Front Convex Circumferential Slot Receiver Processing The Experimental Research On The Impact Of Two-stage Axial Flow Compressor Performance

A single-stage axial-flow compressor test rig in the cascade aerodynamic laboratory was upgraded to a two-stage axial-flow compressor with the fund of Project 211. If necessary, the two-stage axial-flow compressor test rig can be returned to the original single-stage axial-flow compressor. Experiment results indicate that the mechanical and aerodynamical performances on the new two-stage axial-flow compressor have met the design requirements.A new multiposition three-hole pressure probe with the thermo-couple was designed, and was calibrated with the help of the jet wind tunnel. Data acquisition and processing system on multipoint pressure and temperature of the test rig was set up successfully.Based on the research achievements on casing treatment from our predecessors, specially the grooved treated casing which could improve the stall margin and the slopped treated casing which could raise the efficiency, a new kind of grooved treated casing with forward-step was designed, and experimental research on it was accomplished in the original single-stage and the new two-stage axial-flowcompressor, respectively. Experimental results indicate that when n = 0.71, thestall margin of the single-stage and two-stage compressor can increase respectively 8.10% and 8.75%, with the help of the new kind of treated casing. However, the maximum efficiency of the single-stage and two-stage compressor under the same speed can decrease 1.88% and 3.26%, respectively. Meanwhile, a design method on the axial position of the stage with treated casing in multistage axial-flow compressors, i.e., the stage with maximum stalling pressure-rise capability would be treated, was suggested on the basis of much data from the compressor test rig.