压气机转子三维紊流流场

在低速大尺寸压气机试验台上，用单斜热丝、高频压力探针及由旋转四坐标全电动探针位移机构带动的五孔气动探针，测量了单级压气机转子出口和单转子压气机叶片通道尖区在不同流量状态下三维平均和亲流流场。设计状态，叶尖泄漏涡的发展及其与端壁附面层的交混决定了尖区的流动特性。小流量状态，叶片吸力面附面层增厚，近失速状态尖部吸力面附面层发生分离，吸力而附面层内径向潜移强烈，叶尖吸力面角区产生大范围强旋涡，角区部分低能流体移向叶尖通道中部，与端壁附面层、泄漏涡、刮削涡及主流发生交混．

THREE-DIMENSIONAL TURBULENT FLOW FIELD OF AXIAL COMPRESSOR ROTOR PASSAGE

The 3-D turbulent flow at the exit of a single-stage axial compressor rotor passagewas measured using both a hot-wire probe and a high frequency pressure probe ,while the3-D mean flow in the tip region of an isolated axial compressor rotor pasoage were surveyedusing a conica1 five-hole pressure probep of a rotating four axis probe traversemechanism on a low speed large scale axial compressor rig. The development of the tipleakage vortex and its mixing with the end -wall boundary layer are decisive foundary lalyercharacteristics in design condition. With the mass flow reducing, the blade boundary layeron the suction surface is getting thicker and even separates in near stall condition, while theradial migration 0f the blade boundary layer bec0mes stronger. A strong vortex forms atthe casing-blade suction surface corner, and part of low-energy fluid is transported to themid-passage, mixing with the thickened end-wall boundary layer, the tip leakage vortex, theblade scrape vortex and the main flow.