摘要
从满足未来战斗机需求出发,将TRIZ创新理论及其解题工具引入到高推重比发动机方案创新设计中。针对高推重比发动机发展中的两个重要问题进行技术矛盾分析,由矛盾矩阵得到相应的矛盾解决原理(No.1分割原理和No.15动态特性原理),创造性地构建出可变涵道核心机驱动风扇的涡扇发动机概念方案,满足了未来高推重比涡扇发动机宽包线、长航时的技术特征要求。
The TRIZ theory and its solving tools were introduced to the innovation concept design of aero- engine with high thrust-to-weight ratio to meet requirements of future fighter. The conflict of two important problems which aim at the development of high thrust-to-weight ratio engine was analyzed technically, and the corresponding conflict solving principle including the 1st segmentation principle and the 15th dynamic characteristics principle were obtained by using the contradictious matrix. The concept plan for variable by- pass core-driven fan stage （CDFS） requirements of wide envelop and engine. turbofan engine was creatively long endurance characteristics constructed and it can meet the technical for the future high thrust-to-weight ratio engine.
出处
《燃气涡轮试验与研究》
北大核心
2013年第2期59-62,共4页
Gas Turbine Experiment and Research
关键词
高推重比发动机
变循环发动机
核心机驱动风扇
TRIZ理论
创新设计
high thrust-to-weight ratio aero-engine
variable cycle engine
core-driven fan stage （CDFS）
TRIZ theory
innovation design
