Off-design performance analysis of multi-stage transonic axial compressors
An improved streamline curvature numerical method is applied to better approximate the flow fields of multi-stage transonic axial compressor. Specifically, improvements in total pressure loss modeling are implemented to ensure accurate and reliable off-design performance prediction. Compared with the original normal shock, the new shock loss model accounts for shock geometry changes, with shock loss estimated as a function of inlet relative Mach number, flow turning, solidity, leading edge radius and suction surface profile from near-choke to near-stall. The 3-D effects on the deviation model and loading effects on the tip secondary loss model are also accounted in this paper. Data from a two-stage transonic axial compressor provides the basis for experimental comparisons. In general, the effects of important flow phenomena relative to off-design performance of the transonic compressor are accounted, which include the shock loss, second flow and boundary layer transition. The increased shock pressure loss with loading and the analysis of the components of loss across the rotor tip region indicate that the new shock model can be considered a significant improvement in the analysis of multi-stage transonic compressor, indicating that the physical understanding of the blade effects and the flow physics that underlie the new model improvements are correct and realistic.
transonic compressor shock loss model streamlines curvature method off-design
W.H.Du H.Wu L.Zhang
School of Power and Energy Northwestern Polytechnical University ，Xi’an, 710072, China
国际会议
The Fifth International Conference on Fluid Mechanics(第五届国际流体力学会议)
上海
英文
2007-08-15（万方平台首次上网日期，不代表论文的发表时间）