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基于一种泄漏流边界模型的封严篦齿分析方法研究
引用本文:傅鑫,曹永华,张一彬,朱超.基于一种泄漏流边界模型的封严篦齿分析方法研究[J].兵工学报,2017,38(4):824-832.
作者姓名:傅鑫  曹永华  张一彬  朱超
作者单位:(南京航空航天大学 能源与动力学院, 江苏 南京 210016)
基金项目:航空推进技术验证计划项目
摘    要:针对篦齿通道中存在的结构相对复杂、封严间隙随工作状态变化、数值模拟计算域网格量大等问题,对不同密封构型参数下的多种直通式封严篦齿模型进行了高速实验研究,并基于实验结果建立能够反映环境参数和封严构型参数对密封性能影响的篦齿泄漏流边界模型。结果表明:该模型能够很好地还原实验规律,可以在多级的压气机计算中可靠地模拟篦齿泄漏流动,并在某3级压气 机中计算得到0.5%的泄漏量将分别导致压气机流量、压比和效率呈现1.4%、0.3%和1.1%的下降。

关 键 词:航空、航天推进系统  封严篦齿  高速实验  泄漏流边界模型  数值模拟  
收稿时间:2016-06-29

Study of Leakage Flow Boundary Model-based Sealing Labyrinth Analysis Method
FU Xin,CAO Yong-hua,ZHANG Yi-bin,ZHU Chao.Study of Leakage Flow Boundary Model-based Sealing Labyrinth Analysis Method[J].Acta Armamentarii,2017,38(4):824-832.
Authors:FU Xin  CAO Yong-hua  ZHANG Yi-bin  ZHU Chao
Affiliation:(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, Jiangsu, China)
Abstract:In view of the complex structure of labyrinth channel,changing sealing gap and a large amount of grids in numerical simulation calculation domain,a high-speed straight-through sealing labyrinth structure adopting different sealing configuration parameters is investigated.A labyrinth leakage flow boundary model is established based on test results,which can reveal the effects of environmental parameters and sealing configuration parameters on sealing property.The results show that the proposed model can be used to repeat the experimental rule and reliably simulate the labyrinth leakage flow in multistage compressor.The calculated sresult shows that 0.5 % flow leakage would result in decreasing the flow,pressure ratio and efficiency of a three-stage compressor by 1.4%,0.3% and 1.1%,respectively.
Keywords:propulsion system of aviation and aerospace  sealing labyrinth  high speed experiment  leakage flow boundary model  numerical simulation
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