一种冲击-冲压式超音速压气机设计尝试

推进技术 ›› 2014, Vol. 35 ›› Issue (4): 479-484.

一种冲击-冲压式超音速压气机设计尝试

王洪伟,孙芳琦

北京航空航天大学能源与动力工程学院/航空发动机气动热力国防科技重点实验室, 北京 100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国防科技重点实验室, 北京 100191

发布日期:2021-08-15
作者简介:王洪伟(1973—),男,博士,讲师,研究领域为叶轮机内真实流场的实验研究。 E-mail:wanghw@buaa.edu.cn

Design of an Impulse-Ram Type Supersonic Compressor

National Key Laboratory of Science and Technology on Aero-Engine/School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine/School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 为了探索高负荷压气机设计技术,提出了一种冲击-冲压式超声速压气机的设计方案。设计得到的冲击式转子在叶尖切线速度为457m/s下实现了4.6的压比和0.88的绝热效率,该转子的出口马赫数高达2.1,采用了冲压式静子来实现减速扩压,结合边界层吸气等手段,最终整级的压比为3.4,绝热效率为0.72。结果表明:这种超声速压气机设计方案可以实现较高的负荷和可以接受的效率,是一种值得关注与研究的高负荷压气机气动布局。 

关键词: 超声速压气机;高负荷压气机;压气机设计;冲击式转子;冲压式静子 

Abstract: An impulse-ram type supersonic compressor was proposed in order to explore highly-loaded compressor design technique. The rotor is an impulse-type design with tip velocity of 457m/s, pressure ratio 4.6and adiabatic efficiency of 0.88. A ram-type stator was designed to achieve flow diffusion and accommodate the flow at the exit of the rotor, which is as high as Mach number of 2.1. With boundary layer suction, the final compressor stage gives pressure ratio of 3.4and adiabatic efficiency of 0.72. The result suggests that the impulse-ram type supersonic compressor can achieve high load and acceptable efficiency, which states that it is an aerodynamic configuration worthy of concern and investigation. 

Key words: Supersonic compressor; Highly-loaded compressor; Compressor design; Impulse-type rotor; Ram-type stator

王洪伟,孙芳琦. 一种冲击-冲压式超音速压气机设计尝试[J]. 推进技术, 2014, 35(4): 479-484.

WANG Hong-wei, SUN Fang-qi. Design of an Impulse-Ram Type Supersonic Compressor[J]. Journal of Propulsion Technology, 2014, 35(4): 479-484.

参考文献

[1] A Weise.Uberschallaxialverdichter[R].Bericht 171der Lilienthal-Gesellschaft,1943.
[2] 王华青, 陈懋章.高负荷高通流跨音压气机的研制和应用[J].航空动力学报,2003,8(3):175-180.
[3] Kantrowitz A.The Supersonic Axial-flow Com-pressor[R].NACA 974,6.
[4] Guy N Ullman, Hartmann Melvin J, Edward R Tysl.Experimental Investigation of a 16-Inch Impulsive-Type Supersonic-Compressor Rotor[R].NACA E51G19,1.
[5] Klapproth J F, Ullman G N, Edward R Tysl.Performance of an Impulsive-Type Supersonic Compressor with Stators[R].NACA RM52B22, 1952.
[6] Jacklitch J, Hartmann M J.Investigation of 16-Inch Impulse-type Supersonic Compressor Rotor with Turning Past Axial Direction[R].NACA RM E53D13,3.
[7] Wilcox W W.Investigation of Impulse-Type Super-sonic Compressor with Hub-Tip Ratio of 0.6and Turning to Axial Direction:I-Performance of Rotor Only[R].NACA RM E54B25,4.
[8] Wilcox W W.Investigation of Impulse-Type Super-sonic Compressor with Hub-Tip Ratio of 0.6and Turning to Axial Direction:II-Stage Performance with Three Different Sets of Stators[R].NACA RM E55F28,5.
[9] Goldberg T J, Erwin J R.Performance of an Impulse-Type Supersonic-Compressor Rotor Having a Mean Turning of 114°[R].NACA RM L56J01,7.
[10] James R S.Experimental Investigation of an Im-pulse-type Supersonic Compressor Rotor Having a Turning of 73o[R].NACA TN4252,8.
[11] Gallus H E, Bohn D, Broichhausen K D.Unsteady Upstream Effects in Axial-Flow Supersonic Compressor Stages[R].ASME 79-GT-55.
[12] Gallus H E, D Bohn, K D Broichhausen.Measurements of Quasi-steady and Unsteady Flow Effects in a Supersonic Compressor Stage[J].Journal of Engineering for Power, 1977,9(1):15-21.
[13] Wennerstrom A J, Buzzell W A, DeRose R D.Test of a Supersonic Axial Compressor Stage Incorporating Splitter Vanes in the Rotor[R].NACA A237410,5.
[14] Broichhausen K D,Ziegler K U.Supersonic and Transonic Compressors:Past, Status and Technology Trends[R].ASME 2005-GT-69067.
[15] Lawlor S P,Baldwin P.Conceptual Design of a Supersonic CO₂Compressor[R].ASME 2005-GT-68349.
[16] Wennerstrom A J.Design of Highly Loaded Axial-flow Fans and Compressors[M].Vermont:Concepts ETI Inc,2000.