基于时间推进的轴流压气机气动性能计算模型
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摘要
基于时间推进方法,通过求解周向平均带体积力源项的流动控制方程,融合发展较为完善的落后角及损失模型,考虑径向掺混影响,同时引入Koch稳定边界模型,建立了一个轴流压气机性能预测计算模型。利用该模型对两台四级低速轴流压气机及两台单级跨声速压气机展开计算,得到了相应的特性曲线,并将计算值与相关实验数据进行对比分析。结果表明,该模型能可靠预测轴流压气机总体特性,可为多级压气机特性分析提供有效的技术支撑。
Based on the time marching method,an axial flow compressor performance prediction model was established by solving the circumferential average flow control equations with body force source terms and adding the deviation angle and loss model.Meanwhile,the influence of radial mixing was taken into consideration and the Koch stable boundary model was introduced to build a performance prediction calculation model for axial flow compressor.The calculations were carried out for two four stage low speed axial flow compressors and two single stage transonic compressors.The corresponding characteristic curves were obtained and the calculations were compared with the related experimental data.Results show that the model is reliable to predict the overall characteristics of axial flow compressors so to provide a powerful tool for the analysis of multi-stage compressor characteristics.
Based on the time marching method,an axial flow compressor performance prediction model was established by solving the circumferential average flow control equations with body force source terms and adding the deviation angle and loss model.Meanwhile,the influence of radial mixing was taken into consideration and the Koch stable boundary model was introduced to build a performance prediction calculation model for axial flow compressor.The calculations were carried out for two four stage low speed axial flow compressors and two single stage transonic compressors.The corresponding characteristic curves were obtained and the calculations were compared with the related experimental data.Results show that the model is reliable to predict the overall characteristics of axial flow compressors so to provide a powerful tool for the analysis of multi-stage compressor characteristics.
引文
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[7]Pacciani R,Rubechini F,Marconcini M,et al.ACFD-based throughflow method with an explicit bodyforce model and an adaptive formulation for the S2 stream-surface[J].Journal of Power and Energy,2016,230(1):16—28.
[8]Taddei S R,Larocca F.CFD-based analysis of multistagethroughflow surfaces with incidence[J].Mechanics Re-search Communications,2013,47:6—10.
[9]Koch C C.Stalling pressure rise capability of axial flowcompressor stages[J].ASME Journal of Engineering forGas Turbines and Power,1981,103(4):645—656.
[10]Gallimore S J,Cumpsty N A.Spanwise mixing in multi-stage axial flow compressors:part I:experimental investi-gation[R].ASME 86-GT-20,1986.
[11]Gallimore S J,Cumpsty N A.Spanwise mixing in multi-stage axial flow compressors:part II:throughflow calcula-tions including mixing[R].ASME 86-GT-21,1986.
[12]Edwards J R.A low-diffusion flux-splitting scheme forNavier-Stokes calculations[J].Computers&Fluids,1997,26(6):635—659.
[13]Marble F E.Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors[M].Princeton:Princeton University Press,1964.
[14]赵勇.风扇/压气机非设计点性能计算和进气畸变影响预测方法研究[D].南京:南京航空航天大学,2008.
[15]Banjac M,Petrovic M V,Wiedermann A.Secondary flows,endwall effects,and stall detection in axial compressor de-sign[R].ASME GT2014-25115,2014.
[16]张晨凯.多级轴流压气机内复杂流动结构的实验和数值研究[D].南京:南京航空航天大学,2015.
[17]Reid L,Moore R D.Performance of a single stage axi-al-flow transonic compressor with rotor and stator aspect ratio of 1.19 and 1.26,respectively,and with designpressure ratio of 1.82[R].NASA TP-1338,1978.
[18]Moore R D,Reid L.Performance of single-stage axi-al-flow transonic compressor with rotor and stator aspectratios of 1.19 and 1.26,respectively,and with design pres-sure ratio of 2.05[R].NASA TP-1659,1980.
[19]Chima R V.SWIFT code assessment for two similar tran-sonic compressors[R].AIAA 2009-1058,2009.
[2]Novak R A.Streamline curvature computing proceduresfor fluid-flow problems[J].ASME Journal of Engineeringfor Gas Turbines and Power,1967,89(4):478—490.
[3]胡骏.均匀与非均匀进气条件下多级轴流压气机性能计算-均匀进气及径向畸变的影响[J].航空动力学报,2000,15(3):225—228.
[4]Marsh H.A digital computer program for the through-flowfluid mechanics in an arbitrary turbomachine using a ma-trix method[R].London:Aeronautical Research Council Rand M,1968.
[5]Baralon S,Hall U,Eriksson L E.Viscous throughflow mod-elling of transonic compressors using a time-marching fi-nite volume solver[R].ISABE 97-7071,1997.
[6]Simon J F,Léonard O.A throughflow analysis tool based on the Navier-Stokes equations[C]//.Proceedings of 6thEuropean Turbomachinery Conference.France Lille,2005.
[7]Pacciani R,Rubechini F,Marconcini M,et al.ACFD-based throughflow method with an explicit bodyforce model and an adaptive formulation for the S2 stream-surface[J].Journal of Power and Energy,2016,230(1):16—28.
[8]Taddei S R,Larocca F.CFD-based analysis of multistagethroughflow surfaces with incidence[J].Mechanics Re-search Communications,2013,47:6—10.
[9]Koch C C.Stalling pressure rise capability of axial flowcompressor stages[J].ASME Journal of Engineering forGas Turbines and Power,1981,103(4):645—656.
[10]Gallimore S J,Cumpsty N A.Spanwise mixing in multi-stage axial flow compressors:part I:experimental investi-gation[R].ASME 86-GT-20,1986.
[11]Gallimore S J,Cumpsty N A.Spanwise mixing in multi-stage axial flow compressors:part II:throughflow calcula-tions including mixing[R].ASME 86-GT-21,1986.
[12]Edwards J R.A low-diffusion flux-splitting scheme forNavier-Stokes calculations[J].Computers&Fluids,1997,26(6):635—659.
[13]Marble F E.Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors[M].Princeton:Princeton University Press,1964.
[14]赵勇.风扇/压气机非设计点性能计算和进气畸变影响预测方法研究[D].南京:南京航空航天大学,2008.
[15]Banjac M,Petrovic M V,Wiedermann A.Secondary flows,endwall effects,and stall detection in axial compressor de-sign[R].ASME GT2014-25115,2014.
[16]张晨凯.多级轴流压气机内复杂流动结构的实验和数值研究[D].南京:南京航空航天大学,2015.
[17]Reid L,Moore R D.Performance of a single stage axi-al-flow transonic compressor with rotor and stator aspect ratio of 1.19 and 1.26,respectively,and with designpressure ratio of 1.82[R].NASA TP-1338,1978.
[18]Moore R D,Reid L.Performance of single-stage axi-al-flow transonic compressor with rotor and stator aspectratios of 1.19 and 1.26,respectively,and with design pres-sure ratio of 2.05[R].NASA TP-1659,1980.
[19]Chima R V.SWIFT code assessment for two similar tran-sonic compressors[R].AIAA 2009-1058,2009.