| Citation: | FANG Mingchang, WANG Yanrong. Forced response analysis of mistuned bladed disk with aerodynamic damping[J]. Journal of Aerospace Power, 2022, 37（10）：2224-2232 doi: 10.13224/j.cnki.jasp.20220266
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The forced response of the mistuned bladed disk was analyzed by use of the fundamental mistuning model (FMM) combined with the influence coefficient method. The finite element method and computational fluid dynamics method were used to obtain the modal results and aerodynamic influence coefficients of the tuned bladed disk, and then the FMM considering aerodynamic damping was constructed. The modal frequency, mode shape and damping ratio of the mistuned bladed disk were obtained by solving the matrix eigenvalues, and then the modal superposition method was used to calculate the forced response of the mistuned bladed disk under traveling wave excitation. The above method was used to calculate the forced responses of various intentional mistuned bladed disks before and after the superposition of random mistuning. Results indicated that the forced response of the mistuned bladed disk decreased significantly after considering aerodynamic damping. Taking the alternating mistuned bladed disk as an example, the forced response can be reduced by increasing the mistuning value within an appropriate range. The frequency difference between adjacent blades of the model should be 6%, and the corresponding mistuning value was 4.32. In addition, increasing the frequency difference between adjacent blades with an interval of one blade can further reduce the forced response.
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