航空学报 > 2017, Vol. 38 Issue (3): 120308-120308   doi: 10.7527/S1000-6893.2016.0195

喉道对压气机超声叶栅流态及性能的影响

江雄, 邱名, 范召林   

  1. 中国空气动力研究与发展中心 计算空气动力学研究所, 绵阳 621000
  • 收稿日期:2016-04-11 修回日期:2016-06-14 出版日期:2017-03-15 发布日期:2016-06-28
  • 通讯作者: 范召林,E-mail:fzl-cardc@163.com E-mail:fzl-cardc@163.com
  • 基金资助:

    国家自然科学基金(11572339)

Effect of supersonic compressor cascade throat on flow pattern and cascade performance

JIANG Xiong, QIU Ming, FAN Zhaolin   

  1. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-04-11 Revised:2016-06-14 Online:2017-03-15 Published:2016-06-28
  • Supported by:

    National Natural Science Foundation of China (11572339)

摘要:

为更深入认识超声叶栅流动机理,以ARL-SL19、CM-1.2和SM-1.5叶栅为研究对象,采用数值模拟和理论分析相结合的方式开展喉道对超声叶栅激波结构和性能影响的研究。研究结果表明:超声叶栅存在两种稳定工作状态,起动状态和溢流状态;在来流马赫数较高时,叶栅只工作于起动状态;在来流马赫数较低时,叶栅只工作于溢流状态;存在一个马赫数区间,叶栅的工作状态由前一个状态决定;对于低马赫数C形超声叶栅,高压比下气动喉道起决定因素;对于高马赫数S形超声叶栅,真实喉道起决定因素;若为气动喉道导致溢流,溢流实现更大的裕度和更低的损失,进口马赫数和气流角会受压比影响;若为真实喉道引进的溢流,溢流会降低裕度并增加损失,叶栅保持唯一进气角流动,但进口气流角和马赫数与起动状态不同。

关键词: 超声叶栅, 叶栅喉道, 起动状态, 溢流状态, 激波结构, 唯一进气角

Abstract:

To have a better understanding of the flow mechanism of the supersonic cascade, the effect of throat on supersonic cascade's shock-wave configuration and performance is studied through numerical simulation and theoretical analysis. Cascade ARL-SL19, Cascade CM-1.2 and Cascade SM-1.5 are taken as the object of the study. The results show that there are two kinds of steady working states for the supersonic cascade:starting state and overflow state. When the inlet Mach number is high, the supersonic cascade works in the starting state; when the Mach number is low, the supersonic cascade works in the overflow state. There is a Mach number range, and the supersonic cascade works in the state the same as the previous state. The aerodynamic throat is determinant in near stall pressure-ratio for the C-shaped supersonic cascade with divergent channel at lower supersonic, but the real throat is determinant for S-shaped supersonic cascade with convergent channel. If it is caused by the aerodynamic throat, the overflow achieves less loss and greater margin, and the inlet Mach number and the flow angle are influenced by the outlet pressure. If it is caused by the real throat, the overflow achieves more loss and smaller margin, and the cascade still works in the unique incidence.

Key words: supersonic cascade, cascade throat, starting state, overflow state, shock-wave structure, unique flow angle

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