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航空发动机工作过程中,转子叶片的工作环境较为恶劣,会无法避免地受到气动和机械等载荷的激励作用而引发强迫振动,特别是当载荷频率与叶片的动频相同时就会使叶片共振、应力增大甚至造成叶片破坏,故准确获得叶片在不同转速时的动频就显得尤为重要。根据叶片的受力分析,通过引入叶片的变形系数,建立了叶片的自由振动方程。然后利用Ritz-Galerkin方法得到了一种可以计算叶片静频和动频的数值方法,计算结果与实验测量结果比较接近。本文方法与现有相关方法相比,其特点在于所建立的叶片振动方程与实际情况更趋相符,计算简便、结果可靠,并具有一定的工程应用价值。
During the operation of aeroengine, the working environment of the rotor blades is rather harsh, and will inevitably be forced by the aerodynamic and mechanical loads to induce forced vibration. In particular, when the load frequency is the same as that of the blades, the blades will resonate, Increasing the stress or even causing damage to the blade, so it is particularly important to accurately obtain the frequency of the blade at different speeds. According to the force analysis of the blade, the free vibration equation of the blade is established by introducing the deformation coefficient of the blade. Then, a numerical method for calculating the static frequency and the dynamic frequency of the blade is obtained by using the Ritz-Galerkin method. The calculated results are close to the experimental ones. Compared with the existing methods, this method is characterized by the fact that the established blade vibration equation is more consistent with the actual situation, the calculation is simple, the result is reliable, and has certain engineering application value.