| 曹铭栋，王 昭，高靖俞，樊 巍，刘 兵.基于飞/发性能一体化快速迭代的循环参数匹配[J].航空发动机,2024,50(1):35-43 |
| 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 |
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| DOI： |
| 中文关键词: 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 |
| 英文关键词:high bypass turbofan engine aircraft/engine performance integration fast iteration coupled iteration overall
performance parameter optimization |
| 基金项目:航空动力基础研究项目资助 |
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| 摘要点击次数: 397 |
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| 中文摘要: |
| 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。 |
| 英文摘要: |
| 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. |
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