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压气机角区的大范围回流通常会引起叶片通道中的三维阻塞现象,并伴随有强烈的掺混流动损失。采用德国航空航天中心(DLR)开发的TRACE程序,在其推进技术研究所的高速压气机叶栅试验台(包含5个NACA65K48直叶片)上,研究了位于端壁上的边界层吸气措施——叶片弦中近尾缘吸气槽(MTE)对该直压气机叶栅通道的角区分离进行控制,减小二次流动损失,进而削弱其对总损失的影响。通过基于定常雷诺平均Navier-Stokes(RANS)方法的数值模拟研究与相应的试验研究对比,端壁边界层吸气能够较好地重新组织角区气流流动,减弱附着于叶片吸力面尾缘的集中脱落涡,使得角区分离涡强度显著降低,由此引起的二次流损失也明显降低,与无吸气状态相比最大降幅可达81.2%;在设计状态下采用吸气流量率为1%的MTE,总压损失有很大程度的降低:在数值计算中,降幅为15.2%;试验测量中为9.7%。
A large range of recirculation at the compressor corner generally causes three-dimensional clogging in the vane passage with strong mixing flow losses. Using the TRACE program developed by the German Aerospace Center (DLR), the boundary layer suction at the end wall was studied at its High Speed Compressor Cascade test rig (containing 5 NACA65K48 straight blades) at the Institute of Propulsion Technology - - The near-trailing edge suction slot (MTE) of the blade chord controls the angular separation of the straight-flow compressor cascade duct, reducing the loss of secondary flow and further impairing the total loss. By numerical simulation based on the steady Reynolds average Navier-Stokes (RANS) method and corresponding experimental studies, the inspiratory in the boundary layer of the end wall can reorganize the airflow in the corner zone well and weaken the concentration of the tail edge attached to the suction surface of the blade Shedding vortex, so that the corner of the separation of vortex intensity was significantly reduced, resulting in secondary loss was significantly reduced, compared with non-aspirated state the largest decline of up to 81.2%; in the design state using the inspiratory flow rate of 1% MTE, the total pressure loss is greatly reduced: in the numerical calculation, a decrease of 15.2%; experimental measurement was 9.7%.