多用途战斗机/涡扇发动机一体化循环参数优化

Integrated Design Optimization of Turbofan Engines Cycle for Multi-role Fighters

针对多用途战斗机的特点,发展了基于飞/发一体化的涡扇发动机循环参数优化设计模型和相应的计算程序,优化设计模型中包括双变量控制涡扇发动机特性计算模型、进排气系统安装特性计算模型、飞机气动特性分析模型、重量组成分析模型、任务剖面分析模型、约束分析与任务分析模型和优化计算模型等。重点研究了多用途战斗机约束边界的获得方法,利用多岛遗传算法和自适应模拟退火优化算法,分别对现役多用途战斗机、不加力超声速巡航多用途战斗机以及下一代先进多用途战斗机用涡扇发动机循环参数进行了优化计算,对计算结果进行了分析,获得了对多用途战斗机用涡扇发动机循环参数选择有指导意义的结论。

For studying the method of cycle parameters design optimization of turbofan engine,an integrated optimization design model of multirole fighters and turbofan engines is presented,and the computer program based on the model is developed.The model includes a bivariate controlled turbofan engine performance computing model,installed performance computing model,fighter dynamic analysis model,weight composing analysis model,mission profile analysis model,constraint and mission analysis model,and optimization computing model,etc.The study emphasis is to find the way of getting the constraint limitations of multi-role fighters.The multi-island genetic algorithm and adaptive simulated annealing are used to implement the cycle parameters design optimization for multi-role fighters in service,supercruising multi-role fighters without after-burning,and next generation advanced multi-role fighters.Some valuable conclusions for cycle parameters choice of turbofan engine are gained by analyzing the computation results.