关键词: 超声速串列转子;激波;附面层;数值模拟

Abstract: In order to reveal the flow characteristics in a supersonic tandem rotor, a three-dimensional steady Navier-Stokes simulation was performed. The numerical results show that the combined compressing effect through shock wave and turned air flow can be obtained by supersonic tandem rotor. The predicted results also show that the interaction between the forward and aft blades induces a detached shock wave located at the leading edge of the aft blade, which results in the increase of flow loss in the tandem rotor. And a low velocity region is observed near the pressure side of the forward blade at the range from 65% to 75% span, which attenuates the aerodynamic loading of the aft blade. The results indicate that the interaction among the tip leakage flow, the passage shock and boundary layer flow leads to the increase of the flow deviation angle near the forward and aft blades tip region. The numerical results also indicate that the increase of the back pressure at the rotor exit tends to attenuate the intensity of the terminal shock wave in the rotor and improve the isentropic efficiency of the rotor. 

Key words: Supersonic tandem rotor; Shock wave; Boundary layer; Numerical simulation