Aerodynamic and structural dynamics analysis of swept transonic compressor rotors

The application of sweep on rotor blades is one of the most significant technological evolution to improve the aerodynamic behavior of transonic compressor stages. 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. 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 behavior of transonic axial-flow compressor rotors is undertaken. Then, the static, dynamic natural frequencies and mode shapes of Rotor 37 and new swept transonic compressor rotors are calculated. By using CFX Pressure load, the static structural analysis is carried out with rotational load to understand the stress levels of swept models at design and two-off design speeds. At the last, the harmonic response behavior of Rotor 37 and swept models are calculated.