固体火箭超燃冲压发动机燃气喷射燃烧数值仿真研究

陈永志; 石保禄; 赵马杰; 李鹏昌; 冯滢

doi:10.13224/j.cnki.jasp.20220944

固体火箭超燃冲压发动机燃气喷射燃烧数值仿真研究

doi: 10.13224/j.cnki.jasp.20220944

北京理工大学宇航学院，北京 100081

详细信息

作者简介:
陈永志（1998-），男，硕士生，主要从事固体火箭超燃冲压发动机流动燃烧数值模拟研究

通讯作者:
赵马杰（1990-），男，教授、博士生导师，博士，主要从事超声速燃烧、湍流燃烧数值模拟研究。E-mail：zhaomj@bit.edu.cn

中图分类号: V235.21
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出版历程
- 收稿日期: 2022-12-09
- 网络出版日期: 2024-03-12

Numerical research on gas injection combustion of solid rocket scramjet

School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

摘要

摘要:
针对固体火箭超燃冲压发动机燃烧室内燃料滞留时间短、与空气来流掺混困难，火焰稳定性差，颗粒燃烧效率低等问题。基于欧拉-拉格朗日方法建立了两相流动燃烧数值模拟方法，利用最小自由能法及能量、质量守恒定律进行一次燃气简化。基于某型带凹腔火焰稳定装置的固体火箭超燃冲压发动机模型，探究了不同燃气喷射角度、不同燃气喷射位置对发动机温升效率、总压恢复系数、凹腔性能、颗粒燃烧效率等参数的影响。结果表明该数值模拟方法具有较高的计算精度。研究发现增大燃气喷射角度可以提升燃料穿透深度，增加颗粒燃烧效率，但会造成总压损失升高；改变燃气喷射位置发现影响颗粒燃烧效率的原因不仅有颗粒的滞留时间，还包括颗粒所在区域的温度分布。
- 固体火箭超燃冲压发动机 /
- 气固两相流动燃烧 /
- 一次燃气 /
- 超声速流动 /
- 燃烧组织方案
Abstract:
Considering some problems in the combustion chamber of solid rocket ramjet, such as short fuel residence time, difficult mixing with air flow, poor flame stability, and low particle combustion efficiency, based on the Eulerian Lagrange method, a two-phase flow combustion simulation model was established and the primary gas was simplified by using the minimum free energy method and the law of conservation of energy and mass. Based on a solid rocket scramjet model with a cavity flame stabilizer, the influences of different gas injection angles and positions on temperature rise efficiency, total pressure recovery coefficient, cavity performance and particle combustion efficiency were explored. The results showed high calculation accuracy of this method. It was found that increasing the gas injection angle could improve the fuel penetration depth and increase the particle combustion efficiency, but the total pressure loss would increase; the change of gas injection location affected the combustion efficiency of particles not only because of the particle retention time, but also because of the temperature distribution in the region with the particles.
- solid rocket scramjet /
- gas-solid two phase flow combustion /
- primary gas /
- supersonic flow /
- combustion organization

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图 1 固体火箭超燃冲压发动机示意图

Figure 1. Schematic of solid rocket scramjet

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图 2 数值计算域

Figure 2. Simulation domain

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图 3 仿真与试验压力数据对比

Figure 3. Comparison of pressure data between simulation and experiment

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图 4 不同喷射角度燃烧室压力云图

Figure 4. Distributions of pressure in the combustion chamber with different injection angles

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图 5 凹腔马赫数云图

Figure 5. Mach number contours of cavity

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图 6 质量交换率、温升效率、总压恢复系数曲线图

Figure 6. Evolution of mass exchange rate, temperature rise efficiency and total pressure recovery cofficient

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图 7 凹腔入口截面速度云图

Figure 7. Distribution of velocity on the cavity inlet section

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图 8 气相组分燃烧效率

Figure 8. Combustion efficiency of gas phase components

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图 9 不同喷射角度温升效率与颗粒燃烧效率

Figure 9. Evolution of temperature rise efficiency and combustion efficiency at different injection angles

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图 10 燃烧室温度与颗粒轨迹云图

Figure 10. Distributions of combustion chamber temperature and particle trajectory

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图 11 燃气喷射位置结构示意图

Figure 11. Schematic of fuel gas injection position

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图 12 不同喷射位置燃烧室马赫数云图

Figure 12. Mach number contours of combustion chamber at different injection positions

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图 13 凹腔马赫数云图

Figure 13. Mach number contours of cavity

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图 14 不同燃气喷射位置温升效率、颗粒燃烧效率

Figure 14. Temperature rise efficiency and particle combustion efficiency at different gas injection positions

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图 15 流场温度与颗粒滞留时间云图

Figure 15. Distributions of temperature and particle residence time

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表 1 碳颗粒反应机理

Table 1. Reaction mechanism of carbon particles

化学反应	A/（kg/（m³·s））	E/10⁸ （J/kg·mol）
2C+O₂→2CO	0.86	1.495
2CO+O₂→2CO₂	2.239×10¹²	1.7

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表 2 气相化学反应机理

Table 2. Gas phase chemical reaction mechanism

化学反应	A/10⁸ （kg/（m³·s））	E/10⁷ （J/kg·mol）
2CO+O₂→2CO₂	22390	17
2H₂+O₂→2H₂O	9.87	3.1

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表 3 发动机试验与数值模拟入口参数

Table 3. Experimental and numerical simulation of inlet parameters of scramjet

参数	试验空气来流	空气入口边界条件	燃气入口边界条件
质量流率/（kg/s）	0.97		0.035
总温/K	1490	1490	1 835
静温/K	786
总压/MPa	1.54	1.54
静压/MPa	0.088	0.088

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表 4 一次燃气参数

Table 4. Parameters of primary gas

燃气总温/K	比定压热容/（J/（kg·K））	比焓/（J/kg）
1 835	2385	−1283588

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表 5 一次燃气组分质量分数

Table 5. Mass fraction of primary gas

组分	CO	H₂	B	C	G
质量分数/%	10.3	5.3	32	29.2	23.2

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表 6 二次燃气参数

Table 6. Parameters of secondary gas

燃气总温/K	比定压热容/ （J/（kg·K））	比焓/ （J/kg）	摩尔质量/ （g/mol）
2536	2250.7	1153740	29.8

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表 7 不可燃气体G比热多项式系数

Table 7. Polynomial coefficient of specific heat of incombustible gas G

G比热容多项式	α₀	α₁	α₂
α₀+α₁T_G+α₂$T_{\mathrm{G}}^2 $	−555438	433.37	−0.0712
注：表中T_G表示不可燃气体G的温度。

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表 8 仿真与试验数据对比

Table 8. Comparison of simulation and experimental data

参数	试验	仿真
燃烧室出口温度/K	1 940	1 920
燃烧室出口马赫数	1.48	1.50
温升效率/%	48	46

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表 9 不同燃气喷射位置颗粒最长滞留时间

Table 9. Maximum residence time of particles at different injection positions

喷射位置	台阶前壁面	台阶平面	凹腔前壁面
颗粒最长滞留时间/ms	0.764	1.6	0.75

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