Effects of Air Injection on Aerodynamic Performance of a Single-Stage Transonic Axial Compressor

This paper presents a parametric study of stator air injection on aerodynamic performances of a single-stage transonic axial compressor, NASA Stage 37, using three-dimensional Reynolds-averaged Navier- Stokes equations with the k-ε turbulence model and scalable wall functions. The curvature, location and width of the stator injector and the mass flow rate of air injection were tested to find their effects on the aerodynamic performances, such as total pressure ratio, peak adiabatic efficiency, stall margin and stable range extension. The numerical results for adiabatic efficiency and total pressure ratio were validated with experimental data for smooth casing. The results of parametric study show that the aerodynamic performances of the single-stage transonic axial compressor improve greatly the peak adiabatic efficiency compared to the compressor with smooth casing.