失谐叶栅的受迫振动响应特性分析
收稿日期: 2016-12-05
修回日期: 2017-02-26
网络出版日期: 2017-03-20
基金资助
国家自然科学基金（11172237）
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)
采用基于计算流体力学（CFD）方法的降阶气动力模型并耦合结构运动方程，实现了存在外激励载荷时失谐叶栅受迫振动响应的快速分析。针对典型的跨声速叶栅，通过求解其位移响应幅值较系统地研究了失谐方式、失谐强度和叶片质量比对失谐叶栅受迫振动响应幅值的影响。研究表明文中刚度失谐形式可以改善叶栅振动的稳定性，同时导致系统受迫振动响应局部化程度的增加，并且受迫响应的最大振幅放大因子随失谐强度增加或者质量比降低存在先增大后减小的一个峰值，不同失谐形式则对这个峰值的大小有着明显的影响。由于该方法可高效地分析失谐叶栅受迫振动各参数对模态局部化的影响，在工程上有一定的应用价值。
关键词： 计算流体力学(CFD); 降阶模型(ROM); 流固耦合; 失谐; 受迫响应
张伟伟 , 高弈奇 , 全金楼 , 苏丹 . 失谐叶栅的受迫振动响应特性分析[J]. 航空学报, 2017 , 38(9) : 521018 -521018 . DOI: 10.7527/S1000-6893.2017.621018
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.
[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.
/
| 〈 |
|
〉 |
CJA