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为了深入理解频率失谐对跨声速压气机气弹稳定性的影响,基于能量法建立了跨声速颤振实验转子的全周气动阻尼计算模型,数值分析了转子叶片频率交替失谐、随机失谐以及线性失谐对其气弹稳定性的影响。数值计算了该转子的气动性能,颤振边界和叶片模态,其结果和实验数据吻合较好;研究不同模态、不同叶片间相位角条件下谐调转子的气动阻尼,结果表明叶片间相位角对叶片气动阻尼均有较大的影响,尤其在一弯模态下,叶片气动阻尼对叶片间相位角最敏感;对该转子所有叶片的平均气动阻尼而言,失谐的存在弱化了叶片间相角对叶片气动阻尼的影响,显著提高了该转子最不稳定状态的平均阻尼达到7~11倍,反之使其最稳定状态的平均阻尼降低约50%;失谐转子中不同叶片的气动阻尼表现出显著差异,其受叶片局部失谐模式及失谐量的影响较大。
In order to deeply understand the effect of frequency detuning on the aeroelastic stability of transonic compressor, a full-scale aerodynamic damping calculation model of transonic flutter experimental rotor is established based on energy method. Numerical analysis of rotor blade frequency alternating detuning and random detuning And the effect of linear detuning on its aeroelastic stability. The aerodynamic performance, flutter boundary and blade modes of the rotor are numerically calculated. The results agree well with the experimental data. The aerodynamic damping of the tuned rotor under different modalities and different interphase angles is studied. The results show that the interphase angle The aerodynamic damping of the blade is the most sensitive to the phase angle between the blades. In terms of the average aerodynamic damping of all the blades of the rotor, the presence of detuning weakens the inter-blade space The influence of phase angle on the aerodynamic damping of the blade significantly increases the average damping of the rotor at the most unstable state by 7-11 times, on the contrary, reduces the average damping by about 50% at its most stable state. The aerodynamic damping of different blades in the detuning rotor Showing significant differences, which are greatly affected by the local leaf detuning mode and detuning.