Numerical Investigation of New Swept Transonic Compressor Rotors on Design and off Design Conditions

摘要

The new swept rotors are modeled by changing the curvature of the original blade stacking line of NASA Rotor 37 in the meridional plane. But the original tip leading point, tip trailing point, hub leading point and hub trailing point are not changed. A systematic investigation to understand the impact of axially swept blades on the aerodynamic behaviour of transonic axial-flow compressor rotors is undertaken. Effects of axial blade curvature are analyzed. A commercial CFD package, which sloves the Reynolds-averaged Navier-Stokes equations, is used to compute the complex flow field of transonic compressor-rotors. It is validated against NASA Rotor 37 existing experimental data Next, some new transonic swept rotors are modeled from the original Rotor 37, by changing the meridional curvature of the original stacking line through four control points (located at 20%, 40%, 60% and 80% of span). All the new swept transonic rotors are simulated on design and two off-design conditions of original rotor 37. The results revealed many interesting aspects which are believed to be very helpful to better understand the blade curvature effects on the aerodynamic behaviour of transonic compressor rotors.