跨声速轴流压气机转子弯掠控制机理

吕从鹏; 姜斌; 张寅豹; 王国强; 邱毅; 郑群

doi:10.13224/j.cnki.jasp.2017.04.028

跨声速轴流压气机转子弯掠控制机理

doi: 10.13224/j.cnki.jasp.2017.04.028

1.
哈尔滨工程大学动力与能源工程学院，哈尔滨 150001
2.
天津出入境检验检疫局，天津 300201

基金项目: 国家自然科学基金（51676050）；中央高校基本科研业务费专项资金（HEUCF150304）

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出版历程
- 收稿日期: 2015-07-13
- 刊出日期: 2017-04-28

Controlling mechanisms of bowed and swept of rotor in transonic axial compressor

摘要

摘要: 以1.5级跨声速轴流压气机为研究对象，采用三维数值模拟方法研究弯掠叶片技术对压气机不同工况的控制机理.结果表明：设计转速时前掠与反弯的组合弯掠优于前掠与正弯的组合弯掠，而部分转速时正好相反，这是因为不同弯掠方案对跨声速压气机不同工况的控制机理不同.设计转速时弯掠叶片改变叶顶激波强度和位置以及叶顶间隙泄漏涡强度，并改变叶片表面展向“C”型压力分布，三者共同作用从而提高设计转速时压气机的喘振裕度，但也造成设计转速效率下降；而部分转速时，压气机流场中的激波消失，弯掠叶片改变叶顶吸力面逆压力梯度和增强展向“C”型压力分布，两者共同作用使压气机的稳定性提高，但效率也会下降.
- 跨声速转子 /
- 弯掠转子 /
- 喘振裕度 /
- 效率 /
- 激波结构
Abstract: In a 1.5-stage transonic axial compressor, the controlling mechanism of bowed and swept blades was researched by 3-D numerical simulation when the compressor was working at different conditions. Results show that the combined scheme of sweepforward and positive bow is better than the combined scheme of sweepback and negative bow at the design speed, but its completely opposite at the part speed, because the controlling mechanisms of different bowed and swept schemes are different at the design speed and the part speed. The intensity and position of shock can be changed by the bowed and swept blades at the design speed, the same as the leakage vortex in the shroud gap and the spanwise C-shape pressure distribution; so the surge margin of compressor could be improved by combined action of three changed factors, but followed with the decrease of efficiency. However, the shock disappeared at the part speed, the reverse pressure gradient of the suction surface at the top of blade and the spanwise C-shape pressure distribution are changed, improving the aerodynamic stability of compressor and cutting down the efficiency.
- transonic rotor /
- bowed and swept rotor /
- surge margin /
- efficiency /
- shock structure

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参考文献(20)

