The Numerical Optimization Design of Stacking Line at the Rotor's Leading Edge of Transonic Compressor

The numerical optimization design was carried out on the stacking line of the rotor of transonic compressor NASA rotor37.The objective function is adiabatic efficiency,and the constraint condition is the total pressure ratio and mass flow.Then,the changes of geometry,overall performance and flow field were analyzed and compared in detail.The result shows that backward swept bowed blades leads to the inclination of the shock waveform.At the mid-span,the intensity of shock wave has been weaken;at hub,the shock wave has been moved backward.At the same time,it points out that single condition point design has shortage on control the off-design performance.