| 整流支板和火焰稳定器的一体化设计及性能分析 |
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| 引用本文： | 李锋,程明,郭瑞卿,尚守堂,唐正府,李龙贤.整流支板和火焰稳定器的一体化设计及性能分析[J].航空动力学报,2012,27(10):2169-2174. |
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| 作者姓名： | 李锋 程明 郭瑞卿 尚守堂 唐正府 李龙贤 |
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| 作者单位： | 1. 北京航空航天大学能源动力学院,北京,100191
2. 北京航空航天大学能源动力学院,北京100191 中国航空工业集团公司沈阳发动机设计研究所,沈阳110015 |
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| 基金项目： | 国家自然科学基金(90716025,50476005) |
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| 摘 要： | 针对航空发动机高推质比、高隐身的需求，提出一种加力燃烧室整流支板和火焰稳定器一体化设计的方法，并开展了相关模型加力燃烧室的计算和试验研究.研究结果表明：采用一体化设计加力燃烧室能够缩短加力燃烧室长度，人幅降低非加力状态的冷态流阻，明显改善发动机加力燃烧室的性能，提高发动机的推质比.可为解决高推质比、高隐身发动机技术提供了一种新的思路和研究方向.
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| 关 键 词： | 一体化整流支板 整流支板设计 火焰稳定器 加力燃烧室 冲压燃烧室 |
| 收稿时间： | 2012/5/23 0:00:00 |
Frame plate and flame holder integration design and capability analysis |
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| LI Feng,CHENG Ming,GUO Rui-qing,SHANG Shou-tang,TANG Zheng-fu and LI LONG-xian.Frame plate and flame holder integration design and capability analysis[J].Journal of Aerospace Power,2012,27(10):2169-2174. |
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| Authors: | LI Feng CHENG Ming GUO Rui-qing SHANG Shou-tang TANG Zheng-fu and LI LONG-xian |
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| Institution: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China;Shenyang Aeroengine Design and Research Institue, Aviation Industry Corporation of China,Shenyan 110015,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China;Shenyang Aeroengine Design and Research Institue, Aviation Industry Corporation of China,Shenyan 110015,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China;Shenyang Aeroengine Design and Research Institue, Aviation Industry Corporation of China,Shenyan 110015,China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191 ,China |
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| Abstract: | Based on the increasing demand for high thrust weight ratio and high stealthy aero-engine,the design method of integration design frame plate and flame holder afterburner was given and some model afterburner simulations and experiments were conducted.The results show that the length and can flow resistance could be reduced greatly,and the capability and thrust weight ratio of aero-engine can be increased apparently.This work would help to provide a new research direction and method for high thrust weight ratio and high stealthy aero-engine technology. |
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| Keywords: | integration frame plate frame plate design flame holder afterburner ramjet burner |
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