航空发动机附件机匣喷嘴结构优化设计与流量分配研究  

Investigation on Structural Optimization Design and Flow Distribution of Jet Nozzles in Aero-Engine Accessory Gearboxes

作　　者：张华军 李炎军 姜乐 徐永强 ZHANG Huajun;LI Yanjun;JIANG Le;XU Yongqiang(Military Representative Office of Chengdu Bureau of Air Force Equipment Department,Chengdu Sichuan 610500,China;AECC Sichuan Gas Turbine Establishment,Chengdu Sichuan 610500,China;School of Power and Energy,Northwestern Polytechnical University,Xi′an Shaanxi 710129,China)

机构地区：[1]空装成都局某军事代表室,四川成都610500 [2]中国航发四川燃气涡轮研究院,四川成都610500 [3]西北工业大学动力与能源学院,陕西西安710129

出　　处：《润滑与密封》2024年第12期98-105,共8页Lubrication Engineering

基　　金：国家科技重大专项(J2022-Ⅳ-0003-0020)

摘　　要：为通过优化航空发动机附件机匣供油喷嘴结构以达到流量精确分配的目的,根据附件机匣内置流路及喷嘴的流动特点,基于Volume of Fluid(VOF)两相流方法建立三维数值仿真计算模型,结合一维流量特性关联式提出一维-三维耦合迭代求解方法,并探究附件机匣全流路的压力分布以及供油压力和节流孔直径对总流量的影响规律,并对喷嘴结构进行优化设计以满足流量分配需求。结果表明,节流孔、支路交叉连接处存在显著的流动损失,不同支路的压力差异较大,同一支路的压力相差很小,同时总滑油流量受供油压力和节流孔直径的影响较大。在数值仿真和关联式计算结果相互印证的基础上,经过六次耦合迭代计算,获得了满足所有供油喷嘴流量设计要求的供油压力、节流孔及喷孔参数。To optimize the structure of the oil jet nozzle in the accessory gearbox for improved flow distribution,a three-dimensional numerical simulation model was developed based on the Volume of Fluid(VOF)method,taking into account the flow characteristics of the internal flow paths and jet nozzles.By integrating a one-dimensional flow rate characteristic correlation,a one-dimensional and three-dimensional coupled iterative solution method was proposed.The pressure distribution throughout the entire flow path of the accessory gearbox was explored,and the impact of oil supply pressure and throttle orifice diameter on total flow rate was analyzed.The results indicate that there is significant flow losses at the throttling orifices and at the intersections of the branches.The considerable pressure differences are observed between different branches,while pressure variations within the same branch are minimal.The total lubricating oil flow rate is greatly affected by the supply pressure and the diameter of the throttle hole.Based on the mutual validation of numerical simulations and correlation calculations,a coupled iterative computation was performed,leading to the determination of the optimal supply pressure,throttling orifice diameter,and orifice parameters that meet all design requirements for the jet nozzles.

关 键 词：喷嘴 节流孔 供油压力 航空发动机 流量分配 

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]