高速轴承环下润滑收油叶片结构参数与工况参数间的匹配关系  

Matching relationship between structural parameters and operating parameters of oil scoop blade for high-speed bearing with under-race lubrication

作　　者：吕亚国[1] 姜乐 高晓果 刘振侠[1] 朱鹏飞[1] 高文君[1] LYU Yaguo;JIANG Le;GAO Xiaoguo;LIU Zhenxia;ZHU Pengfei;GAO Wenjun(School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China;Key laboratory of Power Transmission Technology on Aero-engine,Aero Engine Corporation of China,Shenyang 110015,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空发动机集团航空发动机动力传输重点实验室,沈阳110015

出　　处：《航空学报》2022年第12期553-567,共15页Acta Aeronautica et Astronautica Sinica

摘　　要：为了研究环下润滑收油叶片结构参数和工况参数间的匹配关系,通过理论分析和数值模拟方法研究了收油叶片半径差、滑油喷嘴喷射角度、收油环转速和滑油流速对滑油损失角和收油效率的影响。研究结果表明:调整滑油喷射角度和收油叶片半径差可改变滑油射流冲击收油叶片外轮廓的冲击点位置,前者的影响较小,后者在低滑油流速下可以降低滑油射流的冲击飞溅量;在考虑风阻影响的情况下得到的滑油损失角小于对应的理论分析结果;11000 r/min转速下,增加收油叶片半径差后收油效率可提高超过3.0%,在一定转速范围内调整收油叶片的半径差可降低滑油的冲击飞溅量、提高收油效率。To study the matching relationship between the structural parameters and the working condition parameters of the oil scoop blade,the effects of the radius difference of the oil scoop blade,the injection angle of the oil jet nozzle,the rotating speed of the oil scoop,and the oil velocity on the oil loss angle and oil capture efficiency are studied by theoretical analysis and numerical simulation.The results show that the impact point position of the oil jet impinging on the outer contour of the oil scoop blade can be changed by adjusting the injection angle and the radius difference of the oil scoop blade.The former has less influence,and the latter can reduce the impact splash amount of the lubricant oil at low oil jet velocity.Considering the influence of wind resistance,the oil loss angle obtained is less than the corresponding theoretical analysis result.The oil capture efficiency can be increased by more than 3.0%by increasing the radius difference of the oil scoop blade at the rotating speed of 11000 r/min.Adjusting the radius difference of the oil scoop blade within a certain rotating speed range can reduce the impact splash amount of the lubricant oil and improve the oil capture efficiency.

关 键 词：径向收油环 半径差 喷射角度 油气两相流 收油效率 

分 类 号：V233.4[航空宇航科学与技术—航空宇航推进理论与工程]