ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Characteristics analysis of forced vibration response of mistuned cascades
Received date: 2016-12-05
Revised date: 2017-02-26
Online published: 2017-03-20
Supported by
National Natural Science Foundation of China (11172237)
This paper employs a reduced order aerodynamic model based on Computational Fluid Dynamics (CFD), coupled with the structural dynamic equation, to analyze the forced vibration response of the mistuned cascade. The displacement amplitude of the typical transonic cascade in the tuned and mistuned cases are calculated by the proposed method, and the effect of mistuning patterns, mistuning strengths and mass ratios on the forced vibration response amplitude of the mistuned cascade are investigated quantitatively. The results show that the stiffness mistuning patterns in this paper can improve the stability of the cascade, but can also result in the increase of the modal localized level. The maximum vibration amplitude magnification factor has a peak value as the mistuning strength increases or the mass ratio decreases, and the peak value is significantly affected by mistuning patterns. Due to its efficiency in the analysis of the modal localization of the mistuned cascade with forced vibration, the proposed method is beneficial for engineering applications.
ZHANG Weiwei , GAO Yiqi , QUAN Jinlou , SU Dan . Characteristics analysis of forced vibration response of mistuned cascades[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(9) : 521018 -521018 . DOI: 10.7527/S1000-6893.2017.621018
[1] LIM S H, BLADH R, CASTANIER M P, et al. Compact, generalized component mode mistuning representation for modeling bladed disk vibration[J]. AIAA Journal, 2007, 45(9):2285-2298.
[2] MARTEL C, CORRAL R. Asymptotic description of maximum mistuning amplification of bladed disk forced response[J]. Journal of Engineering for Gas Turbines and Power, 2009, 131(2):601-610.
[3] PIERRE C, SMITH T E, MURTHY D V. Localization of aeroelastic modes in mistuned high-energy turbines[J]. Journal of Propulsion and Power, 1994, 10(3):318-328.
[4] CAMPOBASSO M S, GILES M B. Analysis of the effect of mistuning on turbomachinery aeroelasticity[C]//Proceedings of the IX International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity in Turbomachines. Grenoble:Presses Universitaires de Grenoble, 2000:885-896.
[5] CHOL B K, LENTZ J, RIVAS-GUERRA A J, et al. Optimization of intentional mistuning patterns for the reduction of the forced response effects of unintentional mistuning:Formulation and assessment[J]. Journal of Engineering for Gas Turbines and Power, 2003, 125(1):131-140.
[6] 廖海涛, 王建军, 李其汉. 随机失谐叶盘结构失谐特性分析[J]. 航空动力学报, 2010, 25(1):160-168. LIAO H T, WANG J J, LI Q H. Mistuning characteristics analysis of mistuned bladed disk assemblies[J]. Journal of Aerospace Power, 2010, 25(1):160-168(in Chinese).
[7] 于长波, 王建军, 李其汉. 失谐叶盘结构的概率响应局部化特性[J]. 航空动力学报, 2010, 25(9):2006-2012. YU C B, WANG J J, LI Q H. Probability characteristics for response localization of mistuned bladed disk assemblies[J]. Journal of Aerospace Power, 2010, 25(9):2006-2012(in Chinese).
[8] PETROV E P. Reduction of forced response levels for bladed discs by mistuning:Overview of the phenomenon[J]. Journal of Engineering for Gas Turbines and Power, 2011, 133(7):1039-1051.
[9] BLEEG J M, YANG M T, ELEY J A. Aeroelastic analysis of rotors with flexible disks and alternate blade mistuning[J]. Journal of Turbomachinery, 2009, 131(1):1-9.
[10] 臧朝平, 段勇亮, PETROV E P. 失谐叶片轮盘的减缩建模及动力响应预测方法[J]. 航空学报, 2015, 36(10):3305-3315. ZANG C P, DUAN Y L, PETROV E P. Reduced-order modelling and dynamic response prediction method for mistuned bladed disks[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(10):3305-3315(in Chinese).
[11] HE Z J, EPUREANU B I, PIERRE C. Fluid-structural coupling effects on the dynamics of mistuned bladed disks[J]. AIAA Journal, 2007, 45(3):552-561.
[12] PETROV E P. A method for forced response analysis of mistuned bladed disks with aerodynamic effects included[J]. Journal of Engineering for Gas Turbines and Power, 2010, 132(6):1-10.
[13] REDDY T S R, MIN J B, TRUDELL J J. Mistuned bladed disk analysis with unsteady aerodynamics using turbo-REDUCE[C]//Proceedings of the 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structual Dynamics & Materials Conference. Reston, VA:AIAA, 2005.
[14] SADEGHI M, LIU F. Computation of mistuning effects on cascade flutter[J]. AIAA Journal, 2001, 39(1):22-28.
[15] 郑赟, 王静. 错频对叶片的气动弹性稳定性的影响[J]. 航空动力学报, 2013, 28(5):1029-1036. ZHENG Y, WANG J. Influence of frequency mistuning on aeroelastic stability of blade[J]. Journal of Aerospace Power, 2013, 28(5):1029-1036(in Chinese).
[16] SADEGHI M, LIU F. Investigation of mistuning effects on cascade flutter using a coupled method[J]. Journal of Propulsion and Power, 2007, 23(2):266-272.
[17] 苏丹, 张伟伟, 张陈安, 等. 基于系统辨识技术的叶轮机非定常气动力建模方法[J]. 航空学报, 2012, 33(2):242-248. SU D, ZHANG W W, ZHANG C A, et al. An unsteady aerodynamic modeling for turbomachinery based on system identification[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(2):242-248(in Chinese).
[18] 苏丹, 张伟伟, 全金楼, 等. 基于CFD计算的高效叶栅耦合颤振分析方法[J]. 航空学报, 2014, 35(12):3232-3243. SU D, ZHANG W W, QUAN J L, et al. An efficient coupled method of cascade flutter analysis by using CFD technique[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(12):3232-3243(in Chinese).
[19] SU D, ZHANG W W, YE Z Y. A reduced order model for uncoupled and coupled cascade flutter analysis[J]. Journal of Fluids and Structures, 2016, 61:410-430.
[20] BÖLCS A, FRANSSON T H. Aeroelasticity in turbomachines-Comparison of theoretical and experimental cascade results[R]. Lausanne:Communication du LTATEPEL, 1986.
[21] 王建军, 李其汉, 朱梓根. 失谐叶片-轮盘结构系统振动局部化问题的研究进展[J]. 力学进展, 2000, 30(4):517-528. WANG J J, LI Q H, ZHU Z G. Vibratory localization of mistuned bladed disk assemblies-A review[J]. Advances in Mechanics, 2000, 30(4):517-528(in Chinese).
[22] CASTANIER M P, PIERRE C. Investigation of the combined effects of intentional and random mistuning on the forced response of bladed disks:AIAA-1998-3720[R]. Reston, VA:AIAA, 1998.
/
〈 | 〉 |