周向稳态总压畸变在多级轴流压气机中传递的逐级模拟研究
Study of staged propagation of circumferential steady total pressure distortion in axial flow compressors
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摘要: 基于多级轴流压气机的逐级特性,建立了进口周向稳态总压畸变在多级轴流压气机中传递的逐级计算模型.对总压畸变条件下转子叶片攻角变化、级间周向流动和压气机出口耦合效应进行了数值分析,讨论了周向稳态总压畸变沿轴向衰减、级间周向侧流变化、失稳首发级和压气机出口耦合效应对压气机特性的影响.应用本模型方法对8级轴流压气机进行了详细的数值分析,计算结果表明,该模型方法是合理、可行的.Abstract: Based on the stage characteristics of axial flow compressor,a new model was established for calculating the propagation of circumferential steady total pressure distortion in multistage axial flow compressors.The inlet angle of attack,circumferential flow of stages and coupled compressor diffuser flow were also analyzed numerically.Meanwhile,the influences of axial attenuation of circumferential steady total pressure distortion,unsteady primary level and coupling performance of compressor outlet on the characteristic of compressor were discussed.Based on this model,the multistage axial flow compressors were analyzed numerically,proving that this model is reasonable and feasible.
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[1] Rabe D.Influence of inlet distortion on transonic compressor blade loading[R].AIAA 95-2461. [2] Marshall J G.Prediction of low engine order inlet distortion driven response in a low aspect ratio fan[R].ASME Paper 2000-GT-0374,2000. [3] 吴虎,冯维林.周向总压畸变在轴流压气机中传递特性分析[J].航空动力学报,2005,20(3):725-730.WU Hu,FENG Weilin.Propagation of circumferential presure distortion in axial flow compressors[J].Journal of Aerospace Power,2005,20(3):725-730. [4] 董金钟,王苗苗.总压总温组合畸变对压气机稳定性影响的数值模拟研究[J].航空动力学报,2003,18(6):788-793.DONG Jinzhong,WANG Miaomiao.Effect on stability of compressor with total temperature and pressure distortions[J].Journal of Aerospace Power,2003,18(6):788-793. [5] Hah C.Effects of inlet distortion on the flow field in a transonic compressor rotor[J].ASME J Turbomach,1998,12:233-246. [6] Lecht M.Improvement of parallel compressor by consideration of insteady blade aerodynamics[R].AD-P005467,1987. [7] Kimzey W F.An analysis of the influence of some external disturbances on the aerodynamic atability of turbine engine axial flow fans and compressors[R].AEDC-TR-77-80,Augest 1977. [8] 吴虎,黄智涛,廉小纯.某型发动机对畸变进气响应的流动耦合分析[J].推进技术,2003,24(3):219-235.WU Hu,HUANG Zhitao,LIAN Xiaochun.Coupled compressor diffuser flow model for predicting response of a twin spool turbine engine to inlet pressure distortion[J].Journal of Propulsion Technology,2003,24(3):219-235. [9] Edward J M.Performance of a J85-13 compressor with clean and distortion inlet flow[R].NASA TM X-3304,1975. -
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