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。
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.
作者
傅鑫
曹永华
张一彬
朱超
FU Xin CAO Yong-hua ZHANG Yi-bin ZHU Chao(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, Jiangsu, China)
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2017年第4期824-832,共9页
Acta Armamentarii
基金
航空推进技术验证计划项目(APTD-0302-01)
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
propulsion system of aviation and aerospace
sealing labyrinth
high speed experiment
leakage flow boundary model
numerical simulation
