| 标 题： |
A Comparative Study on the Overall Performance Schemes of Small Turbofan Engines for Business Jet Applications
商用飞机应用小型涡扇发动机整体性能方案的比较研究 |
| 作 者： |
Sihan Lan
Hailong Tang
Jiyuan Zhang |
| 关键词： |
Small turbofan engine [小型涡扇发动机]
Overall performance [ 整体性能]
Scheme design [ 方案设计]
Cycle parameter selection [ 循环参数选择]
Engine characteristics [ 发动机特性] |
| 出版年： |
2026 |
| 文集名： |
Proceedings of the 2nd Aerospace Frontiers Conference (AFC 2025), Volume IV
第二届航空航天前沿会议（AFC 2025）论文集，第四卷 |
| 会议名： |
2nd Aerospace Frontiers Conference (AFC 2025)
第二届航空航天前沿大会（AFC 2025） |
| 届 次： |
2nd |
| 摘 要： |
Addressing the demand for small turbofan engines in the 600-800 kg thrust range for light business jets, this paper proposes three overall performance schemes with varying levels of technological maturity through comparative analysis of existing turbofan engine design parameters, combined with cycle parameter optimization and future technological trends. By constructing an overall performance model for a small separate-flow turbofan engine, three engine schemes with thrust levels of 600 kg, 700 kg, and 800 kg were designed, and control laws and off-design point characteristics were analyzed. The results indicate that increasing the turbine inlet temperature, compressor pressure ratio, and bypass ratio significantly enhances engine performance. Among the schemes, an improved configuration with a booster stage achieved a 19% thrust increase at a lower turbine inlet temperature, demonstrating the effectiveness of configuration innovation. This study provides theoretical and technical references for the design and optimization of small turbofan engines.
针对轻型商务飞机对600-800公斤推力小型涡扇发动机的需求，本文通过对比现有涡扇发动机设计参数，并结合循环参数优化及未来技术发展趋势，提出了三种不同技术成熟度的整体性能方案。基于小型离心涡扇发动机的整体性能模型，设计了推力分别为600公斤、700公斤和800公斤的三种发动机方案，并分析了其控制律与非设计点特性。结果表明，提高涡轮入口温度、压比和旁通比可显著提升发动机性能。在各方案中，采用增压级改进的配置在较低涡轮入口温度下实现了19%的推力提升，验证了构型创新的有效性。本研究为小型涡扇发动机的设计与优化提供了理论和技术参考。 |
| 中文内容为网络AI翻译，专业术语未必准确，仅供参考。 |
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