民用涡扇发动机结构与建模分析研究  

Investigation of Civil Turbofan Structure and Components Modeling

作　　者：雷杰[1] 苏三买[1] 周顾庭 李适[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空工程进展》2013年第4期450-457,共8页Advances in Aeronautical Science and Engineering

基　　金：航空科学基金(2013ZB53019);航空推进技术验证计划(APTD-2012-01)

摘　　要：数学模型是航空发动机性能仿真与控制系统设计的重要技术基础,针对民用涡扇发动机建模需求,以广泛使用的大涵道比涡扇发动机为研究对象,参考国外经验并结合理论分析,进行与整机建模相关的发动机主要部件结构特点和部件建模方法研究,给出发动机大风扇特性分解方法,分析空气引气系统、压气机稳定性控制系统、涡轮叶尖间隙控制系统、反推力装置等系统的结构和建模方法,以期为民用大涵道比涡扇发动机整机建模提供技术支持。Mathematical model is an important technical foundation for aircraft engine performance simulation and control system design. In order to meeting the needs for civil turbofan modeling, a high bypass ratio turbo fan engine is taken as the research object to investigate the structural features and component modeling methods of engine main components related to lhe whole engine modeling. Combining foreign experience with theoretical analysis, the big fan component characteristic decomposing methods, structure and modeling methods of engine air bleed system, compressor stahility control system, turbine blade tip clearance control system and thrust re verser device arc investigated in detail. Which is to provide technical support for high bypass ratio turbofan engine.

关 键 词：大涵道比涡扇发动机 结构特点与数学模型 导叶与稳定性 空气系统 涡轮叶尖间隙 反推力装置 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]