前后掠风扇叶片颤振特性对比分析
Comparison of flutter characteristics of forward/ backward swept fan blades
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摘要: 采用基于能量法的流固耦合数值预测方法对比研究了模态、叶间相位角对前后掠风扇转子叶片气动弹性稳定性的影响.结果表明:对于两种掠形叶片,在所研究的前3阶振动模态下,前掠叶片对应于弯扭耦合振型的气动模态阻尼比最大,其数值为0.801%,而后掠叶片对应于弯扭耦合振型的气动模态阻尼比最小,其数值为0.248%;叶间相位角对两种掠形叶片气动模态阻尼比都有显著影响,在1阶振动模态相同叶间相位角(节径)下,前掠叶片前行波对应的气动模态阻尼比小于逆行波对应的气动模态阻尼比,而后掠叶片与此相反;1阶振动模态所有叶间相位角下,前掠叶片比后掠叶片气弹稳定性更好.Abstract: The effects of mode shape and inter blade phase angle(IBPA) on aeroelasticity stability of forward and backward swept blades were investigated through numerical flutter analysis and comparison based on the energy method.Results show that,for the first three vibration modes,aerodynamic modal damping ratio(AMDR) of forward swept blades corresponding to the coupling mode has the highest value of 0.801%,and that of backward swept blades corresponding to the coupling mode has the lowest value of 0.248%.IBPA has significant effects on AMDR for two kinds of swept blades.AMDR corresponding to forward travelling wave is lower than that corresponding to backward travelling wave for forward swept blades vibration in the 1st flapping mode at the same IBPA,while it is contrary for the backward swept blades;forward swept blades have better aeroelasticity than backward swept ones at arbitrary IBPA when blades vibrate in the 1st flapping mode.
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Key words:
- forward swept /
- backward swept /
- flutter /
- energy method /
- mode shape /
- inter blade phase angle
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[1] Amano R S,Xu C.Blade swept effects of turbomachinery [R].AIAA-2005-48,2005. [2] 陈懋章.风扇/压气机技术发展和对今后工作的建议[J].航空动力学报,2002,17(1):1-15. CHEN Maozhang.Development of fan/compressor techniques and suggestions on further researches[J].Journal of Aerospace Power,2002,17(1):1-15.(in Chinese) [3] Carta F O.Coupled blade-disk-shroud flutter instabilities in turbojet engine rotors[J].Journal of Engineering for Power,1967,89(3):419-426. [4] Marshall J M,Imregun M.A review of aeroelasticity methods with emphasis on turbomachinery applications[J].Journal of Fluids and Structures,1996,10(3):237-267. [5] 张小伟,王延荣,徐可宁.叶轮机械叶片颤振的影响参数[J].航空动力学报,2011,26(7):1557-1562. ZHANG Xiaowei,WANG Yanrong,XU Kening.Effects of parameters on blade flutter in turbomachinery[J].Journal of Aerospace Power,2011,26(7):1557-1562.(in Chinese) [6] Bakhle M A,Srivastava R,Keith T G,et al.A 3D Euler/Navier-Stokes aeroelastic code for propulsion applications [R].AIAA-97-2749,1997. [7] Reddy T S R,Bakhle M A,Trudell J J,et al.LINFLUC-AE:a turbomachinery aeroelastic code based on a 3-D linearizd Euler solver [R].NASA/TM-2004-212978,2004. [8] 徐可宁.叶轮机械叶盘结构气动弹性算法研究及程序实现 [D].北京:北京航空航天大学,2011. XU Kening.On the algorithm of aeroelasticity and the program implementation of bladed disk assemblies in turbomachines [D].Beijing:Beijing University of Aeronautics and Astronautics,2011.(in Chinese) [9] 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[J].航空动力学报,2011,26(1):191-198. XU Kening,WANG Yanrong.Application of time domain method in aeroelastic computations for compressor rotors[J].Journal of Aerospace Power,2011,26(1):191-198.(in Chinese) [10] 徐可宁,王延荣.压气机转子叶片的气动弹性数值模拟[J].航空动力学报,2010,25(10):2206-2210. XU Kening,WANG Yanrong.Numerical simulation of aeroelastic response in compressor rotor blades[J].Journal of Aerospace Power,2010,25(10):2206-2210.(in Chinese) [11] 张小伟,王延荣,张潇,等.涡轮机械叶片的流固耦合数值计算方法[J].航空动力学报,2009,24(7):1622-1626. ZHANG Xiaowei,WANG Yanrong,ZHANG Xiao,et al.Numerical method for fluid- structure interaction in turbomachinery bladings[J].Journal of Aerospace Power,2009,24(7):1622-1626.(in Chinese) [12] 张小伟,王延荣,徐可宁.压气机转子叶片颤振边界的预测方法[J].航空动力学报,2011,26(2):392-396. ZHANG Xiaowei,WANG Yanrong,XU Kening.Prediction method of blade flutter boundary in a compressor stage[J].Journal of Aerospace Power,2011,26(2):392-396.(in Chinese) [13] Kielb R E,Chiang H D.Recent advancements in turbomachinery forced response analysis [R].AIAA Paper 92-0012, 1992. [14] Moffatt S,He L.Blade forced response prediction for industrial gas turbines:Part Ⅰmethodologies [R].ASME Paper GT-2003-38640,2003. [15] Li H D,He L.Single-passage analysis of unsteady flows around vibrating blades of a transonic fan under inlet distortion[J].ASME Journal of Turbomachinery,2002,124(2):285-292. [16] 张小伟.叶轮机械叶片气动弹性稳定性数值预测方法研究 [D].北京:北京航空航天大学,2011. ZHANG Xiaowei.Numerical prediction method for aeroelastic stability of blades in turbomachines [D].Beijing:Beijing University of Aeronautics and Astronautics,2011 (in Chinese)
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