旋转爆震加力燃烧室进气含氧量下限及性能分析研究

周虹羽; 王星贵; 钱志豪; 李华东; 彭瀚; 黄玥; 尤延铖

doi:10.13224/j.cnki.jasp.20250591

旋转爆震加力燃烧室进气含氧量下限及性能分析研究

doi: 10.13224/j.cnki.jasp.20250591

周虹羽^{1, 2,},
王星贵²,
钱志豪^{1, 2},
李华东²,
彭瀚^1,*, ,,
黄玥¹,
尤延铖¹

1.
厦门大学航空航天学院，福建厦门 361102
2.
中国航发四川燃气涡轮研究院，成都 610500

基金项目: 国家自然科学基金（52376128，52406157）；厦门市自然科学基金（3502Z202471003）；中央高校基本科研业务费（20720240079）

详细信息

作者简介:
周虹羽（2003-），女，硕士生，研究方向为旋转爆震发动机。E-mail：hongy_zhou@163.com

通讯作者:
彭瀚（1994-），男，助理教授，博士，研究方向为爆震燃烧、旋转爆震发动机等。E-mail：han.peng@xmu.edu.cn

中图分类号: V239
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出版历程
- 收稿日期: 2025-12-18
- 网络出版日期: 2026-03-25

Study on the lower limit of oxygen concentration at inlets and performance analysis of rotating detonation afterburner

ZHOU Hongyu^{1, 2
,},
WANG Xinggui²,
QIAN Zhihao^{1, 2},
LI Donghua²,
PENG Han^{1,*
, ,},
HUANG Yue¹,
YOU Yancheng¹

1.
School of Aerospace Engineering，Xiamen University，Xiamen Fujian 361102，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
实现低含氧量进气条件下旋转爆震的稳定自持是旋转爆震加力燃烧室设计的关键。通过乙烯/空气非预混旋转爆震流场二维数值模拟，研究贫燃条件下进气温度对旋转爆震起爆临界进气含氧量下限的影响。结果表明，随着加力燃烧室进气温度从875 K增至1025 K，旋转爆震稳定传播进气氧气质量分数下限从15%变为14%。在进气含氧量降至接近起爆临界下限时，进气温度升高对燃烧室流场平均释热率影响较小，但高温进气可通过增强流场中的缓燃，实现爆震波在速度亏损超过8%下的自持传播，从而拓宽稳定起爆的边界。此外，进气温度升高还会诱导流场出现复杂多波模态，而进气含氧量降低则促使旋转爆震趋于单波模态传播。进一步分析表明，旋转爆震多波模态显著影响加力燃烧室总压损失和比推力，混合模态则主导燃烧室温升比和燃烧效率变化。进气温度升高会使旋转爆震加力燃烧室各项性能参数降低，但在适当的进气温度和含氧量下，旋转爆震加力燃烧可使燃烧室总压损失减小。
- 旋转爆震 /
- 加力燃烧室 /
- 进气含氧量 /
- 进气温度 /
- 传播特性 /
- 总压损失
Abstract:
Achieving stable and self-sustained rotating detonation under low-oxygen intake conditions is crucial for the design of rotating detonation afterburners. Through two-dimensional numerical simulations of non-premixed ethylene/air rotating detonation flow fields, this study investigated the influence of intake temperature on the critical lower limit of oxygen concentration required for rotating detonation initiation under fuel-lean conditions. The results showed that as the intake temperature of the afterburner increased from 875 K to 1025 K, the lower limit of oxygen mass fraction for stable propagation of the rotating detonation shifted from 15% to 14%. When the oxygen concentration approached the critical lower limit for initiation, increasing the intake temperature had a minor effect on the average heat release rate in the combustor flow field. However, higher intake temperatures can enhanced deflagration within the flow field, enabling self-sustained propagation of the detonation wave even when the velocity deficit exceeded 8%, thereby broadening the stable initiation boundary. Furthermore, increased intake temperature induced the emergence of complex multi-wave modes in the flow field, while reduced oxygen concentration tended to drive the rotating detonation toward propagation in a single-wave mode. Further analysis indicated that multi-wave modes significantly affected the total pressure loss and specific thrust of the afterburner, while mixed modes dominated variations in the temperature rise ratio and combustion efficiency. Increasing the intake temperature generally degrades the performance parameters of the rotating detonation afterburner; nevertheless, under appropriate intake temperature and oxygen concentration conditions, rotating detonation after burning can achieve lower total pressure loss.
- rotating detonation /
- afterburner /
- intake oxygen concentration /
- intake temperature /
- propagation characteristics /
- total pressure loss

HTML

图 1 计算域与边界条件

Figure 1. Computational domain and boundary conditions

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图 2 三种分辨率网格沿X轴压力分布

Figure 2. Pressure along the X-axis at three mesh scales

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图 3 典型爆震流场温度压力云图

Figure 3. Temperature and pressure contour of detonation in typical flow field

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图 4 稳定起爆进气含氧量下限阈值

Figure 4. Lower limit of oxygen concentration in the air for stable detonation initiation

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图 5 旋转爆震波起爆情况

Figure 5. Initiation conditions of rotating detonation waves

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图 6 流场平均释热率分布

Figure 6. Average of HRR in flow field

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图 7 流场中的缓燃

Figure 7. Deflagration in flow field

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图 8 临界工况温度、释热率云图

Figure 8. Temperature and HRR contour of critical cases

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图 9 各工况波速与速度亏损变化规律

Figure 9. Variation of wave velocity and velocity loss for cases

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图 10 对撞模态流场分布

Figure 10. Flow field in collision mode

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图 11 混合模态时序变化

Figure 11. Temporal variation of temperature nephograms

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图 12 不同进气温度和含氧量下的总压损失

Figure 12. Pressure loss ratio under different inflow temperatures and oxygen volume fractions

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图 13 不同进气温度和含氧量下的比推力

Figure 13. Specific thrust under different inflow temperatures and oxygen volume fractions

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图 14 不同进气温度和含氧量下的温升比

Figure 14. Temperature-rise ratio under different inflow temperatures and oxygen volume fractions

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图 15 不同温度和含氧量下的燃烧效率

Figure 15. Combustion efficiency under different inflow temperatures and oxygen volume fractions

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表 1 计算条件

Table 1. Calculated operating conditions

参数变化范围变化量

ER 0.8
$ T_{\text {inlet}} $/K 875～1025 75
w（O₂）_inlet/% 23～17、17～10 2、1

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