时域法在压气机转子气动弹性计算中的应用

徐可宁; 王延荣

时域法在压气机转子气动弹性计算中的应用

北京航空航天大学能源与动力工程学院,北京 100191

基金项目: 国家重点基础研究发展计划(2007CB210103)

计量
- 文章访问数: 1423
- HTML浏览量: 1
- PDF量: 9
- 被引次数: 0
出版历程
- 收稿日期: 2010-08-16
- 修回日期: 2010-10-20
- 刊出日期: 2011-01-28

Application of time domain method in aeroelastic computations for compressor rotors

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 发展了用于三维叶轮机气动弹性计算的软件系统AEAS(aeroelastic analysis system).该系统采用时间推进法求解转子叶片的瞬态位移及动应力,以模拟压气机转子中的气动弹性现象.AEAS主要应用于强迫响应分析和颤振分析,强迫响应分析中,在坎贝尔图上共振点对应的工况下,在转子叶片上施加周期性变化的非定常压力场,通过计算动应力的振幅预测转子的危险应力状态;颤振分析中,交替调用结构求解模块和非定常流体求解模块,通过所获得的叶片瞬态动应力预测颤振是否发生.对真实叶片进行气动弹性计算,可以看出所提供的方法和软件系统可以直观地反映流体作用下叶片的振动形式和动应力水平,具有工程应用价值.
- 气动弹性 /
- 强迫响应 /
- 颤振 /
- 时间推进法 /
- 有限单元法
Abstract: An aeroelastic analysis system(AEAS) was been designed to perform aeroelastic analysis for three-dimensional turbomachinery rotor blade models.A time-marching method was applied in AEAS for transient displacement and dynamic stress responses of rotor blades,thus simulating aeroelastic phenomena in compressor rotors.Forced response and flutter analyses modules are two major aeroelastic modules in the AEAS code.In forced response analysis,periodic unsteady pressure field was applied to rotor blades at possible resonances on Campbell diagram to compute the amplitudes of dynamic stresses,therefore dangerous conditions of rotors were assessed.In flutter analysis,the structural solver and the unsteady flow solver were invoked alternately; transient responses of blades were provided to determine whether flutter occurs.Numerical results show good agreement with experimental measurements,indicating that it is possible to obtain dynamic stresses in fluid induced vibration analyses using the time-marching method.
- aeroelasticity /
- forced response /
- flutter /
- time-marching method /
- finite element method

HTML

参考文献(18)

[1]	Spiker M A.Development of an efficient design method for non-synchronous vibrations .North Carolina:Duke University,2008.
[2]	Miyakozawa T.Flutter and forced response of turbomachinery with frequency mistuning and aerodynamic asymmetry .North Carolina:Duke University,2008.
[3]	Mikolajczak A A,Arnoldi R A,Snyder L E,et al.Advances in fan and compressor blade flutter analysis and predictions[J].Journal of Aircraft,1975,12(4):325-332.
[4]	Vahdati M,Sayma A I,Marshall J G,et al.Mechanisms and prediction methods for fan blade stall flutter[J].Journal of Propulsion and Power,2001,17(5):1100-1108.
[5]	Chew J W,Marshall J G,Vahdati M,et al.Part-speed flutter analysis of a wide-chord fan blade[M]//Fransson T H.Unsteady aerodynamics and aeroelasticity of turbomachines.Dordrecht:Kluwer Academic Publishers,1998.
[6]	Doi H.Fluid/structure coupled aeroelastic computations for transonic flows in turbomachinery .California:Stanford University,2002.
[7]	Zienkiewicz O C,Taylor R L.The finite element method[M].Oxford:Butterworth-Heinemann,2000.
[8]	Liu J W H.Modification of the minimum-degree algorithm by multiple eliminations[J].ACM Transactions on Mathematical Software,1985,11(2):141-153.
[9]	Farhat C,Lesoinne M,LeTallec P.Load and motion transfer algorithms for fluid/structure interaction problems with non-matching discrete interfaces:momentum and energy conservation,optimal discretization and application to aeroelasticity[J].Computer Methods in Applied Mechanics and Engineering,1998,157(1-2):95-114.
[10]	Kielb R E,Chiang H D.Recent advancements in turbomachinery forced response analyses .AIAA 92-0012,1992.
[11]	Reddy T S R,Bakhle M A,Srivastava R.A review of recent aeroelastic analysis methods for propulsion at NASA Lewis Research Center .NASA TP-3406,1993.
[12]	Jadic I.Flow-induced vibrations of turbomachinery blades .Arizona:Arizona State University,1997.
[13]	Gill J D,Capece V R.Experimental investigation of flutter in a single stage unshrouded axial-flow fan .AIAA 2004-686,2004.
[14]	Srivastava R,Bakhle M A,Keith T G,Jr.Aeroelastic stability computations for turbomachinery .NASA/TM-2001-210693,2001.
[15]	Srinivasan A V.Flutter and resonant vibration characteristics of engine blades[J].ASME Journal of Engineering for Gas Turbines and Power,1997,119(4):742-775.
[16]	Reddy T S R.LINFLUX-AE:a turbomachinery aeroelastic code based on a 3-D linearized Euler solver .NASA/TM-2004-212978,2004.
[17]	Wilson M J,Imregun M,Sayma A I.The effect of stagger variability in gas turbine fan assemblies[J].Journal of Turbomachinery,2007,129(2):404-411.
[18]	Platzer M F,Carta F O.AGARD manual on aeroelasticity in axial-flow turbomachines .AGARD-AG-298,1987.