InvesInvestigation of the Effects of Airfoil-probes on the Aerodynamic Performance of an Axial Compressor  

作　　者：HE Xiang MA Hongwei REN Minglin XIANG Honghui 

机构地区：[1]National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beihang University, Beijing 100191, China [2]China Gas Turbine Establishment, Chengdu 621703, China

出　　处：《Chinese Journal of Aeronautics》2012年第4期517-523,共7页中国航空学报（英文版）

基　　金：National Natural Science Foundation of China(51161130525);"111" Project (B08009)

摘　　要：In order to investigate the effects of the airfoil-probes on the aerodynamic performance of an axial compressor,a numerical simulation of 3D flow field is performed in a 1.5-stage axial compressor with airfoil-probes installed at the stator leading-edge（LE）.The airfoil-probes have a negative influence on the compressor aerodynamic performance at all operating points.A streamwise vortex is induced by the airfoil-probe along both sides of the blade.At the mid-operating point,the vortex is notable along the pressure side and is relatively small along the suction side（SS）.At the near-stall point,the vortex is slightly suppressed in the pressure surface（PS）,but becomes remarkable in the suction side.A small local-separation is induced by the interactions between the vortex and the end-wall boundary layer in the corner region near the hub.That the positive pitch angle of the airfoil-probe at 6.5% span is about 15° plays an important role in the vortex evolution near the hub,which causes the fact that the airfoil-probe near the hub has the largest effects among the four airfoil-probes.In order to get a further understanding of the vortex evolution in the stator in the numerical simulation,a flow visualization experiment in a water tunnel is performed.The flow visualization results give a deep insight into the evolution of the vortex induced by the airfoil-probe.In order to investigate the effects of the airfoil-probes on the aerodynamic performance of an axial compressor,a numerical simulation of 3D flow field is performed in a 1.5-stage axial compressor with airfoil-probes installed at the stator leading-edge（LE）.The airfoil-probes have a negative influence on the compressor aerodynamic performance at all operating points.A streamwise vortex is induced by the airfoil-probe along both sides of the blade.At the mid-operating point,the vortex is notable along the pressure side and is relatively small along the suction side（SS）.At the near-stall point,the vortex is slightly suppressed in the pressure surface（PS）,but becomes remarkable in the suction side.A small local-separation is induced by the interactions between the vortex and the end-wall boundary layer in the corner region near the hub.That the positive pitch angle of the airfoil-probe at 6.5% span is about 15° plays an important role in the vortex evolution near the hub,which causes the fact that the airfoil-probe near the hub has the largest effects among the four airfoil-probes.In order to get a further understanding of the vortex evolution in the stator in the numerical simulation,a flow visualization experiment in a water tunnel is performed.The flow visualization results give a deep insight into the evolution of the vortex induced by the airfoil-probe.

关 键 词：transonic compressor airfoil-probe numerical simulation flow visualization streamwise vortex disturbance 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.41