[1]	Wadia A R,Szucs P N,Crall D W.Inner workings of aerodynamic sweep［J］.Journal of Turbomachinery,1998,120(4):671-682.
[2]	Denton J D.The effects of lean and sweep on transonic fan performance:a computational study［J］.Task Quaeterly,2002,6(1):1-17.
[3]	Okui H,Verstaete T.Three-dimensional design and optimization of a transonic rotor in axial flow compressor［J］.Journal of Turbomachinary,2013,135(3):45-53.
[4]	Benni E,Biollo R.On the aerodynamics of swept and leaned transonic compressor rotors［R］.ASME Paper GT2006-90547,2006.
[5]	Jin H L,Jin D H,Zhu F.Design of a highly loaded transonic two-stage fan using swept and bowed blade［R］.ASME Paper GT-2011-45988,2011.
[6]	毛明明,宋彦萍,王仲奇.跨声速轴流压气机动叶弯和掠效应的应用［J］.工程热物理学报,2009,30(4):581-586.MAO Mingming,SONG Yanping,WANG Zhongqi.Application of bowed and swept rotors in a transonic axial compressor［J］.Journal of Engineering Thermophysics,2009,30(4):581-586.(in Chinese)
[7]	毛明明.跨声速轴流压气机弯和掠的数值研究［D］.哈尔滨:哈尔滨工业大学,2008.MAO Mingming.Numerical investigation of bowed and swept rotor［D］.Harbin:Harbin Institute of Technology,2008.(in Chinese)
[8]	毛明明,宋彦萍.跨声轴流压气机动叶的三维弯掠设计应用［J］.动力工程,2008,28(1):58-63.MAO Mingming,SONG Yanping.Research on design of swept and bowed rotor in a transonic axial flow cmpressor［J］.Journal of Power Engineering,2008,28(1):58-63.(in Chinese)
[9]	姜斌,王松涛,冯国泰,等.高负荷低压风扇三维气动设计与损失分析［J］.航空动力学报,2010,25(2):424-433.JIANG Bin,WANG Songtao,FENG Guotai,et al.Research on three-dimensional aerodynamic design of transonic fan and loss analysis［J］.Journal of Aerospace Power,2010,25(2):424-433.(in Chinese)
[10]	姜斌,郑群,王松涛,等.跨声速风扇的弯、掠三维设计研究［J］.航空动力学报,2012,27(8):1815-1825.JIANG Bin,ZHENG Qun,WANG Songtao,et al.Research on three-dimensional design of bowed and swept blade of transonic fan［J］.Journal of Aerospace Power,2012,27(8)：1815-1825.(in Chinese)
[11]	茅晓晨,刘波,张国臣.复合弯掠优化对跨声速压气机性能影响的研究［J］.推进技术,2015,36(7):996-1004.MAO Xiaochen,LIU Bo,ZHANG Guochen.Effectivenss of composite optimization of lean and sweep on transonic compressor performance［J］.Journal of Propulsion Technology,2015,36(7):996-1004.(in Chinese)
[12]	Simon J G,John J B.The use of sweep and dihedral in multistage axial flow compressor blading:Part Ⅰ university research and methods development［R］.ASME Paper GT- 2002-30328,2002.
[13]	Simon J G,John J B.The use of sweep and dihedral in multistage axial flow compressor blading:Part Ⅱ low and high speed designs and test verification［R］.ASME Paper GT-2002-30329,2002.
[14]	张华良.采用叶片弯/掠及附面层抽吸控制扩压叶栅内涡结构的研究［D］.哈尔滨：哈尔滨工业大学,2007.ZHANG Hualiang.Investigation on application of dihedral/swept blade and boundary layer suction to control vortex configuration in compressor cascades［D］.Harbin：Harbin Institute of Technology,2007.(in Chinese)
[15]	Gummer V,Wenger U,Kau H P.Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressor［J］.Journal of Turbomachinery,2001,123(1):40-48.
[16]	Roy B,Laxmiprasanna P A.Low speed studies of sweep and dihedral effects on compressor cascades［R］.ASME Paper GT-2002-30441,2002.
[17]	Reid L,Moore R D.Design and overall performance of four highly loaded,high-speed inlet stages for an advanced high-pressure-ratio core compressor［R］.NASA-TP-1337,1978.
[18]	Moore R D,Reid L.Performance of single-stage axial- flow transonic compressor with rotor and stator aspect ratio of 1.19 and 1.26,respectively,and with design pressure ratio of 2.05［R］.NASA-TP-1659,1980.
[19]	李绍斌,苏杰先,王仲奇.采用高负荷弯曲静叶的压气机改型研究［J］.航空动力学报,2006,21(4):741-746.LI Shaobin,SUN Jiexian,WANG Zhongqi.Redesign of a transonic compressor stage using highly loaded bowed stator［J］.Journal of Aerospace Power,2006,21(4):741-746.(in Chinese)
[20]	Herrick G P,Hathaway M D,Chen J P.Unsteady full annulus simulations of a transonic axial compressor stage ［R］.AIAA-2009-1059，2009.