小流量多级高负荷轴流压气机设计

解亚东; 单鹏

小流量多级高负荷轴流压气机设计

解亚东,
单鹏

北京航空航天大学能源与动力工程学院, 北京 100191

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出版历程
- 收稿日期: 2011-10-14
- 刊出日期: 2012-09-28

Design research of small flow rate multi-stage high-loaded axial compressor

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100019, China

摘要

摘要: 以增压比为6的国外某小流量5级轴流压气机为设计原型,在不超过其前3级的轴向长度的条件下,设计了3级轴流压气机,研究其最大增压能力.在采用了正预旋、静子端弯、第2、3级转子叶尖适度斜流等措施后,3级轴流的设计点流量为5.80kg/s,增压比为5.445,效率为0.8272,喘振裕度为11.8%,3级平均级增压比为1.759.研究结果表明:在一定的轴向长度限制下,小流量3级轴流压气机虽可以达到5.5量级的增压比,但其流量特性曲线已经变得很陡峭.
- 轴流压气机设计 /
- 小流量压气机 /
- 多级压气机 /
- 高负荷 /
- 端弯
Abstract: The pressure ratio of a five stage foreign compressor with small flow rate is 6.On condition that not exceeding its pre three stage axial length,a three stage compressor was designed and its maximum pressurizing ability was researched.By using positive pre-whirl,end-bend stator and the measure that properly boosted the shroud of the second and third stages,the design result of this three stage compressor was that the mass flow rate was 5.80kg/s,pressure ratio was 5.445,efficiency was 0.8272,surge margin was 11.8%,and average stage pressure ratio was 1.759.On condition that not exceeding the limit of a certain axial length,the small flow three stages got the pressure level of 5.5.The flow characteristic curve has been cliffy.
- axial compressor design /
- small mass flow ratio compressor /
- multi-stage compressor /
- high-loaded axial compressor /
- end-bend

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参考文献(15)

[1]	陈懋章.叶轮机气动力学研究及其发展趋势//中国航空学会航空百年学术论坛动力分坛论文集:一.北京:中国航空学会动力专业分会,2003:17-39.
[2]	周拜豪,程荣辉,尹红顺,等.带箍高性能两级风扇设计//中国航空学会2007学术年会:动力专题50.深圳:中国航空学会动力专业分会,2007:1-13.
[3]	温泉.一台高负荷小流量轴流压气机的三维粘性数值模拟//FLUENT第一届中国用户大会文集.北京:, 2001.
[4]	《世界中小型航空发动机手册》编委会.世界中小型航空发动机手册[M].北京:航空工业出版社,2006.
[5]	单鹏,桂幸民,周盛,等.高负荷后掠风扇设计若干问题[J].工程热物理学报,1999,20(5):576-579. SHAN Peng,GUI Xinmin,ZHOU Sheng,et al.Fundamental considerations on high loading backward swept fan design[J].Journal of Engineering Thermophysics,1999,20(5):576-579.(in Chinese)
[6]	Wennerstrom A J.Low aspect ratio axial flow compressor:why and what it means[J].ASME Journal of Turbomachinery,1989,111(4):357-365.
[7]	赵斌,徐鹏飞,刘宝杰.高负荷风扇气动设计:转子叶尖参数选取分析[J].航空动力学报,2010,25(11):2564-2570. ZHAO Bin,XU Pengfei,LIU Baojie.Aerodynamic design of highly loaded fan:analysis of rotor tip parameter selection[J].Journal of Aerospace Power,2010,25(11):2564-2570.(in Chinese)
[8]	Hah C,Wennerstorm A J. Three-dimensional flowfield inside a transonic compressor with swept blades[J].ASME Journal of Turbomachinary,1991,113(1):241-250.
[9]	Sellin M D,Puterbaugh S L,Copenhaver W W.Tip shock structure in transonic compressor rotor. AIAA 93-1869,1993.
[10]	Wennerstrom A J.Design of highly loaded axial-flow fans and compressors[M].Vermont,USA:Edwards Brothers Incorporated,2000.
[11]	张永军,王会社,徐建中,等.扩压叶栅中弯叶片的作用气动机理的探究[J].工程热物理学报,2008,29(9):1471-1474. ZHANG Yongjun,WANG Huishe,XU Jianzhong,et al.Investigation on aerodynamics mechanism of bowed blade in diffusioncascade[J].Journal of Engineering Thermophysics,2008,29(9):1471-1474.(in Chinese)
[12]	周亚峰,胡国荣.某风扇试验件的性能计算与分析[J].航空发动机,2003,30(4):10-13. ZHOU Yafeng,HU Guorong.Performance caculation and analysis of a fan rig[J].Aeroengine,2003,30(4):10-13.(in Chinese)
[13]	周拜豪,尹红顺,苏延铭,等.高性能前掠三级轴流风扇的设计与研究[J].燃气涡轮实验与研究,2008,21(2):1-8.(in Chinese) ZHOU Baihao,YI Hongshun,SU Yanming,et al.Design and experiment of a high performance three-stage axial fan with forward swept blades[J].2008,21(2):1-8.(in Chinese)
[14]	单鹏.超跨音轴流压气机前缘掠弯的运动学问题. 北京:北京航空航天大学,1996. SHAN Peng.Kinematic problems of leading edge supersonic sweep-bend in supersonic and transonic axial compressors. Beijing:Beijing University of Aeronautics and Astronautics,1996.(in Chinese)
[15]	单鹏,桂幸民.单级后掠风扇ATS-2设计与实验研究最终报告. 北京:北京航空航天大学,GF-A0041935,2000.