Research On Blade Profile Design Method And Aerodynamic Performance Of Supersonic Low-Reaction Compressor Rotor

The single stage load of compressor can improve the thrust-weight ratio of aeroengine,the improvement of per-stage pressure ratio can achieve by improving the circumferential speed and the twist speed,high circumferential speed lead to the emergence of supersonic compressor.The static pressure rise can achieve by shock wave,while shock wave also cause energy loss and become one of the core problems of supersonic compressor Based on the rotor of the first stage of low-reaction axial compressor.This paper propose blade profile design method,and explore the influence of pre-compression on blade aerodynamic performance and shock wave structure.This paper first proposes a large turning angle blade profile modeling method with pre-compression characteristics.The first half of the blade adopts the direct structure suction and pressure surface modeling method and the second half adopts the middle arc line superposition thickness distribution modeling method.Then,the modeling method is used to complete the shape of the blade with 100% and 75% leaf height.Under different Mach,the influence of pre-compression length on the aerodynamic performance and flow field shock structure of the blade is explored.The results show that under the high inflow Mach,the front negative curvature profile of the pre-compression section forms a series of weak compression waves to attenuate the shock wave intensity and significantly reduce the shock loss.The posterior positive curvature profile of the pre-compression section inhibits the development of the shock-attached boundary layer,which can effectively reduce the loss of profile.As the flow rate decreases,the shock wave moves forward,the effect of pre-compression weakening the shock wave strength will continue to decrease,the benefit of reducing the shock wave loss gradually disappears.and the shorter precompression length will disappear in advance.Finally,the paper performs three-dimensional blade calculation to investigate the effects of pre-compression length and depth of 100% and 75% leaf height on the aerodynamic performance and shock structure.The results show that the introduction of pre-compression can effectively reduce the shock intensity,so that the shock wave moves backward at the position of the suction surface of the blade,reducing the shock loss.There is a better pre-compression length,so that the blade pressure ratio remains basically the same,the peak efficiency is improved and the operating margin is wider.As the precompression depth increases,the efficiency and pressure ratio of the blade remain basically the same,and the operating margin increases.