Influence of rotor leading edge winglet on the stability of transonic compressor
In order to further expand the stability margin of the axial compressor,taking the transonic compressor NASA(National Aeronautics and Space Administration)Stage35 as the research object,the expansion mechanism of the rotor leading edge winglet was studied by using the numerical simulation method after numerical verification,and the effects of leading edge winglet on transonic compressor performance and internal flow were discussed in detail.The research results show that all leading edge winglet cases reduce the peak efficiency of the compressor.The suitable length leading edge winglet of the rotor blade can increase its stability margin by 14.96%while keeping the compressor stage pressure and efficiency basically unchanged near the near-stall operating condition.Compared with the prototype compressor,the leading edge winglet increases the blade tip chord of rotor,and the blade tip load near the leading edge is reduced,thereby reducing the tip leakage vortex intensity and the flow blockage caused by the shock wave/tip leakage vortex interaction,and improving the working stability of the compressor.The reason for the decrease in peak efficiency of the compressor caused by the leading edge winglet is that the leading edge winglet weakens the blowing effect of the tip leakage flow on the separation fluid of the suction surface and end wall area of the rotor blade.
rotor leading edge winglettransonic compressortip leakage vortexstability marginvortex structure
国家科技期刊平台
NSTL
万方数据
