多级轴流压气机进气畸变模型研究
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摘要
为研究进气畸变对多级轴流压气机性能以及稳定性的影响,基于彻体力模型理论建立了一个模拟多级轴流压气机进气畸变的三维分析模型CSAC,并采用实验与CFD相结合的方法进行了验证。利用CSAC模型模拟了周向总压畸变对四级低速轴流压气机性能的影响。结果表明:均匀进气下CSAC与CFD计算特性最大误差不超过1.5%;进口总压畸变传递到第三级时畸变度衰减为0;在低压区的转子出口存在一个高总温畸变区,其强度在向下游传递中逐渐增强,到达第四级时总温最大升高0.4%;高总温影响区域在向下游发展中沿叶片转动方向逐渐扩张,造成压气机性能损失加大,最大总压比下降0.7%。所有结果均显示出CSAC模型是当前分析畸变对压气机性能影响的有力工具。
In order to analysis the effects of inlet-distortion on multistage axial compressors performance and stability,a three-dimensional analysis model called CSAC for multistage axial compressor was developed based on body-force model theory. CSAC model was validated by both measurements and CFD methods. The effects of inlet circumferential total pressure distortion on the four-stage compressor were analyzed using this model. The results show that the maximum error of both CSAC and CFD results under clean inlet is less than 1.5%.The inlet circumferential total pressure distortion decays rapidly to zero when it propagates to the third stage. A high total temperature distortion area appears at the exit of rotor,and the temperature increases by 0.4% when it spreads to the fourth stage. The affected region extends circumferentially along rotation direction,which causes more serious loss with 0.7% in total pressure ratio decrease. All results show that the CSAC model is a powerful distortion analysis tool for compressors in current time.
In order to analysis the effects of inlet-distortion on multistage axial compressors performance and stability,a three-dimensional analysis model called CSAC for multistage axial compressor was developed based on body-force model theory. CSAC model was validated by both measurements and CFD methods. The effects of inlet circumferential total pressure distortion on the four-stage compressor were analyzed using this model. The results show that the maximum error of both CSAC and CFD results under clean inlet is less than 1.5%.The inlet circumferential total pressure distortion decays rapidly to zero when it propagates to the third stage. A high total temperature distortion area appears at the exit of rotor,and the temperature increases by 0.4% when it spreads to the fourth stage. The affected region extends circumferentially along rotation direction,which causes more serious loss with 0.7% in total pressure ratio decrease. All results show that the CSAC model is a powerful distortion analysis tool for compressors in current time.
引文
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[9]Ewan J Gunn,Sarah E Tooze,Cesare A Hall.An Experimental Study of Loss Sources in a Fan Operating with Continuous Inlet Stagnation Pressure Distortion[J].Journal of Turbomachinery,2013,135(5).
[10]许开富,乔渭阳,罗华玲.风扇/压气机稳定性三维模型的研究[J].推进技术,2008,29(3):344-348.(XU Kai-fu,QIAO Wei-yang,LUO Hua-ling.A 3-D Analysis Code of Fan and Compressor Stability[J].Journal of Propulsion Technology,2008,29(3):344-348.)
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[12]Davis M W Jr,William T C.Evaluating Complex Inlet Distortion with a Parallel Compressor Model:Part 2-Applications to Complex Patterns[R].ASME GT-2011-45068.
[13]屠宝锋,胡骏.旋转总压畸变对压气机稳定性影响的三维非定常模型[J].航空动力学报,2011,26(2):255-261.
[14]Hale A A,Davis M W Jr,Kneile K R.Turbine Engine Analysis Compressor Code:TEACC Part I:Technical Approach and Steady Results[R].AIAA 94-0148.
[15]Hale A,O’Brien W.A Three-Dimensional Turbine Engine Analysis Compressor Code(TEACC)for Steadystate Inlet Distortion[J].Journal of Turbomachinery,1998,120(3):422-430.
[16]Chima R V.A Three-Dimensional Unstedy CFD Model of Compressor Stability[R].ASME GT-2006-90040.
[17]Andreas Lesser,Jens Iseler,Reinhard Niehuis.Numerical Investigation of a Highly Loaded Axial Compressor Stage with Inlet Distortions[R].ASME GT-2011-46457.
[18]Peng Sun,Haiyang Gao,Jinjun Zhong,et al.Study on the Influence of Total Pressure Distortion on End Wall Flow Field in a Supersonic Compressor[R].ASME GT-2013-94729.
