Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip

Parameter studies for different attenuation thickness(in the tangential direction of blade) and relative height(in the spanwise direction of blade) of pressure surface at tip region are developed,which take ROTOR37 as an example and adopt numerical simulation to obtain the results.Aerodynamic performance curves are obtained at 60%,80%,90% and 100% of design rotate speed working conditions,moreover,detailed analysis of internal flow field is presented for design condition.Results of ten models including the model with unchanged blade element indicate that blade tip attenuation within certain range can advance choke mass flow,total pressure ratio and adiabatic efficiency,and decrease stall margin of the rotor,however,the influence is not so patent.