Study on flow separation and suction control of a compressor tandem cascade
参考中译:压气机串联叶栅流动分离及吸入控制研究


          

刊名：Proceedings of the Institution of Mechanical Engineers
作者：Botao Zhang（School of Power and Energy, Northwestern Polytechnical University）
Xiaochen Mao（School of Power and Energy, Northwestern Polytechnical University）
Bo Liu（School of Power and Energy, Northwestern Polytechnical University）
Hejian Wang（School of Power and Energy, Northwestern Polytechnical University）
Zonghao Yang（School of Power and Energy, Northwestern Polytechnical University）
Ran Zhang（School of Power and Energy, Northwestern Polytechnical University）
刊号：780C0002-C
ISSN：0954-4062
出版年：2023
年卷期：2023, vol.237, no.23
页码：5588-5601
总页数：14
分类号：TH11
关键词：Tandem cascade；Flow separation；Boundary layer suction；Blade wake；Flow control
参考中译：串联叶栅；流动分离；附面层抽吸；叶片尾流；流动控制
语种：eng
文摘：To control the boundary layer separation on the front blade suction surface in a compressor tandem cascade at a high incidence angle, three suction schemes at different axial positions were introduced and the cascade performance improvement and separation flow control effects were investigated. Based on the experimental and numerical simulations, the aerodynamic performance of the prototype tandem cascade reaches the peak at the incidence angle of 5°. Continue to increase the incidence angle, the loss increases sharply, and the static pressure rise coefficient and diffusion factor begin to decrease. With the boundary layer suction on the suction surface of the front blade, fluid energy in the upstream boundary layer of the suction slot is increased, and the adverse pressure gradient downstream is decreased. By suction, the development and separation of the boundary layer are inhibited, and the loss in the tandem cascade is significantly reduced. The flow control effect of the suction scheme at the onset location of boundary layer separation is the best, and the flow loss can be reduced by about 34.9% with a suction flow rate of 1% at the incidence angle of 5°. The suction schemes have good flow control effects in a wide working range and broaden the available range of incidence angles of the tandem cascade. This study provides a reference for the design of tandem blades considering flow control and has a positive significance for improving compressor efficiency and pressure ratio.
参考中译：为了在大攻角下控制压气机串列叶栅前叶片吸力面的边界层分离，采用了3种不同轴向位置的吸气方案，研究了不同吸气方案对叶栅性能的改善和分离流动控制效果。在实验和数值模拟的基础上，原型串列叶栅的气动性能在攻角为5°时达到最大。继续增大入射角，损失急剧增加，静压升系数和扩散系数开始减小。前叶片吸力面的边界层吸力增加了吸力槽上游边界层内的流体能量，减小了下游的逆压梯度。吸力抑制了附面层的发展和分离，显著降低了串列叶栅的损失。在附面层分离开始处，吸气方案的控流效果最好，在5°入射角下，吸气流量为1%时，可使流动损失减少约34.9%。吸气方案在较宽的工作范围内具有良好的流量控制效果，拓宽了串列叶栅的攻角适用范围。该研究为考虑流量控制的串列叶片设计提供了参考，对提高压气机效率和压比具有积极意义。



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