Vorticity-based Research Of Aero Engine Compressor Stall And Surge

Compressor is an important part of aviation engines, and aerodynamic stability is an important issue of compressor design. Rotating stall and surge are the two main aerodynamic unstable states in compression system, so it is one of the main tasks of aero engine control that avoiding rotating stall and surge in working condition.First, analyze the mechanism of compressor stall and surge, and establish the theoretical basis of vorticity dynamics. By establishing Rotor37 blade model, use computational fluid dynamics software NUMECA to simulate the compressor under different inlet air flow. Then obtain the flow field characteristics at different air flow, prejudge the stall point of the model,and analyze the steady flow field of compressor rotor.Second, analyze the wake flow section of cascade passage. According the vorticity dynamics theory, find the performance parameters: total pressure flow and tangential vorticity.The result shows that the blade tip and area nearby the case are the important parts to work and pressurize.Third, analyze the vortex dynamics parameters of the rotor blade surface. According the vorticity dynamics theory, find the parameters of rotor blade analysis: the axial component of Boundary Vorticity Flow Rate. The result indicates that, compared with static pressure,Boundary Vorticity Flow can show the problem more easily and guide the improvement of blade design. At the same time, vorticity line can diagnose the flow separation area quickly and accurately.