航空发动机高压转子"可容模态"设计及实验验证

In order to reduce the vibration of aero-engine high pressure rotor, and improve the tolerability to complex working conditions, a dynamical model simulating high pressure rotor with two dampers was established, based on which modal and response analysis were carried out, and effect laws of key structural parameters on workable mode were studied. Tolerability evaluation function η was constructed, and workable mode design method was established. A test rig simulating high pressure rotor was designed. The accuracy of calculation model and method were verified by modal checking experiments, and the feasibility of design method was proved by workable mode experiments. According to research findings, method that using equivalent critical speed ω to estimate the first two critical speeds of high pressure rotor system is feasible, with the critical speeds of test rig satisfying relational expression ω_crl≤ωˉ andωˉ≤ω_cr2≤2ωˉ. The continuous resonance time at the first two order workable modes of test rig are no less than 7125s. The peaks of vibration displacement at key positions are less than 79.42μm, and effective values of vibration velocity are less than 2.33mm/s, with the relative fluctuations less than 10.59%. The results indicate that the workable mode design method of aero-engine high pressure rotor established is effective.