喉部长度和扩张角对离心压气机管式扩压器影响研究 *

推进技术 ›› 2014, Vol. 35 ›› Issue (12): 1607-1614.

喉部长度和扩张角对离心压气机管式扩压器影响研究 *

韩　戈^1,2,卢新根¹,赵胜丰¹,阳诚武^1,2,朱俊强¹

中国科学院工程热物理研究所/轻型动力重点实验室，北京 100190; 中国科学院大学，北京100190,中国科学院工程热物理研究所/轻型动力重点实验室，北京 100190,中国科学院工程热物理研究所/轻型动力重点实验室，北京 100190,中国科学院工程热物理研究所/轻型动力重点实验室，北京 100190; 中国科学院大学，北京100190,中国科学院工程热物理研究所/轻型动力重点实验室，北京 100190

发布日期:2021-08-15
作者简介:韩　戈(1989—)，男，博士生，研究领域为叶轮机气动热力学。
基金资助:
国际合作专题项目(2014DFR70080)。

Effects of Diffuser Throat Length and Divergence Angle on Performance of Centrifugal Compressor with Pipe Diffuser

Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China; University of Chinese Academy of Sciences，Beijing 100190，China,Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China,Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China,Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China; University of Chinese Academy of Sciences，Beijing 100190，China and Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China

Published:2021-08-15

摘要/Abstract

摘要： 针对带楔形扩压器的高负荷离心压气机，利用数值模拟手段对其进行了研究，计算获得的离心压气机特性与试验结果符合较好。在此基础上，设计了具有不同喉部长度和扩张角的管式扩压器，利用经过校核的数值模拟手段对管式扩压器的喉部长度和扩张角进行了参数化研究。研究发现较长的喉部会使压气机设计点的性能下降，但是却可以抑制近失速点扩压器内的流动分离，喉部长度与喉部直径之比为0.5时综合性能较优；较大的扩张角会造成扩压器内流动分离，增加流动损失，扩张角由4°增加到12°时压气机效率降低了约3%。

关键词: 离心压气机；管式扩压器；数值模拟

Abstract: Numerical investigation of a highly loaded centrifugal compressor with wedge diffuser was performed and the result matches well with test data. Then，pipe diffusers with different throat length and divergence angle were designed and parametric studies of pipe diffuser throat length and divergence angle were carried out with the validated numerical method. It is found that long pipe diffuser throat length could decrease compressor performance at design point but could depress diffuser flow separation near surge. Performance is better when the ratio of throat length to throat diameter is 0.5. More loss could be caused by flow separation in pipe diffuser with larger divergence angle. The stage efficiency drops about 3% when divergence angle enlarges from 4°to 12°.

Key words: Centrifugal compressor；Pipe diffuser；Numerical simulation

韩　戈,卢新根,赵胜丰,阳诚武,朱俊强. 喉部长度和扩张角对离心压气机管式扩压器影响研究 *[J]. 推进技术, 2014, 35(12): 1607-1614.

HAN Ge^1,2,LU Xin-gen¹,ZHAO Sheng-feng¹,YANG Cheng-wu^1,2,ZHU Jun-qiang¹. Effects of Diffuser Throat Length and Divergence Angle on Performance of Centrifugal Compressor with Pipe Diffuser[J]. Journal of Propulsion Technology, 2014, 35(12): 1607-1614.

参考文献

[1] 王博, 严明. 离心压气机管式扩压器设计与计算分析[J]. 航空动力学报, 2012, 27(6), 1030-1311.
[2] 王毅, 赵胜丰, 卢新根. 高负荷离心压气机管式扩压器特点及机理分析[J].航空动力学报, 2011, 26(3):649-655.
[3] Wrong C B. Turbine Engine Design[R]. AIAA 81-0915.
[4] Moustapha H. Small Gas Turbine Technology: Evolution and Challenges[R]. AIAA 2003-2559.
[5] Kenny D P. A Novel Low-cost Diffuser for High-performance Centrifugal Compressors[J]. Journal of Engineering for Power, 1969, 37-47.
[6] Bennett I, Tourlidakis A, Elder R L. The Design and Analysis of Pipe Diffuser for Centrifugal Compressors[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2000, 214(1): 87-96.
[7] Bourgeois J A, Martinuzzi R J, Roberts D, et al. Experimental and Numerical Investigation of an Aero-Engine Centrifugal Compressor[R]. ASME 2009-GT-59808.
[8] Zachau U and Buescher C. Experimental Investigation of a Centrifuagl Compressor Stage with Focus on the Flow in the Pipe Diffuser Supported by Particle Image Velocimetry(PIV) Measurements[R].ASME 2008-GT-51538.
[9] Zachau U, Niehuis R, Hoenen H, et al. Expermental Investigation of the Flow in the Pipe Diffuser of a Centrifugal Compressor Stage under Selected Parameter Variations[R]. ASME 2009-GT-59320.
[10] Kunte R, Schwarz P, Wilkosz B, et al. Experimental and Numerical Investagation of Tip Clearance and Bleed Effects in a Centrifugal Compressor Stage with Pipe Diffuser[R]. ASME 2011-GT-45128.
[11] Kunte R, Jeschke P, Smythe C. Experimental Investigation of a Truncated Pipe Diffuser with a Tandem Deswirler in a Centrifugal Compressor Stage[R]. ASME 2012-GT-68449.
[12] Gould K A, Tan C S, Macrorie M. Characterization of Unsteady Impeller- blade Loading in a Centrifugal Compressor with a Discrete-passage Diffuser[R]. ASME 2007-GT-28002.
[13] Grates D R, Jeschke P, Niehuis R. Numerical Investigation of the Unsteady Flow inside a Centrifugal Compressor Stage with Pipe Diffuser[R]. ASME 2013-GT-95465.
[14] Skoch G J, Prahst P S, Wernet M W, et al. Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller[R].Army Research Laboratory, Lewis Research Center, USA: Technical Report ARLTR-1448, 1997.
[15] McKain T F, Holbrook G J. Coordinates for a High Performance 4:1 Pressure Ratio Centrifugal Compressor[R]. NASA 204134, 1997.(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2013-12-08；修订日期:2014-02-20。基金项目:国际合作专题项目(2014DFR70080)。作者简介:韩戈(1989—),男,博士生,研究领域为叶轮机气动热力学。E-mail:hange898525@sina.com