| 尾缘吹气式稳定器后体角对燃烧性能影响的试验 |
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| 引用本文： | 杨阳,马文杰,樊未军,岳明,杨茂林.尾缘吹气式稳定器后体角对燃烧性能影响的试验[J].航空动力学报,2008,23(5):851-857. |
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| 作者姓名： | 杨阳 马文杰 樊未军 岳明 杨茂林 |
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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,北京,100083 |
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| 摘 要： | 通过数值模拟了后体角为60°,120°和180°三种尾缘吹气稳定器的回流区,试验测试了后两种稳定器的冷态雾化场、贫熄边界和燃烧效率,从而研究了尾缘后体角改变对其燃烧性能的影响.试验结果表明由于后体角直接影响回流区大小和雾化质量,从而影响稳定器的燃烧性能.燃烧试验表明120°尾缘吹气稳定器贫熄边界和燃烧效率优于后体角为180°的稳定器和槽宽大50%的V型稳定器.
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| 关 键 词： | 航空、航天推进系统 火焰稳定器 气动稳定 加力燃烧 雾化测试 |
| 文章编号： | 1000-8055(2008)05-0851-07 |
| 收稿时间： | 2007/4/30 0:00:00 |
| 修稿时间： | 2007年4月30日 |
Experimental investigation on the effects of base plan angle on flameholders' combustion performance |
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| YANG Yang,MA Wen-jie,FAN Wei-jun,YUE Ming and YANG Mao-lin.Experimental investigation on the effects of base plan angle on flameholders'' combustion performance[J].Journal of Aerospace Power,2008,23(5):851-857. |
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| Authors: | YANG Yang MA Wen-jie FAN Wei-jun YUE Ming and YANG Mao-lin |
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| Institution: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | The recirculating zone of edge blowing mixture curtain flameholders with base plan angle 60°,120°and 180°was simulated numerically.An experimental investigation of the base plan angle 120°and 180°flameholders atomization,lean limit of the flame stabilization and combustion efficiency was conducted.So,the effects of angle variety of edge base plan on the combustion performance were studied.The test experiments show that,when the base plan angle is 120°,the lean limit of the flame stabilization is wider and combustion efficiency is superior to that of 180°and a Vgutter.It is possible to apply in future afterburner. |
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| Keywords: | aerospace propulsion system flame holder aerodynamic stabilization afterburning atomization measure |
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