基于核心机的GTF发动机方案研究  

Investigation of GTF Engine Based on Core Engine

作　　者：齐晓雪[1] 郝勇[1] 唐宇峰[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2014年第3期40-44,共5页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：齿轮传动风扇(GTF)发动机具有部件效率高、噪声低、级数少和质量轻的特点,是未来大型民用发动机的主要发展方向之一。为加快后续发动机的发展,在现有核心机的基础上,通过发动机典型气动循环参数的匹配分析,完成GTF发动机总体性能设计方案。分析了涵道比、风扇外涵压比、低压压气机压比、传动比等参数对GTF发动机性能的影响,初步确定参数选取范围。通过对比相同涵道比的GTF发动机与常规结构发动机,其推力和耗油率等性能指标基本接近,但GTF发动机具有低压部件级数显著减少的优点;总结了GTF发动机特有的关键技术。With fewer but more efficient parts,lower noise level and light weight,Geared Turbo Fan（GTF） has become one of the main develop options for futures large civil engines.In order to promote further development of the engine,this paper studied the matching of typical pneumatic cycle parameters,and finally accomplished GTF engine general aerodynamic design,based on the existing core engine.It analyzed influence on the performance of GTF engine in several aspects,such as the bypass ratio,outer fan pressure ratio,low pressure compressor pressure and gear ratio,and then primarily confirmed the range of parameters.Compared with conventional configuration engines that have the same bypass ratio,GTF can achieve nearly the same performance targets such as thrust and SFC,but it is advanced in fewer LP component stages.Finally,the main key technologies for GTF design were summarized.

关 键 词：齿轮传动风扇发动机 民用发动机 核心机 气动循环参数 关键技术 

分 类 号：V235.131[航空宇航科学与技术—航空宇航推进理论与工程]