单级低速模拟轴流压气机实验台改进设计

In order to obtain a better representation of the rear stage flow field of high pressure compressor, the optimization design of a conventional three-row-blade single stage was performed. A novel five-row-blade configuration (including an inlet guide vane (IGV), an inlet stator (S1), a rotor (R), an outlet stator (S2) and an outlet guide vane(OGV)) was adopted and the hub-to-tip ratio was increased properly. Three-dimensional (3D) printing technique was employed to produce the blades. Experimental results were compared with those of a repeating four-stage large scale low speed axial compressor (LSLSAC, the third stage). It was demonstrated that the efficiency of the redesigned compressor reached 89.1% and the stall margin was 32.9%, which agreed with the repeat stage compressor. Similar inter-stage performance parameters were also achieved. The redesigned test facility had a stronger ability to reproduce the rear stage flow field of high pressure compressor compared with conventional low-speed large scale compressor test facilities. Owing to its advantages of low financial and time costs, the design method has the prospect to be utilized into more compressor rear-stage investigations.