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为研究大攻角状态压气机转子内部分离区的脱落和传播过程及转子叶片对其动力响应问题,对某跨声速压气机级进行了非定常数值模拟和双向迭代流固耦合数值模拟。研究结果表明,在近失速状态,转子叶片通道内会周期性地发生2次叶背分离区的脱落和传播现象。第1个分离区主要表现出轴向传播特性,其会对下游流场产生影响;第2个分离区主要表现出周向传播特性,其会作用于周向相邻的转子叶片,对转子叶排自身产生激励作用,进而影响叶片表面压力分布,引起叶片较强的动力响应,对叶片结构强度的影响不可忽略。非定常/流固耦合计算手段能够较全面地预测流场中激励源的频率、幅值与位置等,在压气机设计阶段应对此类预测工作予以重视,以期更准确地预测叶片共振及动力响应等问题。
In order to study the process of shedding and propagation of the internal separation zone and the dynamic response of the rotor blades in the high angle of attack, a transonic compressor stage is simulated by unsteady numerical and two-way iterative fluid-structure interaction numerical simulation. The results show that in the near-stall state, the shedding and propagation of leaf-dorsal segregation zone occurs periodically in the rotor blade passage. The first separation zone mainly exhibits axial propagation characteristics, which will affect the downstream flow field. The second separation zone mainly exhibits circumferential propagation characteristics, which act on circumferentially adjacent rotor blades and influence the rotor blade row itself Resulting in incentives, and then affect the pressure on the blade surface distribution, causing a strong blade dynamic response, the strength of the blade structure can not be ignored. The unsteady / fluid-structure interaction calculation method can predict the frequency, amplitude and position of the excitation source in the flow field more fully. At the compressor design stage, such prediction should be paid more attention to in order to more accurately predict the blade’s resonance and dynamic response And other issues.