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.
JING Tong
,
ZANG Chaoping
,
ZHANG Tao
,
Yevgen Pavlorich PETROV
. Transient forced response analysis of mistuned bladed disks under complex time-varying excitation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021
, 42(9)
: 224529
-224529
.
DOI: 10.7527/S1000-6893.2021.24529
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