This paper investigates the effects of recirculation channel on the performance of a single-stage transonic axial compressor, NASA Stage 37, such as pressure ratio, adiabatic efficiency, and operating range. Numerical analysis was conducted by solving three-dimensional steady Reynolds-averaged Navier-Stokes equations with the k-epsilon turbulence model. The recirculation channel bled the high-pressure flow from the stator shroud domain and injected it into the rotor tip clearance domain to increase the aerodynamic performance. |
