摘要
以某组合压气机的高进口马赫数径向扩压器为研究对象,调整中弧线分布和展向积叠方式,实现了径向扩压器三维叶片设计,提升了组合压气机的气动性能。数值计算表明,与直叶片方案相比,三维叶片方案的堵点流量基本不变、设计点恢复系数提高1.1%,峰值恢复系数提高0.4%;轴流离心组合压气机的峰值效率提升0.2%,喘振裕度由15.8%提升至17.3%。与直叶片方案相比,三维叶片方案更能适应离心叶轮出口流场;根部迎角增大和尖部迎角减小;根部叶盆前缘由于负迎角导致的局部高马赫数区域得到消除,叶盆侧通道内的分离范围明显减小;叶中和叶尖部位的尾迹得到改善;径向扩压器进口马赫数的均匀性得到提高。本文为进一步提高扩压器的性能提供设计参考。
The radical vaned diffuser of a combined compressor is investigated through adjusting the arbitrary blade profile camber lines and span-wise stacking,thus achieving the 3D vaned diffuser and improving the aerodynamic performance.Numerical simulation indicates that,compared with the classical vaned diffuser with uniform spanwise profile,the mass flow rate of 3D blade near chock point remains the same and the total recovery coefficient increases,with 1.1%at design point and 0.4%at stall point,meanwhile the peak efficiency of the combined compressor is increased by 0.2%and the surge margin is improved from 15.8%to 17.3%.Moreover,the 3D vaned diffuser is more adaptive to the variable flow field of the impeller.Negative angle of attack in the hub region and the positive angle of attack in tip region are improved.The high-Mach region at leading edge caused by negative angle of attack is eliminated.The core of flow separation near the pressure side is significantly narrowed.The distribution of Mach number at the inlet of 3D vaned diffuser is more uniform.This paper provides a design reference for further improving the performance of the diffuser.
作者
杨晰琼
李杜
Yang Xiqiong;Li Du(Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine,AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)
出处
《航空科学技术》
2022年第2期29-35,共7页
Aeronautical Science & Technology
关键词
径向扩压器
三维叶片
数值模拟
流场分析
radical diffuser
3D blade
numerical simulation
flow analysis
