内部混合式油雾应急润滑系统引射结构几何影响因素研究  

Geometric Influencing Factors of Ejector in Internal-Mixing Oil Mist Emergency Lubrication System

作　　者：朱鹏飞[1] 汪峰 胡剑平[1] 张丽芬[1] 刘振刚 ZHU Peng-fei;WANG Feng;HU Jian-ping;ZHANG Li-fen;LIU Zhen-gang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;AECC Aero Engine Control System Institute,Wuxi 214000,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航发控制系统研究所,江苏无锡214000

出　　处：《推进技术》2023年第9期30-39,共10页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅲ-0023-0067)。

摘　　要：为探究结构参数对应急润滑系统引射结构性能的影响,以某型航空发动机内部混合式油雾应急润滑系统引射结构为对象,通过油气两相流数值模拟并结合试验验证,分析了空气喷嘴直径、滑油引油管直径等结构参数对滑油引射流量、引射系数的影响规律,并基于敏感性分析方法,获得了引射滑油流量关于不同结构参数的敏感性系数。结果表明,滑油引射流量的计算结果与试验结果最大误差不超过11%;存在最佳的空气进口段直径、空气喷嘴直径和混合室直径使得引射滑油流量达到最大,而滑油流量随空气喷嘴出口直径、引油管直径的增大呈现出逐渐增加的趋势;对比分析各结构参数敏感性系数,发现混合室直径、空气进口段直径、引油管直径是影响引射结构性能的三个重要参数。In order to explore the influence of geometric parameters on the performance of ejector in emer gency lubrication system,the ejector in oil mist emergency lubricating oil system of an aeroengine is taken as the object.Through the numerical simulation of oil-gas two phase flow and verification experiment,the effects of vari ous geometric parameters such as the diameter of air nozzle and oil pipe on the oil flowrate ejected and ejection co efficient are investigated.Based on sensitivity analysis,the sensitivity coefficients of the oil flowrate with respect to different geometric parameters are obtained.Comparison between experimental data with calculated values shows that the maximum error of oil mass flowrate is less than 11%.There are optimal values for the air inlet diam eter,air nozzle diameter and mixing chamber diameter to maximize the oil flow rate.Moreover,the oil flow rate increases with the increase of air nozzle outlet diameter and oil pipe diameter.By comparing the sensitivity coeffi cients of geometric parameters,it is found that mixing chamber diameter,air inlet diameter and oil pipe diameter are three important parameters that affect the ejecting performance.

关 键 词：航空发动机 应急润滑系统 引射结构 试验验证 敏感性分析 

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]