大涵道比涡扇发动机试飞平台动力装置系统设计  

Design of Propulsion System for Testing Platform of Large Bypass Turbofan Engine

作　　者：吕其明[1] 刘虎平[1] 钟剑龙[1] 

机构地区：[1]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《航空科学技术》2015年第12期20-25,共6页Aeronautical Science & Technology

摘　　要：为满足大涵道比涡扇发动机试飞平台研制需要,开展了基于试飞平台的动力装置系统设计。主要包括发动机安装系统、地面配套补加工、发动机舱通风冷却、发动机供回油系统、火警探测及灭火系统等分系统设计。设计中采用了全三维电子样机设计,采用了流体仿真计算技术对分系统性能进行了优化。通过地面调试及飞行试验表明系统工作可靠,满足性能指标要求。该设计方法可以为以后类似系统设计提供参考。According to the request of flight testing platform for large bypass turbofan engine, the propulsion system based on the testing platform was designed. The systems consists of installation system, ground support and processing, venting and cooling system, fuel supplying and returning system, fire detection and extinguish subsystems. 3D digital mockup technology was applied in the design and CFD simulation was used for performance optimization of the system. The system was validated to be reliable by the ground test and flight test, and performance met the requirements. The design method can be a reference for the systems＇ design in the future.

关 键 词：大涵道比 涡扇发动机 全权限数字电子控制器 冗余设计 试飞平台 动力装置 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]