摘要
针对航空发动机减速器轴承腔上的新型高速气液混相回流泵送密封(GL-RPS)机构,揭示了其开启过程的温度特性。通过建立数值分析模型,分析动压槽槽数、槽深、槽坝比对密封开启力的影响,得到密封开启性能的优选结构参数,基于优选参数进行GL-RPS的开启过程温度特性试验。基于温度特性,从开启状态、开启转速、开启温度和摩擦磨损等角度对比分析了4种密封结构的开启特性。结果表明:在开启过程中,端面温度的变化分为3个明显阶段,分别对应密封端面的3个接触状态,可以有效监测和表征密封开启过程;在密封未开启阶段,端面温度随转速增大而升高;在过渡阶段,端面温度随转速增大逐渐降低,端面温度存在跳跃;在完全开启阶段,端面温度随转速增大基本不变;密封开启转速、过渡阶段转速跨度、开始开启和完全开启时的端面温度差都随压力增大线性增大。得出了GL-RPS开启性能较好的结构参数,能有效降低GL-RPS的开启转速和开启温度,减小密封端面磨损。研究结果可为航空发动机减速器轴承腔GL-RPS的设计提供参考,并提供了一种密封端面接触状态监测方法。
Aiming at the new high-speed gas-liquid mixed-phase reflux pumping seal(GL-RPS)on the reducer bearing cavity of aeroengine,the temperature characteristics of GL-RPS was revealed in the opening process.A numerical analysis model was established to study the influence of the number of hydrodynamic grooves,groove depth and groove-dam ratio on the sealing opening force.The optimum structural parameters with better sealing opening performance were obtained.Based on the temperature method,the opening performance of four kinds of seals was compared and analyzed from the aspects of opening state,opening speed,opening temperature and friction and wear.The results show that the temperature change of the sealing face can be divided into three distinct stages,corresponding to the three contact states of the sealing face,which can effectively monitor the sealing opening process.When the seal is not opened,the temperature of the end face increases with the increase of rotational speed.In the transition stage,the temperature of the end surface decreases gradually with the increase of rotational speed,and there is a jump in the temperature of the end surface.In the fully open stage,the temperature of the end surface basically remains unchanged with the increase of rotational speed.Seal opening speed,speed span in transition stage,tempera⁃ture difference of end face at start and full opening all increase linearly with the increase of pressure.The experimental results are in good agreement with the numerical simulation results.The structure parameters of GL-RPS with good opening performance are obtained,which can effectively reduce the opening speed and temperature of GL-RPS,and reduce the wear of sealing face.The research results provide a reference for the design of GL-RPS for the reducer bearing cavity of aeroengine and a method for monitoring the contact state of sealing end face.
作者
李庆展
李双喜
郑娆
力宁
李世聪
LI Qing-zhan;LI Shuang-xi;ZHENG Rao;LI Ning;LI Shi-cong(Research Center of Fluid Sealing Technology,Beijing University of Chemical Technology,Beijing 100029,China;AECC Hunan Power Machinery Research Institute,Zhuzhou Hunan 412002,China)
出处
《航空发动机》
北大核心
2021年第3期72-79,共8页
Aeroengine
基金
国家重点研发计划(2018YFB2000800)资助。
关键词
气液混相
开启特性
密封
轴承
减速器
航空发动机
gas-liquid mixed-phase
opening characteristic
seal
bearing
reducer
aeroengine
