Aerodynamic Design Of High Load Multi-stage Axial Compressor

High efficiency,high pressure ratio and large stability margin are the performance indexes pursued by supersonic compressor design.In order to increase pressure ratio,the compressor is needed have a high load,and the increase of the load factor will make the compressor inlet appear supersonic area,so the design of supersonic compressor is of great significance.In this paper,the initial design of the compressor blade is carried out by S1 and S2 flow surface design methods,and the blade is optimized by the automatic optimization method.The Streamline curvature method is used to determine the rule of blade torsion,which provided the import and export conditions for the design and analysis of S1 surface.The two-dimensional blade profile design of S1 flow surface use parametric method,and then use the Bezier curve to fit the blade geometry to generate a smooth blade profile.The blade profile designed by S1 flow surface is radial stacked into a three-dimensional blade profile along the core,and adopt automatic optimization method based on genetic algorithm to improve the two-dimensional blade profile and aerodynamic performance,by change blade stacked lines,meridian flow channel shape,blade profile,installation angle.And then turn the stator to cooperate,turn the levels to cooperate to get good performance.The design and performance calculation of the supersonic compressor with a design flow of 6.3 kg/s are carried out by the self-developed design platform of Professor Zhou Zhenggui and his students and NUMECA.The designed compressor has a total of five rows of blades,including the inlet guide vane,the first level including rotor and stator,and the second level.Then we obtain the performance indicators: the design mass flow is 6.35,the design total pressure ratio is 4.76,the efficiency is 0.842,and stability margin is 7.23%;the result shows that the designed supersonic compressor has a satisfactory aerodynamic performance.