基于油流图谱的高负荷压气机叶栅叶顶涡系研究

Through the oil flow experiments on the tip clearance flow of a highly loaded compressor cascade under different attack angles and Mach numbers，the oil flow patterns on the tip wall and suction surface of the blade were clearly captured， and the vortex structure of the blade tip was studied by topological analysis. The results showed that there existed six key vortices in the tip region of the compressor blade: tip leakage vortex， tip separation vortex， tip secondary vortex， horseshoe vortex and induced vortex; the increase of the attack angle of the incoming flow led to the increase of the blade load and the change of load distribution， the position of the maximum pressure difference was advanced，leading to the leakage in advance，yielding an obvious influence on the vortex structure of the flow field. On the contrary，the change of Mach number had little effect on the vortex structure.