Aerodynamic design method of high loaded supersonic axial-compressor with low reaction

For supersonic axial flow compressors, a brief summary was given for its historical development. The internal flow characteristics and problems of the two kinds of traditional supersonic compressors were analyzed. Some prospects were proposed for its future technology trends and research orientation. According to the flow characteristics in supersonic compressors, a new aerodynamic design method of high loaded supersonic axial-compressor with low reaction was put forward. Using this method, active flow control means are not necessary in the efficient rotor, and the exit absolute Mach number of the rotor is decreased. For the downstream stator, boundary layer suction is used to solve its internal flow problems to fulfill an efficient and high loaded stage design. A preliminary design verification of the principle has been conducted. The 3-D viscous numerical simulation results show that at the tip tangential speed of 360 m/s, the stage pressure ratio of 2.3 and the isentropic efficiency of 86.5% are achieved in the use of this concept.