火箭推进

为了探究煤油燃料火箭基组合循环(RBCC)发动机燃烧室在冲压模态下的燃烧特性,构建了一套仿真计算方法用于预测、分析燃烧室内流动及燃烧过程。以带支板喷注器、单凹腔火焰稳定器RBCC燃烧室为例,开展了冲压模态下的内流场三维数值模拟,计算得到的壁面压力曲线与地面试验及飞行试验结果符合良好。分析燃烧室压力、马赫数、燃气组分等参数可以发现:当前燃烧室结构能够实现冲压模态下液体煤油燃料的稳定、高效燃烧; 与冷流相比,压升可达5倍以上; 支板能够有效提高煤油燃料的掺混能力; 火箭安装台阶下游存在利于燃烧和火焰稳定的回流区; 通过调整凹腔、支板等喷注器供油规律,可提高来流氧气的利用率,实现更为充分的燃烧。

In order to explore the combustion characteristics of a rocket based combined cycle(RBCC)engine with kerosene in ramjet mode,a numerical simulation method was proposed to predict and analyze the flow and combustion process in the combustion chamber. The 3D internal flow field of a RBCC combustor with strut injectors and a cavity flame holder in ramjet mode were simulated numerically. The calculated wall pressure curve is in good agreement with the results obtained by ground tests and a flight test,indicating that the calculation model is reasonable and practicable. By analyzing the combustor pressure,Mach number,gas composition and other parameters,it can be found that the current combustion chamber structure can realize the stable and efficient combustion of liquid kerosene fuel in ramjet mode. Compared with the cold flow,the pressure rise can reach more than 5 times. The struts can effectively improve the mixing performance of kerosene fuel and air. There is a reflux zone at the downstream of the step for mounting rocket,which is conducive to combustion and flame stability. By adjusting the fuel supply law of injectors such as the cavity and the struts,the utilization rate of inlet oxygen can be improved and more sufficient combustion can be achieved.

引言
1 物理模型
2 数值方法
3 计算结果分析
4 试验验证情况
5 结论

图1 RBCC燃烧室结构示意图<br/>Fig.1 Schematic graph of RBCC combustion chamber

图1 RBCC燃烧室结构示意图
Fig.1 Schematic graph of RBCC combustion chamber

表1 模拟工况参数和燃油分配<br/>Tab.1 Parameters and fuel injection of simulated case

表1 模拟工况参数和燃油分配
Tab.1 Parameters and fuel injection of simulated case

图2 冷流流场马赫数云图及流线<br/>Fig.2 Mach number cloud diagram and streamline of cold flow field

图2 冷流流场马赫数云图及流线
Fig.2 Mach number cloud diagram and streamline of cold flow field

图3 冷流流场压力云图<br/>Fig.3 Static pressure cloud diagram of cold flow field

图3 冷流流场压力云图
Fig.3 Static pressure cloud diagram of cold flow field

图4 化学反应流场静温云图<br/>Fig.4 Static temperature cloud diagram of chemical reaction flow field

图4 化学反应流场静温云图
Fig.4 Static temperature cloud diagram of chemical reaction flow field

图5 化学反应流场马赫数云图<br/>Fig.5 Distribution of Mach number in the chemical reaction flow field

图5 化学反应流场马赫数云图
Fig.5 Distribution of Mach number in the chemical reaction flow field

图6 化学反应流场静压分布<br/>Fig.6 Distribution of static pressure in the chemical reaction flow field

图6 化学反应流场静压分布
Fig.6 Distribution of static pressure in the chemical reaction flow field

$图7 化学反应流场CO2质量分数云图<br/>Fig.7 Mass fraction of CO2 in the chemical reaction flow field$

图7 化学反应流场CO2质量分数云图
Fig.7 Mass fraction of CO2 in the chemical reaction flow field

$图8 化学反应流场H2O质量分数云图<br/>Fig.8 Mass fraction of H2O in the chemical reaction flow field$

图8 化学反应流场H2O质量分数云图
Fig.8 Mass fraction of H2O in the chemical reaction flow field

$图9 化学反应流场O2质量百分数云图<br/>Fig.9 Mass fraction of O2 in the chemical reaction flow field$

图9 化学反应流场O2质量百分数云图
Fig.9 Mass fraction of O2 in the chemical reaction flow field

$图10 化学反应流场煤油质量百分数云图<br/>Fig.10 Mass fraction of kerosene in the chemical reaction flow field$

图10 化学反应流场煤油质量百分数云图
Fig.10 Mass fraction of kerosene in the chemical reaction flow field

图11 燃烧室壁面静压仿真与试验结果对比<br/>Fig.11 Comparison between simulation and test results of static pressure on the combustion chamber wall

图11 燃烧室壁面静压仿真与试验结果对比
Fig.11 Comparison between simulation and test results of static pressure on the combustion chamber wall

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备注

引言

1 物理模型

2 数值方法

3 计算结果分析

4 试验验证情况

5 结论

期刊信息