基于飞/发性能一体化快速迭代的循环参数匹配
Cycle Parameters Matching Design Based on Fast Iterative Aircraft/Engine Performance Integration
曹铭栋 1王昭 1高靖俞 1樊巍 1刘兵1
作者信息
- 1. 中国航发四川燃气涡轮研究院,成都 610500
- 折叠
摘要
针对150 kN级大涵道比涡扇发动机总体性能参数匹配设计问题,以A340-300飞机对发动机的任务需求为例,采用基于飞/发性能一体化快速迭代优化方法,将飞机/发动机一体化设计与发动机总体性能优化设计进行耦合迭代,对多约束条件下的大涵道比涡扇发动机总体性能方案进行优化设计.结果表明:在保证发动机满足飞机任务需求和任务载荷要求,以及发动机尺寸、质量、污染排放要求等约束条件下,飞机的最大起飞质量较初始方案减轻约14.33％,较A340-300飞机的最大起飞质量减轻约8％～9％;燃油消耗量较初始方案减少约20.6％;在保证发动机与飞机良好匹配性的前提下,通过飞发优化迭代使发动机和飞机的设计难度都有一定程度地降低.采用的研究思路与方法是合理、可行的,具有工程实用价值.
Abstract
Aiming at the overall performance parameters matching design for a 150kN class high bypass ratio turbofan engine,taking the mission requirements of A340-300 aircraft as an example,a fast iterative optimization method based on aircraft/engine performance integration is adopted to couple and iterate the aircraft/engine integration design and engine overall performance design,thus to optimize the design of the overall performance scheme for high bypass ratio turbofan engine with multiple constraints.The results show that when the engines meet the mission and payload requirements of the aircraft,as well as constraints in terms of size,weight,and emission,the maximum take-off weight of the aircraft is reduced by 14.33％,and about 8％-9％lower compared with the actual maximum take-off weight of A340-300 aircraft;the fuel consumption is about 20.6％lower than that of the original scheme.On the premise of ensuring a good match between the engine and the aircraft,the design difficulty of both the engine and the aircraft is reduced to a certain extent through iterative optimization of the aircraft/engine integration.The ideas and methods are reasonable,feasible,and have practical engineering value.
关键词
大涵道比涡扇发动机/飞/发性能一体化/快速迭代/耦合迭代/总体性能参数/优化Key words
high bypass turbofan engine/aircraft/engine performance integration/fast iteration/coupled iteration/overall performance parameter/optimization引用本文复制引用
出版年
2024
NETL
NSTL
万方数据