关键参数对固冲发动机二次燃烧性能影响规律及优化
发布时间：2019-05-23 05:03
【摘要】：系统梳理了影响固体火箭冲压发动机二次燃烧性能的关键参数,通过数值仿真研究了各因素对二元双下侧进气道布局固冲发动机二次燃烧性能的耦合影响规律,在此基础上,完成了高性能固体火箭冲压发动机地面试验样机设计和验证。研究结果表明,采用轴向一次进气方案时,进气角度在45°~60°、头部距离在0.5D~0.75D时,二次燃烧效率较高,设计点余气系数2.0时,在该范围内应尽可能选用大的进气角度和头部距离;设计点余气系数2.0时,应优先选用轴向两次进气的结构形式,二次进气的间距在0.5D附近、二次进气角度在45°~60°时,可达到较高的燃烧效率;经优化设计,空燃比14~20范围内变化时,发动机的燃烧效率达到0.924以上。
[Abstract]:The key parameters affecting the secondary combustion performance of solid rocket ramjet are systematically combed, and the coupling law of each factor on the secondary combustion performance of binary double lower inlet layout solid impact engine is studied by numerical simulation. The ground test prototype of high performance solid rocket ramjet is designed and verified. The results show that when the axial primary intake scheme is used, the intake angle is 45 掳~ 60 掳and the head distance is 0.5D~0.75D, the secondary combustion efficiency is higher and the residual gas coefficient of the design point is 2.0. In this range, a large intake angle and head distance should be selected as much as possible. When the residual gas coefficient of the design point is 2.0, the structure of the axial and secondary intake should be preferred. When the distance between the secondary intake and the angle of the secondary intake is about 0.5D and the angle of the secondary intake is 45 掳~ 60 掳, the combustion efficiency can be achieved. After optimization design, the combustion efficiency of the engine is more than 0.924 when the air-fuel ratio varies within the range of 14 鈮，
本文编号：2483627
[Abstract]:The key parameters affecting the secondary combustion performance of solid rocket ramjet are systematically combed, and the coupling law of each factor on the secondary combustion performance of binary double lower inlet layout solid impact engine is studied by numerical simulation. The ground test prototype of high performance solid rocket ramjet is designed and verified. The results show that when the axial primary intake scheme is used, the intake angle is 45 掳~ 60 掳and the head distance is 0.5D~0.75D, the secondary combustion efficiency is higher and the residual gas coefficient of the design point is 2.0. In this range, a large intake angle and head distance should be selected as much as possible. When the residual gas coefficient of the design point is 2.0, the structure of the axial and secondary intake should be preferred. When the distance between the secondary intake and the angle of the secondary intake is about 0.5D and the angle of the secondary intake is 45 掳~ 60 掳, the combustion efficiency can be achieved. After optimization design, the combustion efficiency of the engine is more than 0.924 when the air-fuel ratio varies within the range of 14 鈮，
本文编号：2483627
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