航空发动机推重比技术指标研究  

Research on thrust-weight ratio of aero-engine

作　　者：孟令勇[1] 高海红[1] 郑天慧[1] 郭琦[1] 

机构地区：[1]中国燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2016年第2期57-62,共6页Gas Turbine Experiment and Research

摘　　要：以战斗机动力中的推重比指标为研究对象,分析了欧美预研计划中提出的推重比发展目标,及其在具体型号产品中的发展,重点分析了F119发动机推重比指标的实现情况。结果表明:推进系统技术发展指导思想,已从将推重比和耗油率作为技术评价体系改为强调向系统综合要效益;F119发动机采用了预研计划中的高推重比先进技术,但其实际推重比并未达到10;战斗机动力型号产品研发中应秉持全面平衡的指导思想,避免唯性能论。Taking thrust-weight ratio of fighter as the research object, the goal of thrust-weight ratio pro-posed in advanced development programs in Europe and U.S. and its development in specific type was in-vestigated. And the realization of thrust-weight ratio goal for F119 was focused. The results show that the guideline of propulsion technology has been transferred from performance-oriented to comprehensive sys-tem integration in the latest decade. The thrust-weight ratio of F119 is far from class-10 though advanced technologies were adopted from advanced development programs. Compromise between performance, reli-ability, maintainability, affordability and program schedule should be taken into practice during fighter en-gine research and development.

关 键 词：航空发动机 推重比 矢量喷管 平衡设计 F119 预研计划 型号研制 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]