Effect of Discontinuous Bump at Different Spanwise Positions on the Performance of Transonic Compressor Rotor
In order to improve the aerodynamic performance of the transonic compressor,this paper uses numerical simulation methods to study the effect of discontinuous bump at different spanwise positions on the aerodynamic performance of NASA Rotor 37.The results indicate that as the discontinuous bump gradually approaches the blade tip,the bump can more effectively pre-compress the flow before the shock wave,reduce the reverse pressure gradient,and thus reduce the shock wave intensity.At the same time,the inhibitory effect on the interaction between the shock wave and the boundary layer is gradually increasing,which can effectively delay the separation of the boundary layer caused by the shock wave interference,improve the flow situation,and reduce losses.Compared to the prototype rotor,when discontinuous bump are arranged at 60％～90％blade height,the efficiency of the compressor rotor is improved throughout the entire flow range,with the highest efficiency increasing by 0.25％.At the highest efficiency,the total pressure ratio of the prototype blade is increased by 0.13％.
NETL
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万方数据
维普
