| Citation: | LUO Chuwei, CHEN Jiang, XU Ning, et al. Numerical analysis on blade failure induced by strut wake in axial compressor[J]. Journal of Aerospace Power, 2022, 37（11）：2617-2626 doi: 10.13224/j.cnki.jasp.20220293
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To explore the reasons for fatigue failure of inlet guide vane (IGV) downstream the strut in the transition section of a gas turbine compressor, unsteady numerical simulation and one-way fluid-structure coupling methods were used to analyze the effects of strut on unsteady flow in 1.5 stages high-pressure compressor and forced response characteristics of the IGV. Furthermore, the analysis results were checked by fatigue strength experiments. The results showed that the isentropic efficiency in the design point of compressor was reduced by 3.6 percent points compared with the model without strut. Vortex shedding alternately at the trailing edge of the strut caused the inlet attack angle of the IGV to deviate from the design value, resulting in a decrease in aerodynamic performance and a significant increase in the unsteady pressure pulsation on the IGV surface. With the increase of circumferential distance between IGV and strut, the influence of strut on IGV first increased and then decreased rapidly. The perturbation frequency resulted from the shedding vortex was relatively disperse, and the low-order resonance of IGV induced by the low frequency component was the fundamental reason of the fatigue failure of IGV; the maximum vibration stress can reach 400 MPa. The numerical simulation results were consistent with the experiment, proving the reliability of the simulation.
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