang,CAI Yuanhu,CHEN Yuchun.Effect of pressure and temperature distortion orientation on turbine engine stability[J].Journal of Propulsion Technology,2001,22(4):307-310.(in Chinese)
[14]叶巍,唐世建,白磊.进气温度畸变对某发动机稳定性影响的研究[J].燃气涡轮试验与研究,2006,19(4):6-15.YE Wei,TANG Shijian,BAI Lei.Study on the effects of inlet temperature distortion on stability of an engine[J].Gas Turbine Experiment and Research,2006,19(4):6-15.(in Chinese)
[15]程邦勤,王旭,陶增元.进气总压畸变对某型涡扇发动机性能的影响[J].空军工程大学学报,2004,5(4):4-7.CHENG Bangqin,WANG Xu,TAO Zengyuan.Effect of inlet total pressure distortion on the performance of a certain-type turbofan engine[J].Journal of Air Force Engineering University,2004,5(4):4-7.(in Chinese)
[16]TESCH W A,STEENKEN W G.Blade row and dynamic digital compressor program:Volume 1J85clean inlet flow and parallel compressor models[R].NASA CR-134978,1976.
[17]DAVIS M W,O BRIEN W F.Stage-by-stage poststall compression system modeling technique[R].AIAA 87-2088,1987.
[18]HALE A,O BRIEN W.A three-dimensional turbine engine analysis compressor code(TEACC)for steady-state inlet distortion[J].Journal of Turbomachinery,1998,120(7):42-53.
[19]CHALK J C,HALE A A.A three-dimensional compression system model using NPARC[R].AIAA 97-0992,1997.