Workable mode design and experimental verification of aero-engine low-pressure rotor system
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摘要: 建立了带弹性支承和阻尼器的航空发动机低压柔性转子动力学模型，进行了模态计算以及临界转速处的响应计算。在考虑临界转速约束与“临界跟随”现象约束的条件下，综合模态不平衡影响因子、弹支应变能占比以及套齿连接结构稳定性构造了可容度评价函数，建立了低压转子系统的“可容模态”优化设计方法。设计并搭建了低压转子实验系统，从模态测试实验、阻尼器减振实验以及长时间“共振”实验，验证了设计方法的可靠性。研究结果为计算的临界转速与实际测量的临界转速最大误差为3.86%，阻尼器在1阶与2阶临界转速处的减振比最大可达45.6%，实验转子系统在1阶与2阶临界转速处各完成了长达412.5 s和429.8 s的“共振”实验，共振过程中转子系统各通道振动单峰值稳定在100 μm以内，且无次谐波产生。表明了所建立的航空发动机低压转子系统“可容模态”优化设计方法是可行的。Abstract: A dynamic model of aero-engine low-pressure flexible rotor with elastic supports and dampers was established，the modal and critical speed responses were calculated.Under the condition of considering the constraint of critical speed and the constraint of “critical following”phenomenon，the influence factors of modal imbalance，the proportion of spring-supported strain energy，and the stability of the sleeve-tooth connection structure were synthesized to construct a tolerance evaluation function，and a “workable mode” optimization design method for the low-pressure rotor system was established.The low-pressure rotor experimental system was designed and established，and the reliability of the design method was verified from the modal test experiment，damper damping experiment and long-term “resonance” experiment.The study results indicated that the maximum error between the calculated critical speed and the actual measured critical speed did not exceed 3.86%.The maximum damping ratio of the damper at the first and second critical speeds can reach 45.6%.The experimental rotor system completed 412.5 s and 429.8 s “resonance” experiment at the first and second critical speeds，and the rotor system of each channel vibration peak kept stable within 100 μm during the resonance process without sub-harmonic generation.The results show that the established optimization design method of “capacity mode” for aero-engine low-pressure rotor system is feasible.
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