| 复合式收扩套筒空气雾化喷嘴燃烧室点火研究 |
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| 引用本文： | 林宇震,林培华,许全宏,刘高恩.复合式收扩套筒空气雾化喷嘴燃烧室点火研究[J].航空动力学报,2007,22(3):342-346. |
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| 作者姓名： | 林宇震 林培华 许全宏 刘高恩 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院,航空发动机气动热力重点实验室,北京,100083 |
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| 摘 要： | 复合式收扩套筒空气雾化喷嘴中,副油路是一个单油路离心喷嘴,主油路采用双旋流空气雾化,喷嘴是直射式.在点火研究中,只是单油路离心喷嘴工作.实验用的燃烧室是一个单头部矩形燃烧室,在燃烧室进口温度为常温,进口压力为常压,燃烧室压力降0.9%～9.0%的试验条件下研究了复合式空气雾化喷嘴燃烧室的点火性能.在同样条件下,研究了复合式空气雾化喷嘴的雾化性能并总结了经验关系.分析了影响点火的主要因素,通过整理雾化数据,以Lefebvre点火模型为基础,总结了该类燃烧室点火经验关系.
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| 关 键 词： | 航空、航天推进系统 航空发动机 燃烧室 点火 复合式空气雾化喷嘴 模型 复合式 套筒 空气雾化 雾化喷嘴 燃烧室 研究 hybrid performance ignition 点火模型 数据 整理 因素 影响点 分析 经验关系 雾化性能 试验条件 点火性能 压力降 |
| 文章编号： | 1000-8055(2007)03-0342-05 |
| 收稿时间： | 2006/3/22 0:00:00 |
| 修稿时间： | 2006年3月22日 |
Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve |
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| LIN Yu-zhen,LIN Pei-hu,XU Quan-hong and LIU Gao-en.Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve[J].Journal of Aerospace Power,2007,22(3):342-346. |
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| Authors: | LIN Yu-zhen LIN Pei-hu XU Quan-hong and LIU Gao-en |
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| Institution: | School of Jet Propulsion, National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | For a hybrid airblast atomizer combustor with convergent-divergent sleeve,a simplex pressure swirl nozzle is used for the primary fuel circuit,and a direct-injection airblast atomizer is used for the main fuel circuit.Only the pilot simplex nozzle was operated in the ignition tests.The test combustor is a single-nozzle rectangular combustor,with normal inlet temperature and normal inlet pressure.Under the test condition of pressure drop of 0.9%-9.0%,the ignition performance of hybrid airblast atomizer combustor was analyzed.And,the atomization performance of this hybrid atomizer was also summarized to obtain the empirical correlation under the same condition.While major influential factors to ignition were analyzed,the empirical correlation of such combustors was summarized based on the atomization data and Lefebvre's ignition model. |
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| Keywords: | aerospace propulsion system aircraft engine combustor ignition hybrid airblast atomizer model |
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