氢燃料超燃冲压发动机燃烧流场结构和性能

黄刚; 李朗; 田野; 张伟

doi:10.13224/j.cnki.jasp.20210725

氢燃料超燃冲压发动机燃烧流场结构和性能

doi: 10.13224/j.cnki.jasp.20210725

黄刚^1,,
李朗^1,*, ,,
田野²,
张伟¹

1.
西南科技大学土木工程与建筑学院，四川绵阳 621010
2.
中国空气动力研究与发展中心空天技术研究所，四川绵阳 621321

基金项目: 国家自然科学基金（11902278）

详细信息

作者简介:
黄刚（1997-），男，硕士生，研究领域为空气动力学。E-mail：468457877@qq.com

通讯作者:
李朗（1979-），女，副教授，博士，研究领域为空气动力学。E-mail：lilang0211@swust.edu.cn

中图分类号: V233.1
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- 被引次数: 0
出版历程
- 收稿日期: 2021-12-24
- 网络出版日期: 2023-02-09

Combustion flow field structure and performance in hydrogen-fueled scramjet

HUANG Gang^1
,,
LI Lang^{1,*
, ,},
TIAN Ye²,
ZHANG Wei¹

1.
School of Civil Engineering and Architecture， Southwest University of Science and Technology，Mianyang Sichuan 621010，China
2.
Aerospace Technology Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621321，China

摘要

摘要:
基于氢燃料单凹腔矩形截面超燃冲压发动机，在发动机入口马赫数为2的条件下，采用RANS（Reynolds-averaged Navier Stokes）方法求解包含10组分21步化学反应机理模型，并结合有限速率燃烧模型进行了数值模拟研究，并与试验数据进行对比。分析了无化学反应和化学反应流动条件下的燃烧室流场结构，研究了不同当量比对燃烧室燃烧性能的影响，考察了不同喷注位喷注氢气时的流场燃烧特性。结果表明：当量比的提高会使燃烧产物分布扩大并后移，发动机燃烧模态由超燃转为亚燃，发动机总压损失上升，燃烧效率降低，推力增加。在当量比为0.1～0.3时，在凹腔前端喷注燃料的发动机燃烧性能优于凹腔内喷注，当量比为0.4～0.5则相反。
- 超燃冲压发动机 /
- 氢气 /
- 燃烧效率 /
- 当量比 /
- 总压损失
Abstract:
Based on the hydrogen-fueled single cavity rectangular cross-section scramjet, under the inflow condition of Mach number 2, the RANS （Reynolds-averaged Navier Stokes） method was used to solve the chemical mechanism model (10 species and 21 reactions), while the finite-rate combustion model was used to finish numerical simulation, and compared with the experimental data. The flow field structure of the combustor under nonreacting and reacting flow conditions was analyzed, then the effects of different equivalence ratios on the combustion performance of the combustor were discussed, and the combustion flow field characteristics of hydrogen injection at different injection positions were investigated. Results demonstrated that the distribution of combustion products was expanded and also moved back with the increase of equivalence ratio, changed the engine combustion mode from supersonic combustion to subsonic combustion, increased the total pressure loss, decreased the combustion efficiency and augment the thrust. At 0.1 to 0.3 equivalent ratios, the scramjet combustion performance of fuel injected at the front of the cavity was better than that injected in the cavity, which was contrary to 0.4 to 0.5 equivalent ratios.
- scramjet /
- hydrogen /
- combustion efficiency /
- equivalence ratio /
- total pressure loss

HTML

图 1 超燃冲压发动机示意图

Figure 1. Schematic illustration of the scramjet

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图 2 超燃冲压发动机模型

Figure 2. Scramjet combustor model

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图 3 试验与仿真结果对比

Figure 3. Comparison of experiment and simulation results

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图 4 测点压力分布图

Figure 4. Distributions of wall pressure at measuring point

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图 5 测点壁面切应力分布图

Figure 5. Distributions of wall shear stress at measuring point

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图 6 数值计算及试验壁面压力分布图

Figure 6. Distributions of numerical and experimental wall pressures

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图 7 凹腔内燃烧流动参数对比

Figure 7. Comparison of combustion flow characteristics in cavity

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图 8 J1喷口下不同当量比马赫数分布云图

Figure 8. Contour of Mach number distribution at different equivalent ratios with injector J1

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图 9 J1喷口下不同当量比水质量分数分布云图

Figure 9. Contour of mass fraction distribution of water at different equivalent ratios with injector J1

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图 10 J1喷口下不同当量比壁面马赫数分布

Figure 10. Wall Mach number distribution at different equivalent ratios with injector J1

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图 11 J2喷口下不同当量比马赫数分布云图

Figure 11. Mach number distribution at different equivalent ratios with injector J2

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图 12 J2喷口下不同当量比水的质量分数分布云图

Figure 12. Mass fraction distribution of water at different equivalent ratios with injector J2

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图 13 J2喷口下不同当量比壁面压力分布

Figure 13. Wall pressure distribution at different equivalent ratios with injector J2

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图 14 J2喷口下不同当量比壁面马赫数分布

Figure 14. Wall Mach number distribution at different equivalent ratios with injector J2

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图 15 总压损失比较

Figure 15. Comparison of total pressure loss

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图 16 燃烧效率对比

Figure 16. Comparison of combustion efficiency

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图 17 发动机推力对比

Figure 17. Comparison of engine thrust

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表 1 无化学反应流动数值计算结果与试验值比较

Table 1. Comparison between experimental values and numerical simulation

参数	试验值	计算值	相对误差/%
监测点1壁面压力/MPa	0.103	0.109	5.83
监测点2壁面压力/MPa	0.101	0.103	1.98
监测点1壁面切应力/Pa	825	770	−6.67
监测点2壁面切应力/Pa	401	382	−4.74

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表 2 出口处燃烧效率

Table 2. Combustion efficiency of outlet

φ	J1	J2
0.1	0.888	0.899
0.2	0.689	0.844
0.3	0.784	0.791
0.4	0.721	0.715
0.5	0.626	0.605

下载: 导出CSV

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