低温进气对点火过程影响的大涡模拟

王辉; 刘永丰; 胡传龙; 石云姣; 刘潇

doi:10.13224/j.cnki.jasp.20250077

低温进气对点火过程影响的大涡模拟

doi: 10.13224/j.cnki.jasp.20250077

王辉^{1, 2,},
刘永丰^{1, 2},
胡传龙³,
石云姣³,
刘潇^3,*, ,

1.
中国兵器工业集团有限公司中国北方发动机研究所，天津 300405
2.
中国兵器工业集团有限公司中国北方发动机研究所车用动力系统全国重点实验室，天津 300405
3.
哈尔滨工程大学动力与能源工程学院，哈尔滨 150001

基金项目: 基础性科研院所稳定支持项目（WDZC-2023-HJSY-02）

详细信息

作者简介:
王辉（1995-），男，硕士，主要研究方向为燃烧动力学

通讯作者:
刘潇（1988-），男，副教授、博士生导师，博士，主要从事燃气轮机燃烧理论与技术研究。E-mail：liuxiao_heu@163.com

中图分类号: V231.2
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- 被引次数: 0
出版历程
- 收稿日期: 2025-02-15
- 网络出版日期: 2025-08-19

Large eddy simulation on the impact of low-temperature inlet on the ignition process

WANG Hui^{1, 2
,},
LIU Yongfeng^{1, 2},
HU Chuanlong³,
SHI Yunjiao³,
LIU Xiao^{3,*
, ,}

1.
China North Engine Research Institute，China North Industries Group Corporation Limited，Tianjin 300405，China
2.
National Key Laboratory of Vehicle Power System，China North Engine Research Institute，China North Industries Group Corporation Limited，Tianjin 300405，China
3.
College of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China

摘要

摘要:
燃气轮机燃烧室在低温环境下的可靠运行，其关键在于确保贫油燃烧的点火可靠性。为了提高点火性能，研究关键因素对点火过程的影响是非常重要的。基于多旋流模型燃烧室，研究了低温入口和油气比对初始火焰核和火焰传播行为的影响。使用大涡模拟和动态增厚火焰燃烧模型，结合煤油的骨架化学反应机理，捕捉点火过程中的火焰面信息。结果表明数值方法可以准确地模拟点火过程。随着入口空气温度的降低，点火位置的轴向速度、液滴温度和局部当量比降低；而局部当量比随着油气比的增加而增加。当入口空气温度降低到253 K时点火失败，原因是局部当量比低。通过将油气比提高到0.04，可以成功实现低温进口条件的点火，但点火延迟时间延长了26.72%，火焰传播路径也发生了改变。
- 燃气轮机燃烧室 /
- 喷雾燃烧 /
- 大涡模拟 /
- 点火过程 /
- 动态增厚火焰 /
- 低温点火
Abstract:
The ignition reliability of lean combustion is fundamental to make sure that gas turbine combustor can operate in low-temperature environment reliably. It is important to investigate the influence of key factors on ignition process to improve ignition performance. Based on the multi-swirl staged model combustor, the effects of low-temperature inlet and fuel to air ratio on the behaviors of the initial flame kernel and flame propagation were analyzed. In this work, large eddy simulation and dynamic thickened flame model coupled with skeletal chemical reaction mechanism of kerosene were used to capture flamelet information during the ignition process. The results showed that the numerical method can capture the ignition process accurately. The axial velocity, droplet temperature and local equivalence ratio of the ignition position decreased as the inlet air temperature decreased, while the local equivalence ratio increased with the increase of fuel to air ratio. Ignition failed when inlet air temperature reduced to 253 K, as local equivalence ratio of the ignition position decreased. The ignition with low-temperature inlet air can be realized successfully by raising the fuel to air ratio to 0.04 at the same time, but the ignition delay time was extended by 26.72% and the flame propagation path was changed.
- gas turbine combustor /
- spray combustion /
- large eddy simulation /
- ignition process /
- dynamic thickened flame model /
- low-temperature ignition

HTML

图 1 多旋流模型燃烧室结构示意图

Figure 1. Schematic of the multi-swirl staged model combustor

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图 2 网格自适应示意图

Figure 2. Schematic of adaptive mesh refinement

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图 3 火焰形态的实验结果和模拟结果对比

Figure 3. Comparison of experimental results and simulation results of flame morphology

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图 4 不同工况冷态场对比

Figure 4. Comparison of cold flow field under different cases

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图 5 点火位置沿Y轴的轴向速度对比

Figure 5. Comparison of axial velocity of ignition position along Y axis

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图 6 点火区域的液滴平均温度和局部当量比

Figure 6. Average droplet temperature and local equivalence ratio in ignition region

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图 7 工况1的点火过程

Figure 7. Ignition process of case 1

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图 8 工况2的点火过程

Figure 8. Ignition process of case 2

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图 9 工况3的点火过程

Figure 9. Ignition process of case 3

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图 10 工况1和工况3的温度云图和流线的叠加图

Figure 10. Overlay of temperature contours and streamlines for case 1 and case 3

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图 11 轴向速度云图和液滴温度散点图的叠加图

Figure 11. Overlay of the axial velocity contour and droplet temperature scatterplot

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图 12 OH最大质量分数随时间的增长率曲线

Figure 12. Growth rate of OH maximum mass fraction over time

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图 13 不同工况初始火核火焰体积的比较

Figure 13. Comparison of initial flame volume under different cases

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图 14 点火过程中不同工况火焰面积和火焰体积曲线

Figure 14. Flame area and flame volume curves under different cases during ignition process

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表 1 边界条件

Table 1. Boundary condition

工况空气流量/（g/s）空气温度/K 油气比燃油温度/K

文献[19] 143 286 0.03 287

工况1 143 286 0.03 287

工况2 143 253 0.03 287

工况3 143 253 0.04 287

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