喷注结构对超声速气-固两相富燃燃气燃烧增强特性

杨鹏年; 夏智勋; 马立坤; 陈斌斌; 冯运超; 陈兴元

doi:10.13224/j.cnki.jasp.20240755

喷注结构对超声速气-固两相富燃燃气燃烧增强特性

doi: 10.13224/j.cnki.jasp.20240755

国防科技大学先进推进技术实验室，长沙 410073

基金项目: 国家自然科学基金（12272409，U21B2086）；国防科技大学基石基金计划项目（JS2023-07）；湖南省荷尖人才计划（2022RC1233）；湖南省研究生科研创新项目（CX20230058）

详细信息

作者简介:
杨鹏年（1996-），男，博士生，主要研究方向为新型固体推进技术。E-mail：yangpengnian@nudt.edu.cn

通讯作者:
马立坤（1987-），男，副教授，博士，主要研究方向为新型固体推进技术。E-mail：malikun@nudt.edu.cn

中图分类号: V435
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出版历程
- 收稿日期: 2024-11-05
- 网络出版日期: 2025-10-23

Combustion enhancement characteristics of supersonic gas-solid two-phase enriched fuel by injector structure

Advanced Propulsion Laboratory，National University of Defense Technology，Changsha 410073，China

摘要

摘要:
针对超声速气-固两相富燃燃气燃烧增强特性，采用数值模拟方法，对比分析了不同喷口形状（圆形、椭圆形、矩形）和喷口布置（单侧与双侧喷注，不同喷注角度）对富燃燃气掺混燃烧的影响规律。研究发现，喷口形状和布置策略对燃烧增强特性具有显著影响。与矩形喷口相比，圆形和椭圆形喷口更有助于富燃燃气在燃烧室内的燃烧释热。此外，增加喷口数量和调整喷口角度能提高穿透深度并促进展向分布，有效扩大富燃燃气与来流空气的接触面积，从而显著提升气相组分的燃烧速度及碳颗粒的燃烧效率。研究还发现，颗粒燃烧过程高度依赖于高温与富氧环境的协同作用，富燃燃气释热的过度集中可能不利于颗粒的加热和点火。因此，创造并维持一个稳定的高温富氧环境，同时确保颗粒能够顺利进入这一理想燃烧区域，对于提升颗粒燃烧效率、优化整体燃烧性能至关重要。
- 超声速燃烧 /
- 气-固两相 /
- 富燃燃气 /
- 喷注结构 /
- 燃烧增强
Abstract:
Considering the enhanced combustion characteristics of supersonic gas-solid two-phase enriched fuel, numerical simulation methods were employed to compare and analyze the effects of different nozzle shapes (circular, elliptical, rectangular) and nozzle arrangements (single-sided and double-sided injection, different injection angles) on the mixed combustion of enriched fuel. Research found that nozzle shape and arrangement strategy had a significant impact on combustion enhancement characteristics. Compared with rectangular nozzles, circular and elliptical nozzles could be more conducive to the combustion and heat release of enriched fuel in the combustor. In addition, increasing the number of nozzles and adjusting the nozzle angle can improve penetration depth and promote spanwise distribution, effectively expanding the contact area between enriched fuel and incoming air, thereby significantly improving the combustion rate of gas-phase components and the combustion efficiency of carbon particles. It was also found that the combustion process of particles was highly dependent on the synergistic effect of a high-temperature and oxygen-rich environment, and the excessive concentration of heat release from enriched fuel may be detrimental to the heating and ignition of particles. Therefore, creating and maintaining a stable high-temperature, oxygen-rich environment while ensuring particles to smoothly enter this ideal combustion zone is crucial for improving particle combustion efficiency and optimizing overall combustion performance.
- supersonic combustion /
- gas-solid two-phase /
- enriched fuel /
- injector structure /
- combustion enhancement

HTML

图 1 燃烧室壁面压力试验与数值模拟结果对比

Figure 1. Comparison of experiment and simulation results of wall pressure along the scramjet combustor

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图 2 喷口形状示意图

Figure 2. Schematic of nozzle shapes

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图 3 不同喷口形状下的马赫数、总压恢复系数和总温分布

Figure 3. Mach number, total pressure recovery coefficient and total temperature distributions with different nozzle shapes

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图 4 不同喷口形状下富燃燃气的燃烧效率

Figure 4. Combustion efficiency distributions of the enriched fuel with different nozzle shapes

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图 5 不同喷口形状下燃烧室中的温度云图

Figure 5. Temperature contours in combustors with different nozzle shapes

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图 6 不同喷口形状下的颗粒轨迹

Figure 6. Particle trajectory with different nozzle shapes

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图 7 喷口布置示意图

Figure 7. Schematic of fuel-jet arrangements

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图 8 不同喷口布置下的马赫数、总压恢复系数和总温分布

Figure 8. Mach number, total pressure recovery coefficient and total temperature distributions with different fuel-jet arrangements

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图 9 不同喷口布置下富燃燃气的燃烧效率

Figure 9. Combustion efficiency distributions of the enriched fuel with different fuel-jet arrangements

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图 10 不同喷口布置下燃烧室中的温度云图

Figure 10. Temperature contours in combustors with different fuel-jet arrangements

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图 11 不同喷口布置下的颗粒轨迹

Figure 11. Particle trajectory with different fuel-jet arrangements

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表 1 边界条件

Table 1. Boundary conditions

边界位置	边界类型	总压/MPa	静压/MPa	总温/K
来流入口	压力入口	1.08	0.093	1660
燃料喷口	压力入口	1.26	1.010	1 990
出口	压力出口		0.100	300
壁面	无滑移壁面

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表 2 硼基固体推进剂燃烧的简化组分

Table 2. Simplified component of boron-based solid propellant combustion

相态	组分	质量分数/%
气相	CO	39.73
	HCl	12.75
	HBO₂	0.95
	CO₂	0.004
	MgCl₂	29.33
	B₂O₂	3.34
	H₂O	0.04
	N₂	0.813
	H₂	11.62
	B₂O₃	1.42
	BO₂	0.003
凝相颗粒	B	38.7
	C	27.4
	Al₂O₃	33.9

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表 3 不同喷口形状的燃烧室构型

Table 3. Combustion configuration with different nozzle shapes

工况	喷口布置	喷口形状	喷注角度/（°）
Case 1	单侧喷注	圆形	60
Case 2	单侧喷注	椭圆形	60
Case 3	单侧喷注	矩形	60

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表 4 不同喷口布置的燃烧室构型

Table 4. Combustion configuration with different fuel-jet arrangements

工况	喷口布置	喷口形状	喷注角度/（°）
Case 1	单侧喷注	圆形	60
Case 4	双侧喷注	圆形	60
Case 5	双侧喷注	圆形	90

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