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%。
An efficient novel method for calculating the transient forced response of mistuned blades discs is proposed in this paper, which is different from the traditional numerical integration method. Firstly, the reduced-order modeling is used to reduce the number of degrees of freedom of the large-scale finite element model of the bladed disks which can accurately describe the dynamic characteristics of the blade disk structure. Secondly, In the case of the accelerated turbine blade passing through a complex flow field, the aerodynamic loads on the blade surface are simulated with considering the influence of rotation speed on the natural frequency and mode shapes of the mistuned bladed disk. The rotational speed range of blade disc resonance is analyzed by resonance analysis and the excitation order components that cause resonance. Finally, the transient forced responses and amplitude amplifications are numerically studied when the resonance regimes are passed during gas-turbine engine acceleration. The influence of the excitation force of different rotation acceleration on the transient amplitude amplification factor is illustrated by a large number of the computational results and comparative analysis. The results of a turbine bladed disks composed of 86 blades show that the amplitude of the transient forced response decreases with the increasing of the rotation acceleration and the transient amplification factor of mistuned blades discs is 30% larger than the steady state with the same damping.
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