Effects of Rotor-Bleeding Airflow on Aerodynamic and Structural Performances of a Single-Stage Transonic Axial Compressor

This paper presents the effects of airflow bleed from the rotor shroud surface between leading and trailing edges on aerodynamic and structural performances of a single-stage transonic axial compressor, NASA stage 37, using three-dimensional Reynolds-averaged Navier-Stokes equations with the k-epsilon turbulence model. A small airflow mass flow rate is bleed throughout a rotor-bleeding ejector which designed by seven parameters: bleeding angle (degrees) and ejection angles (degrees), ejection depth (D), bleeding thickness (H), bleeding position from rotor leading edge (L) in flow direction, bleeding ejection curvature (R), and bleeding width contacted on rotor shroud surface (W). The numerical results for aerodynamic performance: total pressure ratio, adiabatic efficiency, and stall margin of a transonic axial compressor were validated with a smooth casing experimental data. A parametric study of seven design parameters of rotor-bleeding ejector above combined with a small ejection mass flow rate in a single-stage transonic axial compressor for aerodynamic and structural performances was performed. The numerical results show that all aerodynamic performance increases with bleeding airflow from rotor shroud surface, the total deformation on rotor tip leading edge in spanwise direction reduces with a very small increasing in Von-Mises stress in a reference-bleeding airflow as compared to the results of smooth casing.