航空学报 > 2021, Vol. 42 Issue (9): 224529-224529   doi: 10.7527/S1000-6893.2021.24529

复杂时变激励下失谐叶盘瞬态强迫响应分析

敬彤1, 臧朝平1, 张涛2, Yevgen Pavlovich PETROV3   

  1. 1. 南京航空航天大学 能源与动力学院, 南京 210016;
    2. 中国航空发动机集团有限公司 中国燃气涡轮研究院, 成都 610500;
    3. 英国萨塞克斯大学, 伦敦 BN1 9RH
  • 收稿日期:2020-07-11 修回日期:2020-08-19 发布日期:2021-09-29
  • 通讯作者: 臧朝平 E-mail:c.zang@nuaa.edu.cn
  • 基金资助:
    国家自然科学基金(12072146);国家自然科学基金委员会与中国工程物理研究院联合基金(U1730129)

Transient forced response analysis of mistuned bladed disks under complex time-varying excitation

JING Tong1, ZANG Chaoping1, ZHANG Tao2, Yevgen Pavlorich PETROV3   

  1. 1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. China Gas Turbine Establishment, Aero-Engine Corporation of China, Chendu 610500, China;
    3. University of Sussex, London BN1 9RH, United Kingdom
  • Received:2020-07-11 Revised:2020-08-19 Published:2021-09-29
  • Supported by:
    National Natural Science Foundation of China(12072146);National Natural Science Foundation of China and National Safety Academic Foundation of China (U1730129)

摘要: 提出一种高效的失谐叶盘瞬态强迫响应分析方法,不同于传统的数值积分方法,该方法推导出瞬态强迫响应的解析表达式,能更为高效地预测失谐叶盘的瞬态强迫响应。首先,对叶盘的高保真有限元模型进行减缩建模,在精确地描述叶盘结构的动力学特性的前提下,极大的减少了模型的自由度数目。其次,模拟加速旋转的涡轮叶盘经过复杂流场时叶片表面上的气动载荷,并建立叶盘固有频率和振型随转速变化的数学函数;通过共振分析确定叶盘共振的转速区间并分析引起共振的激励阶次成分。最后,计算了不同旋转加速度和阻尼下叶盘的瞬态强迫响应,并对叶盘的失谐幅值放大因子进行研究。应用本办法对某86个叶片的涡轮叶盘进行了数值分析,结果表明,相同阻尼水平下,叶盘的瞬态强迫响应幅值随旋转加速度增加而降低,失谐幅值放大因子在瞬态条件下大于稳态条件下,最高可达30%。

关键词: 失谐叶盘, 减缩建模, 瞬态强迫响应, 复杂激励, 变转速

Abstract: An efficient novel method different from the traditional numerical integration method is proposed for transient forced response calculation of mistuned bladed disks. Firstly, under the premise of accurate description of the dynamic structure characteristics of the bladed disk, the number of degrees of freedom of the large-scale finite element model of the bladed disk is reduced using the reduced-order modeling. The blade surface aerodynamic loads are then simulated when the accelerated turbine blades pass through a complex flow field, considering the influence of rotation speed on the natural frequency and mode shapes of the mistuned bladed disk. The resonance analysis determines the rotational speed range of the bladed disk resonance and analyzes the excitation order components causing resonance. Finally, the transient forced responses and amplitude amplifications are numerically studied. The effect of the excitation force of different rotation accelerations on the transient amplitude amplification factor is illustrated by a large number of computational results and comparative analyses. The results of a turbine bladed disk composed of 86 blades show that the amplitude of the transient forced response decreases with the increase of the rotation acceleration, and that the transient amplification factor of the mistuned bladed disk is 30% larger than that in the steady state with the same damping.

Key words: mistuned bladed disks, reduced-order modeling, transient forced response, complex excitation, varying rotation speeds

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