推重比15一级发动机有关总体性能的关键技术和难点分析  

Performance Related Key Technologies and Difficulties of Engines with Thrust to Weight Ratio up to Level of 15

作　　者：陈大光[1] 张津[1] 朱之丽[1] 

机构地区：[1]北京航空航天大学404教研室,北京100083

出　　处：《航空动力学报》2001年第1期8-12,7,共6页Journal of Aerospace Power

摘　　要：本文从发动机总体性能方面分析了推重比 1 5一级发动机设计研制的关键技术及难点。文章首先根据典型飞行任务 ,对推重比 1 5一级加力涡扇发动机的最有利循环参数进行了一体化分析。矢量喷管是先进战斗机的特征 ,本文讨论了实现推力矢量存在的技术难点。降低发动机研制成本和缩短研制周期是发展先进发动机的重要要求。发动机数值仿真技术是解决这些要求的重要途径之一 ,应给予足够重视。发动机状态监视和故障诊断技术可提高发动机工作可靠性并降低直接使用费 ,本文对故障诊断技术的发展和关键技术作了分析。最后对新型发动机的发展 。Performance-related critical technologies and difficulties in the development of engines with a thrust to weight ratio up to the level of 15 are considered.For typical flight roles,the selection of optimum cycle parameters of augmented turbofan engines based on integrated analysis is discussed.As thrust vectoring nozzle is the feature of advanced fighters,the difficulties in implementing thrust vectoring are summarized.The reduction of development cost and time consumed for development is very imporant.Numerical propulsion system simulation is one of the effective ways for engine design and development,as well as cost and time saving and must be the center of our attention.Engine condition monitoring and fault diagnosis may enhance engine operating safety and reduce direct operating cost,so that the development trend and key techniques of fault diagnosis are also surveyed.In conclusion some important tasks are presented.

关 键 词：航空发动机 性能 关键技术 推重比15一级加力涡扇发动机 

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]