超声压气机叶型设计方法

doi:10.7527/S1000-6893.2013.0384

Abstract

Abstract:

In order to make inlet Mach number and flow angle equal to a given value in the design of supersonic compressor blade profile, this paper presents a new blade profile parameterization method. The method is based on solving unique incidence classic method, and gives the relationship between the blade profile shape with unique incidence by analysis and formula derivation. The front part of blade profile is determined by the inlet Mach number and flow angle, and the other part is determined by blade profile characteristic parameters such as the throat area ratio, the small circle radius at the leading edge and trailing edge, the maximum deflection, the maximum thickness, etc. The method is used to design 6 supersonic compressor blade profiles. And Fluent is used to verify the design results. The results show that the design value of inlet Mach number and flow angle are consistent with the Fluent solution result (the maximum error of the Mach number is only 0.01, and the maximum error of the flow angle is only 0.7°); the parameterization method is easy to achieve compression by much oblique shock and a normal shock.

Key words: supersonic cascades, compressors, blade profile design, unique incidence, blade profile parameterization, C-shaped blade profile, S-shaped blade profile

CLC Number:

V231.3

QIU Ming, ZHOU Zhenggui, LIU Longlong, CUI Cui. Supersonic Compressor Blade Profile Design Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(4): 975-985.

References

[1] Chen M Z. Development of fan compressor techniques and suggestions on further researches[J]. Journal of Aerospace Power, 2002, 17(1): 1-15. (in Chinese) 陈懋章. 风扇/压气机技术发展和对今后工作的建议[J]. 航空动力学报, 2002, 17(1): 1-15.

[2] Erwin J R, Wright L C, Kantrowitz A. Investigation of an experimental supersonic axial-flow compressor, NACA-RM-L6J01b. Washington, D.C.: National Advisory Committee for Aeronautics, 1947.

[3] Levine P. Two-dimensional inflow conditions for a supersonic compressor with curved blades[J]. Journal of Applied Mechanics, 1957, 24(2): 165-169.

[4] Lichtfuss H J, Starken H. Supersonic cascade flow[J].Progress in Aerospace Science, 1974, 15: 37-149.

[5] York R E, Woodard W S. Supersonic compressor cas-cades-an analysis of the entrance region flow field con-tain detached[J]. Journal of Engineering for Power, 1976, 98(2): 247-257.

[6] Liu C E, Wu W Q. Computer program of super-sonic flow past inlet of cascade section on an arbitrary stream filament of revolution and determing unique in-let flow angle[J]. Journal of Engineering Thermophysics, 1980, 1(3): 255-264. (in Chinese) 刘翠娥, 吴文权. 任意迥转面叶栅超声速进口流场特征线法计算机程序和唯一进气角的确定[J]. 工程热物理学报, 1980, 1(3): 255-264.

[7] Gallimore S J. Axial flow compressor design[J]. Journal of Mechanical Engineering Science, 1999, 213(5): 437-449.

[8] Chen T, Liu Y, Liu B, et al. A character-parameter method for axial turbomachinery blade design[J]. Journal of Xi'an Jiao Tong University, 1997, 31(5): 52-57. (in Chinese) 陈铁, 刘仪, 刘斌, 等. 轴流式叶轮机械叶型的参数设计方法[J]. 西安交通大学学报, 1997, 31(5): 52-57.

[9] Leonard O. Design method for subsonic and transonic cascade with prescribed mach number distribution[J]. Journal of Turbomachinery, 1992, 114(3): 553-559

[10] Cao Z P, Lan F X, Xia T, et al. An inverse method for high loading fan rotor airfoil design[J]. Gas Turbine Experiment and Research, 2012, 25(2): 1-6.(in Chinese) 曹志鹏, 兰发祥, 夏天, 等. 高负荷风扇转子叶片反问题设计[J]. 燃气涡轮试验与研究, 2012, 25(2): 1-6.

[11] Du L, Ning F F. Aerodynamic inverse design method for low mach number airfoils[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(7): 1180-1187. (in Chinese) 杜磊, 宁方飞. 低速叶型气动反问题设计方法[J]. 航空学报, 2011, 32(7): 1180-1187.

[12] Xiao M, Liu B, Cheng R H. An investigation on a new technique for designing supersonic blade air-foil of axial flow compressor[J]. Journal of Aerospace Power, 2002, 17(1): 83-86.(in Chinese) 肖敏, 刘波, 程荣辉. 轴流压气机超音叶片新设计技术研究[J]. 航空动力学报, 2002, 17(1): 83-86.

[13] Cumpsyt N A. Compressor aerodynamics[M]. London: World Publishing Corp, 1989: 198-204.

[14] Broichhausen K D, Ziegler K U. Supersonic and tran-sonic compressors past, status and technology trends, ASME Paper GT2005-69067. 2005.

[15] Klapproth J F, Ullman G N, Tysl E R. Performance of an impulse-type supersonic compressor with stators, NACA RM52B22. Washington, D.C.: National Advisory Committee for Aeronautics, 1952.

[16] Zhou Z G, Wang G W. Design research of supersonic fan blade profile[J]. Journal of Aerospace Power, 2009, 21(1): 127-131. (in Chinese) 周正贵, 汪光文. 超声速风扇叶型设计研究[J]. 航空动力学报, 2009, 21(1): 127-131

Supersonic Compressor Blade Profile Design Method

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