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建立了航空发动机高压转子的动力学模型,该模型包含所有的结构动力学设计参数,揭示了设计参数与转子振动特性间的关系,提出了转子临界转速界值的估计方法,并予以理论证明.建立了分别基于两阶临界响应的支承刚度设计准则.发现了转子参数临界转速现象,在参数临界转速处,阻尼器将失去阻尼作用,振动趋于无穷大;给出了参数临界转速出现的条件,上述的结论对于航空发动机高压转子的设计具有重要的指导意义.
The dynamic model of aeroengine high-pressure rotor is established. The model includes all the structural dynamic design parameters, reveals the relationship between the design parameters and rotor vibration characteristics, and proposes a method to estimate the critical speed of the rotor, and proves it theoretically. The design criteria of the bearing stiffness based on the second order critical response are respectively established. The critical speed of the rotor is found. At the critical speed, the damper will lose its damping effect and the vibration tends to infinity. The critical speed of the parameter is given, The above conclusion has important guiding significance for the design of aero-engine high-pressure rotor.