涡扇发动机进口畸变条件下的优化控制规律

吴斌; 黄金泉; 叶巍; 王克宏

doi:10.13224/j.cnki.jasp.2015.03.027

涡扇发动机进口畸变条件下的优化控制规律

doi: 10.13224/j.cnki.jasp.2015.03.027

吴斌^1,2,
黄金泉^1,2,
叶巍³,
王克宏³

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京210016;
2. 先进航空发动机协同创新中心, 北京 100191;
3. 中国航空工业集团公司中国燃气涡轮研究院, 成都 610500

基金项目:

江苏省普通高校研究生科研创新计划资助项目(CXZZ12_0166)

中央高校基本科研业务费专项资金(NS2013017)

详细信息

作者简介:
吴斌(1985-),男,江苏大丰人,博士生,主要从事航空发动机控制研究.

中图分类号: V233.7
计量
- 文章访问数: 1584
- HTML浏览量: 225
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- 被引次数: 0
出版历程
- 收稿日期: 2013-10-23
- 刊出日期: 2015-03-28

Optimizated control scheme for turbofan engine under inlet distortion conditions

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
3. China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China

摘要

摘要: 提出了一种满足涡扇发动机不同进口畸变要求的控制规律.在涡扇发动机低进口畸变条件下通过提高增压比来提高性能,在高进口畸变条件下降低增压比并辅助导叶角调节以提高发动机裕度.根据不同的进口畸变条件下的裕度要求,提出了带边界缓冲区的差分进化算法(DEBZ),在包线内优化获取发动机增压比及导叶角控制规律.结合模型、控制器和控制规律完成涡扇发动机全包线仿真.仿真结果表明:采用该控制规律在畸变指数为2的条件下,涡扇发动机推力性能能够提高8%以上,而在畸变指数为8的条件下,涡扇发动机的可用裕度可以满足稳定要求,同时推力性能能够提高1%以上.
- 涡扇发动机 /
- 裕度 /
- 进口畸变 /
- 差分进化 /
- 边界缓冲区 /
- 控制规律
Abstract: A control scheme of satisfying different inlet distortions was proposed for turbofan engine. The turbofan-engine performance was improved by increasing the pressure ratio under low inlet distortion conditions, and the pressure ratio was reduced with addition of guide vane adjustment to provide additional stall protection at high inlet distortion. By using the differential evolution algorithm with border buffer zone(DEBZ), the control scheme of the turbofan engine pressure ratio and variable guide vanes in envelope was optimized and obtained according to the requirements of stall margin with different inlet distortions. The simulation over full envelope was accomplished with the model, control algorithm and control scheme. Using the proposed control scheme, the simulation results show that thrust performance of turbofan engine can be improved more than 8% when the distortion index is 2, and the stall margin requirements can be satisfied when the distortion index is 8 with more than 1% thrust performance improvement.
- turbofan engine /
- stall margin /
- inlet distortion /
- differential evolution /
- border buffer zone /
- control scheme

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参考文献(19)

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