燃烧室双旁侧二次进气固体燃料冲压发动机燃烧特性

doi:10.12382/bgxb.2023.0905

摘要/Abstract

摘要：

针对固体燃料冲压发动机中因扩散燃烧带来的燃速与燃烧效率偏低问题,提出一种燃烧室双旁侧二次进气固体燃料冲压发动机方案,以提高固体燃料冲压发动机燃烧性能。基于标准k-ε湍流模型和涡耗散方程建立冲压发动机燃烧模型,并对冲压发动机基本模型(无旁侧进气)与双旁侧二次进气冲压发动机模型的内流场、燃面退移速率、燃烧效率等展开仿真计算,同时研究了旁路比对双旁侧二次进气冲压发动机性能的影响。仿真结果表明:燃烧室双旁侧二次进气冲压发动机内流场将出现二次回流区、旋流区等新的流场特征,在一定程度上有助于增强发动机掺混燃烧;燃烧效率和比冲随旁路比的增加呈现先增加、后降低趋势,并在旁路比为60%时二者最高,相较冲压发动机基本模型燃烧效率提升了将近40%、比冲提高了12.09%;推力随旁路比增加整体呈现增加趋势,在旁路比为60%时增量最大,之后推力增益效果随着旁路比的增加逐渐减小。

关键词: 固体燃料冲压发动机, 二次进气, 燃面退移速率, 燃烧效率, 推力, 比冲

Abstract:

In response to the low combustion rate and efficiency caused by diffusion combustion in solid fuel ramjet, a solution involving a solid fuel ramjet withdual-side secondary air intake is proposed to improve combustion performance. A combustion model for the ramjet is established based on Standard k-ε turbulence model and vortex dissipation equations. Simulation calculations are conducted to analyze the internal flow field, burning surface recession rate, and combustion efficiency for both the basic ramjet model (without side air intakes) and the dual-side secondary air intake ramjet model. And the influence of bypass ratio on the performance of dual-side secondary air intake ramjet is investigated. The results indicate that the internal flow field of dual-side secondary air intake ramjet exhibits new flow field characteristics such as secondary recirculation zone and swirling zone, which contribute to enhanced mixing and combustion. Combustion efficiency and specific impulse (I_sp) increase first and then decrease with the increase in bypass ratio, reaching their highest values when the bypass ratio achieves 60%. Compared to the basic ramjet model, the combustion efficiency of dual-side secondary air intake ramjet is increased by nearly 40%, and its specific impulse is increased by 12.09% at a bypass ratio of 60%. Overall, the thrust increases with the increase in bypass ratio, with the maximum thrust being observed at a bypass ratio of 60%. However, the thrust increment diminishes gradually as the bypass ratio continues to increase.

Key words: solid fuel ramjet, secondary air intake, recession rate, combustion efficiency, thrust, specific impulse

中图分类号:

V235.21

常亚, 武志文, 王锐, 高琨鹏, 章喆, 王宁飞. 燃烧室双旁侧二次进气固体燃料冲压发动机燃烧特性[J]. 兵工学报, 2024, 45(12): 4451-4461.

CHANG Ya, WU Zhiwen, WANG Rui, GAO Kunpeng, ZHANG Zhe, WANG Ningfei. Combustion Characteristics of a Solid Fuel Ramjet with Secondary Air Intake in Combustion Chamber[J]. Acta Armamentarii, 2024, 45(12): 4451-4461.

图/表 17

表1 试验与数值计算结果对比

Table 1 Comparison of experimental and numerical results

工况	入口内径/mm	装药长度/mm	空气流量/(kg·s^-1)	空气总温/K	压强/MPa	燃速/(mm·s^-1)
工况	入口内径/mm	装药长度/mm	空气流量/(kg·s^-1)	空气总温/K	压强/MPa	试验值	计算值
1	23.4	202	0.293	624	0.807	0.574	0.576
2	23.4	202	0.308	615	0.848	0.597	0.598

图1 物理模型

Fig.1 Physical Model

表2 流场计算边界条件

Table 2 Boundary conditions for flow field calculation

SFRJ模型	质量流量/(kg·s^-1)		总温/K
SFRJ模型	主路	旁路	总温/K
SFRJ基本模型	1		692
燃烧室双旁侧二次进气SFRJ模型	0.7	0.15	692

图2 网格模型

Fig.2 Grid Model

图3 网格无关性验证

Fig.3 Grid independence verification

图4 内流场分析截面

Fig.4 Analytical section of flow field

图5 温度云图

Fig.5 Temperature contour

图6 沿轴向截面温度分布

Fig.6 Temperature distribution along the axial section

图7 压力云图

Fig.7 Pressure Contour

图8 燃烧室上游流线分布

Fig.8 Upstream streamline distribution of combustion chamber

图9 燃烧室下游流线分布

Fig.9 Downstream streamline distribution in combustion chamber

图10 补燃室流线分布

Fig.10 Streamline distribution in afterburning chamber

图11 燃速分析特征线

Fig.11 Analysis characteristic line of burning rate

图12 不同旁路比燃速变化

Fig.12 Burning rates at different bypass ratios

表3 平均燃速变化

Table 3 Variation of average burning rate

旁路比/%	平均燃速/(mm·s^-1)	增长率/%
0	0.784
10	0.830	5.97
20	0.842	1.46
30	0.855	1.48
40	0.859	0.46
50	0.826	-3.82
60	1.038	25.62
70	1.189	14.60
80	1.390	16.87
90	1.703	22.57

图13 不同旁路比下燃烧效率

Fig.13 Combustion efficiencies at different bypass ratios

图14 不同旁路比下推力、比冲变化

Fig.14 Thrust and specific impulse curves at different bypass ratios

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