Effects of Axisymmetric Rotor Injection on the Aerodynamic Performances of a Single-Stage Transonic Axial Compressor

Using 3D-RANS equations with the k- omega turbulence model, this paper shows four parametric studies of axisymmetric rotor injection on aerodynamic characteristics of a single-stage transonic axial compressor. The injection design variables, including mass flow rate, circumferential coverage angle, location, and width are established to find their effects on the compressor performances, comprising total pressure ratio, peak adiabatic efficiency, stall margin, and stable range extension. The simulation results confirm qualitatively and quantitatively that in most cases of the reference designs with the rotor injection, the compressor aerodynamic outcomes are improved considerably. The ideal design was found to augment the adiabatic efficiency, total pressure ratio, and stall margin by 0.67, 0.52 and 2.28%, one-to-one.