Experimental method of varying static pressure ratio for a transonic compressor rotor cascade
The study focused on addressing the experimental challenge of increasing the static pressure ratio for transonic compressor rotor cascades.To this end,various experimental methods were investigated,including altering the blade numbers of the cascade model and adjusting the back pressure in a variable density plane cascade wind tunnel.A calibration method was developed to estimate the Mach number of the flow field,by utilizing the predicted isentropic Mach number distributions of blade surfaces obtained from computational fluid dynamics(CFD).This method effectively guided the high static pressure ratio experiments conducted near the design point of the rotor cascade of the L030-4 compressor.The results demonstrated the success of the combined approach,involving the reduction of blade numbers and adjustment of back pressure in achieving the desired high static pressure ratio conditions with seven blades.Furthermore,the Mach number calibration method based on CFD facilitated the realization of high static pressure ratio experiments near the design point of the L030-4 compressor cascade.The obtained parameters,including total pressure loss,static pressure ratio,exit flow angle,and axial density velocity ratio of the cascade,were compared with the experimental data from foreign wind tunnel experiments.The relative deviations were all below 4％,validating the rationality of the calibration method.
compressortransonicsupersonicrotor cascadestatic pressure ratio
万方数据
维普
