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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。
In order to meet the needs of future fighter jets, TRIZ innovation theory and its solution tools are introduced into the innovative design of high thrust and heavy ratio engine programs. Aiming at the two major problems in the development of high thrust-to-weight ratio engine, a technical contradiction analysis is carried out, the corresponding principle of contradiction resolution (No.1 segmentation principle and No.15 dynamic characteristic principle) is obtained from the contradiction matrix, and a creatively constructed variable tunneling core Turbofan engine-driven fan concept program to meet the future high thrust-to -ration ratio turbofan engine wide envelope, the technical characteristics of long-term requirements.