火箭推进

为研究SMC模式下火箭混合比对RBCC发动机性能的影响规律,完成了氢/氧火箭推力室中心布局、二元定几何结构模型发动机Ma0=4/H=17 km弹道点流场仿真,获得了不同火箭混合比(MR=2、3、4、5、6、8)及燃烧室长度的推力、比冲性能。研究表明:1)在火箭燃气富燃条件下(MR<8),产生了正的火箭推力增益,且随着混合比的减小,火箭推力增益增加; 2)二次燃烧过程受火箭射流与冲压主流剪切层掺混主导,在本文给定的基准燃烧室长度下,燃烧效率随着混合比的提高而增加,且火箭射流与冲压主流的超/超射流剪切层燃烧过程一直持续到喷管出口; 3)通过增加燃烧室长度,火箭富燃燃气获得更为充分的燃烧,发动机性能显著提升,但在具体发动机设计中,燃烧室长度的选取需在燃烧效率与结构惩罚之间进行权衡。

In order to obtain the influence of rocket mixing ratio on RBCC engine performance under SMC mode, the flow field simulation of Ma0=4/H=17 km was conducted for the engine with the center layout of H2/O2 rocket trust chamber and two-dimension fixed structure.. The engine thrust and specific impulse of different rocket mixing ratio(MR=2、3、4、5、6、8)and combustor length were analyzed also. The studies indicates that: 1)Positive rocket thrust augmentation is obtained when the rocket operating under rich-fuel state(MR<8), and rocket thrust augmentation reduces with the rocket mixing ratio increasing; 2)The secondary combustion process is dominated by the shear layer mixing effect between the supersonic rocket gas jet and the supersonic air flow captured by ramjet combustor. Under the given reference combustor length in this paper, the combustion efficiency increases with the improvement of mixing ratio, and the supersonic/supersonic jet shear layer combustion process lasts until the nozzle outlet; 3)Engine thrust and specific impulse can be significantly enhanced by increasing the combustor length so that the rocket fuel-rich gas can be fully burned. However, in the specific engine design, the selection of the combustor length should be balanced between the combustion efficiency and the engine structure penalty.

引言
1 数值方法
2 计算结果及分析
3 结论

图1 计算模型示意图<br/>Fig.1 Sketch of computational model

图1 计算模型示意图
Fig.1 Sketch of computational model

表1 计算工况及边界条件<br/>Tab.1 Calculating cases and boundary conditions

表1 计算工况及边界条件
Tab.1 Calculating cases and boundary conditions

图2 MR=2流场云图<br/>Fig.2 Flow filed contour with MR=2

图2 MR=2流场云图
Fig.2 Flow filed contour with MR=2

图3 不同轴向截面温度分布<br/>Fig.3 Temperature distribution in different axial sections

图3 不同轴向截面温度分布
Fig.3 Temperature distribution in different axial sections

图4 不同轴向截面轴向速度分布<br/>Fig.4 Velocity distribution in different axial section

图4 不同轴向截面轴向速度分布
Fig.4 Velocity distribution in different axial section

图5 发动机性能与混合比关系<br/>Fig.5 Relationship between engine performance and MR

图5 发动机性能与混合比关系
Fig.5 Relationship between engine performance and MR

图6 燃烧效率与混合比关系曲线<br/>Fig.6 Relationship between combustion efficiency and MR

图6 燃烧效率与混合比关系曲线
Fig.6 Relationship between combustion efficiency and MR

表2 MR=3不同燃烧室长度燃烧效率及推力增益<br/>Tab.2 Combustionefficiency and thrust augmentation under different combustor lengths at MR=3

表2 MR=3不同燃烧室长度燃烧效率及推力增益
Tab.2 Combustionefficiency and thrust augmentation under different combustor lengths at MR=3

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备注

引言

1 数值方法

2 计算结果及分析

3 结论

期刊信息