摘要
针对液体火箭发动机机械密封的二次利用问题,为避免碰磨进行了动静压机械密封的结构设计及端面槽型优化研究。采用动压和静压联合工作的原理,设计了动静压机械密封结构,并对静环节流孔及动环动压槽进行了重点设计;基于流体力学方程求解了静环的开启力及泄漏量,通过课题组已有机械密封计算软件计算了动环的开启力及泄漏量等指标;针对外螺旋槽内人字槽的组合槽型,采用正交试验的方法对槽型进行了优化,选定了最优槽型方案,该槽型优化方案的开启力为8.2 kN,泄漏量为0.66 mL/s,在保证泄漏量的前提下可以获得更大的开启力。研究结果表明,采用动静压形式的机械密封在工作中可有效减少磨损,保证泄漏量较小,满足二次利用的要求。该研究成果也可为其他高速旋转机械的机械密封结构优化提供参考。
Aiming at the secondary utilization of mechanical seals for liquid rocket engines, this paper studied the structural design of the dynamic and static pressure mechanical seals and the optimization of the end grooves in order to avoid collision. Based on the principle of combined dynamic and static pressure, a dynamic and static pressure mechanical seal structure is designed, and the flow orifices in the static link and the dynamic pressure grooves in the dynamic ring are designed. The opening force and leakage of the static ring are solved based on the hydrodynamic equation. Based on the existing mechanical seal calculation software of the research group, the indicators such as the opening force and leakage of the moving ring were calculated. For the combined groove shape of the herringbone groove in the outer spiral groove, the geometry was optimized by orthogonal test. An optimal groove plan is determined. The trough optimization scheme has an opening force of 8.2 kN and a leakage volume of 0.66 mL/s. A larger opening force can be obtained on the premise of ensuring the leakage volume. The research results show that the mechanical seal in the form of dynamic and static pressure can effectively reduce wear during work, ensure a small leakage, and meet the requirements of secondary use. The research results can also provide a reference for the optimization of the mechanical seal structure of other high-speed rotating machinery.
作者
王建磊
门川皓
赵伟刚
贾谦
崔亚辉
张琛
袁小阳
WANG Jianlei;MEN Chuanhao;ZHAO Weigang;JIA Qian;CUI Yahui;ZHANG Chen;YUAN Xiaoyang(School of Machinery and Precision Instrument Engineering,Xi’an University of Technology,Xi’an 710048;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072;Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation(CASC),Xi’an 710100;Department of Mechanical Engineering,Xi'an Jiaotong University City College,Xi’an 710018;Key Laboratory of Modern Design and Rotor Bearing System,Ministry of education,Xi’an Jiaotong University,Xi’an 710049)
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2021年第9期108-117,共10页
Journal of Mechanical Engineering
基金
国家自然科学基金(11872289)
国家重点研究计划(2018YFB2000505)资助项目。
关键词
火箭发动机
涡轮泵
动静压机械密封
槽型
正交试验
rocket engine
turbopump
hydrodynamic mechanical seal
geometry
orthogonal experiment
