基于Fibonacci搜索方法的航空发动机性能寻优
发布时间：2018-10-31 07:16
【摘要】：介绍了Fibonacci搜索方法应用于发动机性能优化中的原理,建立带两个出口面积、气流马赫数可变的引射器的涡喷发动机的总体性能计算模型,应用Fibonacci搜索方法在优化参数区间内对该发动机进行了最大推力、最低油耗、最低涡轮前温度模式的寻优.举例说明了Fibonacci搜索方法应用的具体过程.给出了不同高度、马赫数下的寻优结果.结果表明:最优目标性能满足的约束边界与飞行高度、马赫数密切相关.不同的飞行高度、马赫数对应了不同的最优控制策略.但不论飞行任务如何,根据该方法进行的优化控制所获得的目标性能是最佳的.该优化方法不仅适用于该类涡喷发动机,也为其他类型航空发动机的优化控制打下一定的基础.
[Abstract]:The principle of applying Fibonacci search method to engine performance optimization is introduced. The overall performance calculation model of turbojet engine with two exit areas and variable flow Mach number is established. The Fibonacci search method is used to optimize the engine's maximum thrust, minimum fuel consumption and minimum turbine front temperature mode in the optimization parameter range. An example is given to illustrate the application of Fibonacci search method. The optimization results at different heights and Mach numbers are given. The results show that the constraint boundary of the optimal target performance is closely related to the flight altitude and Mach number. At different flight altitudes, Mach numbers correspond to different optimal control strategies. However, regardless of the mission, the target performance obtained by the optimization control based on this method is the best. This optimization method is not only suitable for this kind of turbojet engine, but also lays a foundation for the optimization control of other types of aeroengine.
【作者单位】： 中国航空工业集团公司中国燃气涡轮研究院;
【分类号】：V233.7
本文编号：2301368
[Abstract]:The principle of applying Fibonacci search method to engine performance optimization is introduced. The overall performance calculation model of turbojet engine with two exit areas and variable flow Mach number is established. The Fibonacci search method is used to optimize the engine's maximum thrust, minimum fuel consumption and minimum turbine front temperature mode in the optimization parameter range. An example is given to illustrate the application of Fibonacci search method. The optimization results at different heights and Mach numbers are given. The results show that the constraint boundary of the optimal target performance is closely related to the flight altitude and Mach number. At different flight altitudes, Mach numbers correspond to different optimal control strategies. However, regardless of the mission, the target performance obtained by the optimization control based on this method is the best. This optimization method is not only suitable for this kind of turbojet engine, but also lays a foundation for the optimization control of other types of aeroengine.
【作者单位】： 中国航空工业集团公司中国燃气涡轮研究院;
【分类号】：V233.7
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，本文编号：2301368
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