【摘要】 针对国产压缩机现有的常规轮毂比模型级无法满足七级两段方案的转子稳定性的要求，只能采用双缸设计的问题，提出了一种大轮毂比模型级。以双缸储气库压缩机中等轮毂比模型级为基础，结合正向设计方法，自动优化方法和试验方法，完成了大轮毂比模型级的设计开发。并对不同轮毂比模型级几何形状、宏观性能以及各部件的内部流场特性进行了对比分析，揭示了大轮毂比模型级的流动特性。研究表明，0.46大轮毂比模型级相比0.39轮毂比模型级多变效率低4.3%，叶轮部分的效率降最大，占整级效率降的67.4%，调节叶轮的叶型、叶片数以及降低叶轮与无叶扩压器内部马赫数对提升模型级效率具有更大的潜力。所开发的模型级轮毂比提高了18%，解决了七级两段方案的转子稳定性问题，实现了占地面积小的单缸储气库压缩机设计与开发。CFD与试验结果的效率偏差均在3%以内，具备较强的参考价值，为离心压缩机的大轮毂比模型级的气动设计、开发与应用提供了宝贵的借鉴意义。更多还原

【Abstract】 A large hub to hub ratio model stage is proposed to address the issue of the existing conventional hub to hub ratio model stage for domestic compressors being unable to meet the rotor stability requirements of the seven stage two-stage scheme and can only adopt a dual cylinder design.Based on the medium hub-tip ratio model stage of a double-cylinder gas storage compressor,the design and development of a high hub-tip ratio model stage has been completed by combining the forward design method,automatic optimization method and test method.The geometry,macroscopic performance,and internal flow field characteristics of different hub-tip ratio model stages were also compared and analyzed,and it revealed the flow characteristics of the high hub-tip ratio model stage.The study shows that the polytropic efficiency of the 0.46 high hub-tip ratio model stage is 4.3% lower than that of the 0.39 hub-tip ratio model stage,and the efficiency drop of the impeller part is the largest,accounting for 67.4% of the efficiency drop of the whole model stage.Adjusting the blade profile,the number of blades, and reducing the Mach number inside the impeller and the bladeless diffuser have a greater potential to improve the efficiency of the model stage.The deviation of the efficiency between the CFD and the experimental results is all within 3%,which has strong reference value.The developed model stage hub ratio has been increased by 18%,which solves the rotor stability problem of the seven-stage two-section scheme and realizes the design and development of a single-cylinder gas storage compressor with a small floor area.This study addresses the stability issues of single-cylinder seven-stage two-stage rotors,and fills the research gap in the application of large wheel hub ratio compressors in China,and provides valuable reference significance for the aerodynamic design,development and application of the high hub-tip ratio model of centrifugal compressors.更多还原