[19]Georg A R.Estimation of Axial Compressor Body Forces Using Three-Dimensional Flow Computations[D].Massachusetts:Massachusetts Institute of Technology,2009.
[20]Marble F E.Aerodynamics of Turbines and Compressors[M].Princeton:Princeton University Press,1964:83-166.
[21]Zhang C,Hu J,Wang Z,et al.Design Work of a Compressor Stage Through High-To-Low Speed Compressor Transformation[J].Journal of Engineering for Gas Turbines and Power,2014,136(6).
[2]Kimball A S.Application of a Modified Dynamic Compression System Model to a Low Aspect Ratio Fan:Effects and Inlet Distortion[R].AIAA 95-0301.
[3]刘大响.发动机稳定性评定—航空发动机进口流场畸变评定技术译文集[M].北京:中国燃气涡轮研究院,1997.
[4]AIR-1419 Revision A.Inlet Total Pressure-distortion Considerations For Gas-turbine Engines[S].Society of Automotive Engineers,Inc.,1999.
[5]Novak R A,Hearsey R M,Smith G E.Propulsion System Flow Stability Program(Dynamic)[R].NASA AFAPL-TR68-142.
[6]Longley J P.Measured and Predicted Effects of Inlet Distortion on Axial Compressor[R].ASME 90-GT-214.
[7]李茂义,陆亚钧,弓志强,等.进口畸变条件下轴流压气机转子内流的PIV研究[J].航空动力学报,2006,22(3):461-466.
[8]马明明,马燕荣,王小峰,等.扰流板进气总压畸变实验[J].航空学报,2009,30(8):1361-1366.
[9]Ewan J Gunn,Sarah E Tooze,Cesare A Hall.An Experimental Study of Loss Sources in a Fan Operating with Continuous Inlet Stagnation Pressure Distortion[J].Journal of Turbomachinery,2013,135(5).
[10]许开富,乔渭阳,罗华玲.风扇/压气机稳定性三维模型的研究[J].推进技术,2008,29(3):344-348.(XU Kai-fu,QIAO Wei-yang,LUO Hua-ling.A 3-D Analysis Code of Fan and Compressor Stability[J].Journal of Propulsion Technology,2008,29(3):344-348.)
[11]William T C,Davis M W Jr.Evaluating Complex Inlet Distortion with a Parallel Compressor Model:Part 1-Concepts,Theory,Extensions,and Limitations[R].ASME GT-2011-45067.
[12]Davis M W Jr,William T C.Evaluating Complex Inlet Distortion with a Parallel Compressor Model:Part 2-Applications to Complex Patterns[R].ASME GT-2011-45068.
[13]屠宝锋,胡骏.旋转总压畸变对压气机稳定性影响的三维非定常模型[J].航空动力学报,2011,26(2):255-261.
[14]Hale A A,Davis M W Jr,Kneile K R.Turbine Engine Analysis Compressor Code:TEACC Part I:Technical Approach and Steady Results[R].AIAA 94-0148.
[15]Hale A,O’Brien W.A Three-Dimensional Turbine Engine Analysis Compressor Code(TEACC)for Steadystate Inlet Distortion[J].Journal of Turbomachinery,1998,120(3):422-430.
[16]Chima R V.A Three-Dimensional Unstedy CFD Model of Compressor Stability[R].ASME GT-2006-90040.
[17]Andreas Lesser,Jens Iseler,Reinhard Niehuis.Numerical Investigation of a Highly Loaded Axial Compressor Stage with Inlet Distortions[R].ASME GT-2011-46457.
[18]Peng Sun,Haiyang Gao,Jinjun Zhong,et al.Study on the Influence of Total Pressure Distortion on End Wall Flow Field in a Supersonic Compressor[R].ASME GT-2013-94729.
[19]Georg A R.Estimation of Axial Compressor Body Forces Using Three-Dimensional Flow Computations[D].Massachusetts:Massachusetts Institute of Technology,2009.
[20]Marble F E.Aerodynamics of Turbines and Compressors[M].Princeton:Princeton University Press,1964:83-166.
[21]Zhang C,Hu J,Wang Z,et al.Design Work of a Compressor Stage Through High-To-Low Speed Compressor Transformation[J].Journal of Engineering for Gas Turbines and Power,2014,136(6).