转子涡动对旋转冲压转子进气道起动及性能的影响 *

推进技术 ›› 2014, Vol. 35 ›› Issue (10): 1333-1341.

转子涡动对旋转冲压转子进气道起动及性能的影响 *

亢维佳,刘占生,卢江波,王　羽,张广辉

哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001;哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001;哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001;哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001;哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:亢维佳(1986—)，男，博士生，研究领域为动力机械、转子动力学、设备故障诊断。
基金资助:
国家自然科学基金资助项目(51106035)。

Effects of Rotor Whirl on Starting Ability and Flow

School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China;School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China;School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China;School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China;School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获取转子涡动作用下旋转冲压转子进气道起动及性能的变化规律，对旋转冲压转子涡动时压缩进气道的内部流场进行了数值仿真，分析了转子不同涡动幅值条件下旋转冲压转子进气道的起动转速及性能变化。研究结果表明，转子涡动对旋转冲压转子进气道起动及性能具有显著的影响。旋转冲压转子进气道的稳定工作范围随着转子涡动幅值的增大而逐渐减小。转子涡动幅值对旋转冲压转子进气道性能的影响存在极值点。当涡动幅值小于该极值点e=100μm时，进气道的流动性能良好。旋转冲压转子在定工况运行时，旋转冲压转子进气道流动稳定性随着转子涡动幅值的减小而增强。

关键词: 旋转冲压转子；转子涡动；进气道起动；性流动能；稳定性

Abstract: In order to obtain the variation of starting ability and performance of inlet flow field under rotor whirl，the compression inlet flow field of Rampressor rotor is simulated based on rotor whirl. Starting speed and flow performance of Rampressor inlet are analyzed under different rotor whirl amplitude. The results show that rotor whirl has significant effect on starting ability and performance of Rampressor rotor inlet. Along with the increment of rotor whirl amplitude，the stable working range of Rampressor rotor inlet is reduced. The effect of rotor whirl on flow performance of Rampressor inlet has an extreme point. When rotor whirl amplitude is less than this extreme point e=100μm，flow performance of Rampressor inlet gets better. On the constant operation condition of Rampressor rotor，flow stability of Rampressor inlet heightens with the increase of rotor whirl amplitude.

Key words: Rampressor rotor；Rotor whirl；Inlet starting；Flow performance；Stability

亢维佳,刘占生,卢江波,王　羽,张广辉. 转子涡动对旋转冲压转子进气道起动及性能的影响 *[J]. 推进技术, 2014, 35(10): 1333-1341.

KANG Wei-jia,LIU Zhan-sheng,LU Jiang-bo,WANG Yu,ZHANG Guang-hui. Effects of Rotor Whirl on Starting Ability and Flow[J]. Journal of Propulsion Technology, 2014, 35(10): 1333-1341.

参考文献

[1] Lawlor S P, Hinkey J B, Mackin S G, et al. Supersonic Compressor Stage Design & Test Results[R].IMECE 2004-59914.
[2] Lawlor S P, Baldwin P. Conceptual Design of a Supersonic CO₂ Compressor [R]. ASME 2005-GT-68349.
[3] Grosvenor A D, Taylor D A, Bucher J R, et al. Measured and Predicted Performance of a High Pressure Ratio Supersonic Compressor Rotor [R].ASME 2008-GT-50150.
[4] Ramgen Power Systems Inc. Ramgen Engine Technology Overview Briefing [EB/OL]. http: // www.netl.doe.gov/Publications /proceedings /02 /turbines /steele.pdf,2002-03.
[5] 钟兢军, 韩吉昂, 杨凌. 旋转冲压压缩转子研究进展及发展前景 [J]. 航空动力学报, 2011, 26(10): 2293-2301.
[6] 钟兢军, 韩吉昂. 旋转冲压压缩转子的研究进展及发展前景[C]. 贵阳: 中国航空学会第七届动力年会论文摘要集, 2010.
[7] 亢维佳. 旋转冲压转子气流激振力作用下的动力学响应[D]. 哈尔滨: 哈尔滨工业大学, 2011.
[8] Grosvenor A D. RANS Prediction of Transonic Compressive Rotor Performance Near Stall [R]. ASME 2007-GT-27691.
[9] Tindell R H, Willis B P. Experimental Investigation of Blowing for Controlling Oblique Shock/Boundary Layer Interactions [R]. AIAA 1997-2642.
[10] Strazisar A J, Bright M M, Thorp S, et al. Compressor Stall Control Through Endwall Recirculation [R].ASME 2004-GT-54295.
[11] Shawn Lawlor. CO₂ Compression Using Supersonic Shock Wave Technology[R].Ramgen Power Systems, Project NT42651.
[12] 鲍文, 常军涛, 郭新刚, 等. 超燃冲压发动机进气道不起动仿真研究 [J]. 航空动力学报, 2005, 20(5):731-735.
[13] 袁化成, 梁德旺. 高超声速侧压式模型进气道不起动特性分析 [J]. 南京航空航天大学学报, 2004, 36(6):683-687.
[14] YU Daren, CHANG Juntao, BAO Wen, et al. Optimal Classifications Criterions of Hypersonic Inlet Start/Unstart [J]. Journal of Propulsion and Power, 2007, 23 (2).
[15] 于达仁, 何保成, 吕晓武, 等. 旋转冲压发动机进气道压比特性分析 [J]. 推进技术, 2008, 29(3):329-333.(YU Da-ren, HE Bao-cheng, LV Xiao-wu, et al. Characteristics Analysis of Pressure Ratios for Rotated Ramjet Inlets [J]. Journal of Propulsion Technology, 2008, 29 (3):329-333.)
[16] 刘占生, 亢维佳, 张广辉, 等. 气流激振力作用下旋转冲压转子动力学响应 [J]. 振动与冲击, 2013, 32(3):150-156.
[17] Bogar, T J, Sajben M, Kroutil J C. Characteristic Frequencies of Transonic Diffuser Flow Oscillations[J]. AIAA Journal, 1983, 21(9): 1232-1240.
[18] Allan D Grosvenor, Paul M Brown, Shawn P Lawlor. Design Methodology and Predicted Performance for a Supersonic Compressor Stage[R].ASME 2006-GT-90490.
[19] 韩吉昂, 严红明, 钟兢军, 等. 旋转冲压压缩转子二维进气流道数值研究[J]. 航空动力学报, 2008, 23(6):1054-1060.
[20] 彭泽琰, 刘刚. 航空燃气轮机原理(上册)[M]. 北京: 国防工业出版社, 2000.
[21] Kyung Jin Ryu, Seol Lim, Sang Dug Kim, et al. A Computational Study on the Effect of Angles of Attack on a Double-Cone Type Supersonic Inlet with Bleeding System[R]. ASME 2010-GT-23221.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2013-10-09；修订日期:2013-11-27。基金项目:国家自然科学基金资助项目(51106035)。作者简介:亢维佳(1986—),男,博士生,研究领域为动力机械、转子动力学、设备故障诊断。E-mail:kwj1221@163.com