关键词: 跨音速压气机;损失;数值仿真

Abstract: An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressor.Improvements in the loss and deviation model include incorporation of a physics-based shock loss model which accounts for shock geometry changes from near-choke to near-stall,and loading effects on the tip secondary loss model.Specially,the characteristics of the loss components and the losses of different blade section are compared and analyzed under 100% design rotate speed,and some useful conclusions from those analyses are given.Data from a two-stage transonic axial compressor provides the basis for experimental comparisons.Overall comparisons demonstrate the improved loss and deviation model gives the general accurate results,indicating that the profile loss,the shock loss,the secondary and spanwise mixing loss relative to off-design performance of the transonic axial compressor are adequately captured.

Key words: Transonic compressor;Loss;Numerical simulation