轮缘曲线对低反力度跨声速高负荷转子性能影响的数值研究

In order to explore a superior shroud profiling to further optimize the performance of the low-reaction rotor, three-dimensional numerical simulation is utilized to conduct a comparative study on three different shroud shapes from the first rotor in a two-stage low-reaction high-load counter-rotating compressor. The results show that compared to the case with straight line shroud, the concave-convex wave type (sinusoidal) shroud can improve the flow capacity and reduce the shock intensity of the tip, but at the same time increase the terminal shock intensity at outlet, the rotor peak efficiency decreased by 0.37% and the peak pressure ratio decreased. The convex-concave wave type (the symmetry curve of the sinusoidal curve with respect to the straight line) rotor has the lowest through-flow capacity. Despite an increase in the shock intensity at the leading edge of the blade tip, the concave part of the shroud near the trailing edge significantly reduces the terminal shock intensity at the exit, resulting an increase of 0.05% in rotor peak efficiency with increasing peak pressure ratio. It should be noted that, compared with the linear shroud, the use of wave-type shroud leads to a reduced stall margin. Appropriate shroud contouring could reduce the reaction and loading in the tip region. The shock strength at the leading edge of the blade tip and the trailing edge is effectively reduced to enhance the rotor aerodynamic efficiency in the context that no boundary layer separation occurs.