| 扩张段注气对扩张型双喉道喷管起动的影响研究 |
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| 引用本文： | 王健,额日其太.扩张段注气对扩张型双喉道喷管起动的影响研究[J].航空工程进展,2011,2(3):318-322,329. |
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| 作者姓名： | 王健 额日其太 |
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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,北京,100191 |
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| 摘 要： | 扩张型双喉道喷管存在起动问题,使喷管推力性能显著下降。为此,提出了扩张段注气解决喷管起动问题的方案,并利用数值模拟方法,针对二元扩张型双喉道喷管,研究了扩张段注气压比、注气位置等对喷管流动和性能的影响。研究结果表明：扩张段注气可以产生斜激波系和大的分离区,改变了扩张型双喉道喷管主气流通道的形状,减小了激波损失,解决了喷...
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| 关 键 词： | 矢量喷管 双喉道喷管 扩张段注气 射流控制 |
Effect of Injection at Divergent Section on Starting Problem of Divergent Dual Throat Nozzle |
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| Wang Jian,Eriqitai.Effect of Injection at Divergent Section on Starting Problem of Divergent Dual Throat Nozzle[J].Advances in Aeronautical Science and Engineering,2011,2(3):318-322,329. |
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| Authors: | Wang Jian Eriqitai |
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| Institution: | Wang Jian,Eriqitai(School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | A scheme of injection at the divergent section is put forward to solve the starting problem in the divergent dual throat nozzle.The effects of the injection flow at the divergent section and the injection location on the flow and the performance of the nozzle are studied by two-dimensional divergent numerical simulation.Results indicate that oblique shock series and large separation areas can be made by the injection at the divergent section and change the flow channel shape of the divergent dual throat nozzle,so that the shock losses are reduced,the nozzle starting problem is solved,and the dual throat nozzle performance is remarkably improved.When the injection slot is in the middle of the divergent section,the continuous divergent channel is easily formed,it is helpful to accelerate the main stream and to generate the thrust,and the best thrust performance can be obtained on this condition. |
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| Keywords: | thrust-vectoring nozzle dual throat nozzle injection at divergent section fluidic control |
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