EFFECTS OF INLET DISTORTION ON A LOW SPEED AXIAL COMPRESSOR STABILITY
Inlet distortion in aircraft has been a generally problem accompanying aircraft, which degrades the stable operating range of engine. An experimental is performed on a single stage low speed axial compressor to investigate the stability effect of inlet distorted inlet flow. Flow field around a rotor blade is measured utilizing 2D Digital Particle Image Velocimetry (DPIV) and dynamic pressure probes with uniform inlet flow condition and with distorted inlet flow condition,which is limited to the blade tip region. The flow field around the rotor blade changes significantly with the distorted inlet flow, exhibiting a non-axsymmetrical flow structure, which degrades the characteristics and the stall margin of the compressor, and which changes the mode of stall inception of the compressor.The distorted inlet flow field is circumferentially divided into four sectors to visualize the temporal and spatial flow structure of rotor blade passage in this paper by considering the hysteresis effect of the aerodynamic inertia, viscous property of boundary layer and the pressure degrade between distorted sector and undistorted sector. Three kinds of flow states are presented in rotor blade passage in a revolution period, which are visualized by PIV technique at corresponding circumferential position. Flow separation occurs and develops firstly in distorted sector when mass flow decreases. The disturbance initiating in the distorted sector will experience development and damping when it propagates circumferentially, and which may fail to survive the damping within the undistorted sector. Stall inception occurs only when the damping of the disturbance in the undistorted sector is in sufficient to prevail its growth. Consequently, the stall mode of the compressor is influenced by the development and damping of disturbance, exhibiting a different stall mode. The parallel compressor model, based on the linear stability properties of the undistorted compressor alone, is unable to predict the stall inception with inlet distortion.
Huabing Jiang Wei Yuan Qiushi Li Zhiqiang Gong Yajun LU
National Key Laboratory on Aeroengine, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics Beijing, 100083, P.R.China
国际会议
昆明
英文
413-421
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）