外激励作用下分层旋流火焰流场结构与火焰响应特性

宋雷洋; 姚倩; 黄晓锋; 袁丽; 李建中; 邓远灏; 田世泽

doi:10.13224/j.cnki.jasp.20220362

外激励作用下分层旋流火焰流场结构与火焰响应特性

doi: 10.13224/j.cnki.jasp.20220362

宋雷洋^1,,
姚倩^1,*, ,,
黄晓锋²,
袁丽³,
李建中¹,
邓远灏²,
田世泽¹

1.
南京航空航天大学航空发动机热环境与热结构工业和信息化部重点实验室，南京 210016
2.
中国航发四川涡轮研究院，成都 610599
3.
中国人民解放军陆军工程大学国防工程学院，南京 210007

基金项目: 产学研合作项目（HFZL2020CXY005）

详细信息

作者简介:
宋雷洋（1997-），男，博士生，主要从事燃烧不稳定研究

通讯作者:
姚倩（1990-），女，讲师，博士，主要从事高效低排放燃烧研究。E-mail：nuaa_qyao@nuaa.edu.cn

中图分类号: V231.2
计量
- 文章访问数: 70
- HTML浏览量: 22
- PDF量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2022-05-23
- 网络出版日期: 2023-09-25

Flow field and flame response characteristics of stratified swirl flame with external excitation

1.
Key Laboratory of Aero-engine Thermal Environment and Structure， Ministry of Industry and Information Technology， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610599，China
3.
School of National Defense Engineering， the Army Engineering University of the Chinese People’s Liberation Army，Nanjing 210007，China

摘要

摘要:
为了探究贫油直喷（LDI）燃烧室中剪切旋流与火焰的正反馈作用及其诱导燃烧不稳定机理，通过大涡模拟（LES）结合相空间重构、模态分解分析方法研究了外激励作用下分层旋流火焰流场与火焰的动态响应。将流场的试验与LES时均结果进行对比，发现数值计算的速度分布与涡旋结构的大小、位置都和试验结果吻合较好。对LES采集信号与瞬时流场分析表明：燃烧室内压力与释热率脉动处于极限环振荡状态，速度脉动下回流区的收缩与扩张导致燃料和释热区发生周期性压缩与舒张，从而产生准周期释热率脉动。对LES提取的子午面数据进行模态分解，发现速度脉动和释热率脉动主要集中在射流区与剪切层处，均为进口速度激励导致的纵向脉动。
- 外激励 /
- 分层旋流 /
- 贫油直喷 /
- 大涡模拟 /
- 相空间重构 /
- 模态分解
Abstract:
To study the feedback of shear swirl and flame and its induced combustion instability mechanism in the lean direct injection (LDI) combustor, the dynamic response of flow field and flame excited with external excitation was studied by large eddy simulation (LES) combined with phase space reconstruction and modal decomposition. Comparing the experimental results of the flow field with the time averaged results of LES, it was found that the velocity distribution of the numerical calculation and the size and position of the vortex structure were in good agreement with the experimental results. The analysis of LES acquisition signal and instantaneous flow field showed that the pressure and heat release pulsation were in the limit cycle oscillation state. The contraction and expansion of the recirculation zone under velocity pulsation led to the periodic compression and relaxation of the fuel and heat release zone, resulting in quasi-periodic heat release pulsation. The modal decomposition of the data on the meridian plane showed that the velocity and heat release pulsation were mainly concentrated in the shear layer and the jet region. Meanwhile, the main pulsation modes were all longitudinal pulsations excited by the inlet velocity.
- excitation /
- stratified swirl /
- lean direct injection /
- large eddy simulation /
- phase space reconstruction /
- modal decomposition

HTML

图 1 LDI燃烧室头部结构与时均温度场

Figure 1. Head structure of LDI combustor and its time-averaged temperature field

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图 2 计算域网格划分

Figure 2. Computational domain meshing

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图 3 不同轴向位置声压响应

Figure 3. Sound pressure response at different axial positions

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图 4 试验系统图

Figure 4. Schematic of experimental setup

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图 5 子午面速度云图及流线图

Figure 5. Meridional velocity contour and streamline

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图 6 子午面不同轴向位置时均轴向速度分布

Figure 6. Time-averaged axial velocity distribution at different axial positions on meridional plane

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图 7 湍动能谱

Figure 7. Turbulent kinetic energy spectrum

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图 8 频域与相空间轨迹

Figure 8. Frequency domain and phase space trajectories

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图 9 速度、压力与释热率时域图

Figure 9. Time domain of velocity, pressure and heat release

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图 10 子午面流场与释热率发展情况图

Figure 10. Development of meridional flow field and heat release

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图 11 1个周期内PVC与涡量发展情况

Figure 11. Development of precession vortex core and vorticity in a time period

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图 12 y=31 mm截面瞬时压力、周向速度及流线图

Figure 12. y=31 mm plane instantaneous pressure, circumferential velocity and streamline diagram

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图 13 速度场与释热率脉动POD结果

Figure 13. Velocity field and heat release pulsation POD result

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图 14 速度与释热率脉动DMD结果

Figure 14. Velocity field and heat release pulsation DMD result

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