进气畸变下压气机叶片强度分析

张明明; 侯安平; 贺小帆; 李绍斌; 梁超

进气畸变下压气机叶片强度分析

1.
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科技重点实验室,北京 100191
2.
北京航空航天大学航空科学与工程学院,北京 100191

基金项目: 国家自然科学基金(60934001)

计量
- 文章访问数: 1613
- HTML浏览量: 88
- PDF量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2009-12-08
- 修回日期: 2010-04-06
- 刊出日期: 2011-01-28

Intensity analysis of blades in axial compressor with inlet distortion

1.
National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China
2.
School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 介绍了一种考核进气畸变对压气机叶片强度影响的分析方法.通过对压气机全周数值模拟,分析进气总压畸变下转子叶片响应的非定常压力场;并对叶片进行模态及应力的有限元分析,研究进气畸变对叶片强度特性的影响.分析表明,周向总压畸变不但会降低压气机效率、稳定裕度等气动稳定性,而且会引起叶片气动力在周向分布的不均匀,对其强度产生重要影响.
- 压气机 /
- 总压畸变 /
- 数值模拟 /
- 叶片强度 /
- 流固耦合
Abstract: A method of examining inlet distortion for intensity of compressor blades was described.A CFD (computational fluid dynamics) modeling of entire compressor flowpath was conducted to analyze the pressure fluctuation on the rotor blades due to inlet total-pressure distortion.A finite element model of the blade was then used to analyze the modal frequencies and stress,providing information on the fatigue failure potential and sensitivity to the imposed distortion.Results show that circumferential total-pressure distortion not only causes the decrease of efficiency and stall margin of compressor,but also leads to nonuniformity of aerodynamic force of blades at different circumferential positions,producing an important influence on the blade intensity.
- compressor /
- total-pressure distortion /
- numerical simulation /
- blade intensity /
- fluid-solid coupling

HTML

参考文献(12)

[1]	Cousins W T,Georges M J,Rezaei H.Inlet distortion testing and analysis of a high-bypass ratio turbofan engine .ISABE Paper 2003-1110,2003.
[2]	Kenyon J A,Rabe D C,Fleeter S.Aerodynamic effects on blade vibratory stress variations[J].Journal of Propulsion and Power,1999,15(5):675-680.
[3]	Awatef H,Keith N.Inlet distortion considerations for high cycle fatigue in gas turbine engine .AIAA 1997-3364,1997.
[4]	Danforth C E.Distortion-induced vibration in fan and compressor blading [J].Journal of Aircraft,1975,12(4):216-225.
[5]	Rabe D,Bolcs A,Russler P.Influence of inlet distortion on transonic compressor blade loading .AIAA 1995-2461,1995.
[6]	Wallace R M,King P S,Kenyon J,et al.Assessing fan and compressor blade HCF sensitivity to non-uniform inlet Flows .ASME GT2004-54264,2004.
[7]	Mihigo J P,Malloy D J,Vining C R,et al.The need to address aeromechanical T&E requirements during engine inlet distortion tseting .ASME GT2009-59009,2009.
[8]	ZHANG Yangfeng,CHU Wuli,LU Xingen.Numerical simulation of the effect of inlet distortion to the subsonic axial-flow compressor .AIAA 2008-77,2008.
[9]	陈美宁,朴英,王大磊.总压进气畸变对压气机转子气动影响的数值模拟[J].航空动力学报,2009,24(8):1793-1798. CHEN Meining,PIAO Ying,WANG Dalei.Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor [J].Journal of Aerospace Power,2009,24(8):1793-1798.(in Chinese)
[10]	陶立权,孙鹏,钟兢军.总压畸变对风扇流场影响的全流道数值研究[J].航空动力学报,2009,24(3):643-651. TAO Liquan,SUN Peng,ZHONG Jingjun.Numerical simulation of full annuls of a transonic fan with distorted inlet [J].Journal of Aerospace Power,2009,24(3):643-651.(in Chinese)
[11]	吴成伟,关振群,郭杏林,等.大型离心压缩机叶轮叶片疲劳可靠性分析[J].装备制造技术,2008(8):1-3. WU Chengwei,GUAN Zhenqun,GUO Xinglin,et al.Fatigue reliability analysis of blades of large centrifugal compressor [J].Equipment Manufacturing Technology,2008(8):1-3.(in Chinese)
[12]	赵少汴,王忠保.抗疲劳设计——方法与数据[M].北京:机械工业出版社,1997.