Influence of continuous and individual bumps on aerodynamic performance of transonic compressor rotor
In order to study the influence of bumps on aerody-namic performance of the transonic compressor rotor,NASA Rotor 37 was taken as the research object with the spanwise continuous and individual bumps configured on the suction surface,the flow field structure and aerodynamic performance of the prototype rotor and the bump rotors under variable speed conditions were studied by numerical simulation.Re-sults show that at the design speed and 110％design speed,the continuous bump has better control effect on the shock wave near the blade tip,the gas before the shock wave can be pre-compressed to reduce the reverse pressure gradient before and after the shock wave,weaken the shock wave intensity,and thereby reducing the losses associated with shock wave.Under the peak efficiency operating condition of the designed speed,the total pressure ratio of the rotor with the spanwise individual bump is increased by 0.236％,and the efficiency is increased by 0.309％.The total pressure ratio of the rotor with the continuous bump is increased by 0.285％,and the effi-ciency is increased by 0.454％.At 50％,60％and 90％of design speed,the bumps has no beneficial effect on the aero-dynamic performance of the rotor.
万方数据
维普
