某型涡扇发动机润滑系统高空适应性改进设计  

Improved design of high altitude adaptability on a turbo-fan aero-engine's lubricating system

作　　者：王灵锋[1] 郭迎清[1] 张效伟[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《机械设计与制造》2005年第12期1-3,共3页Machinery Design & Manufacture

摘　　要：某新型高空长航时无人机动力装置是在国产某涡扇发动机的基础上改进设计的。为了解决其润滑系统高空适应性问题,这里利用原型机润滑系统主要元件(滑油泵、燃滑油散热器等)和整机地面实验数据,结合理论分析与计算,建立了润滑系统的供油系统和冷却系统的数学模型,对原型机润滑系统进行了详细全面的计算和分析。在此基础上,提出了润滑系统适应高空性能的改进设计方案,即在保持流量基本不变的情况下降低滑油泵转速,在气路上增设高空活门。A new - type engine for a high altitude long endurance （HALE） UAV is designed on the basis of a turbo -fan aero - engine. In order to improve its lubricating system adaptability at the high altitude, we built the lubricating system mathematics models including oil supply subsystem and cooling subsystem. Then we modified the models by the use of experimental data of the prototype lubricating system and its main components （oil pump, fuel - oil heater exchanger, etc. ）. Finally we analyzed the prototype lubricating system adaptability at the high altitude in detail. On this basis, an improved design plan has proposed for the lubricating system altitude adaptability, that is to reduce the rotational speed of oil pump while keeping the flow not changing basically and set up high altitude valves on the ventilation pipeline system more.

关 键 词：高空长航时无人机 润滑系统 高空适应性 

分 类 号：TH16[机械工程—机械制造及自动化]