Study of aerodynamic design method for downstream stator based on supersonic impulse rotors

For supersonic compressors, the aerodynamic design characteristics of the two types of traditional supersonic rotors were analyzed. Taking into account the high exit absolute Mach number of the impulse rotors, which always may cause problems for the downstream stator design, two kinds of stator aerodynamic design methods were put forward. And stator was matched for a special impulse rotor with these two kinds of design methods separately. From the three-dimensional viscous numerical simulation results, the flow details have been initially realized. As for the first stator aerodynamic design method, the flow at the stator entrance is decreased to subsonic and the turning of the flow in the stator can even be ignored. A supersonic compressor stage has been attained with pressure ratio not less than 2.2 and efficiency higher than 82%. As for the second stator aerodynamic design method, a compressor stage with pressure ratio not less than 2.1 and efficiency higher than 77% has been attained. But considering the highest stage efficiency attained when a normal shock exits at the entrance of the stator, the design does not achieve the goals to reduce the shock losses by this method.