微扩散氢燃料喷嘴设计对燃烧振荡特性的影响

李笑靥; 李嘉怡; 昌运鑫; 杨一然; 韩啸; 林宇震

doi:10.13224/j.cnki.jasp.20240566

微扩散氢燃料喷嘴设计对燃烧振荡特性的影响

doi: 10.13224/j.cnki.jasp.20240566

李笑靥^{1, 2, 3, 4,},
李嘉怡^{1, 3, 4},
昌运鑫^{1, 3, 4},
杨一然^{1, 3, 4},
韩啸^{1, 3, 4,*, ,},
林宇震^{1, 3, 4}

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
北京航空航天大学国家卓越工程师学院，北京 100191
3.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 100191
4.
先进航空发动机协同创新中心，北京 100191

基金项目: 国家自然科学基金（52476099）；航空发动机及燃气轮机基础科学中心项目（P2022-A-Ⅱ-006-001）；重点实验室基金（2023-JCJQ-LB-063-0306）；中央高校基本科研业务费专项资金

详细信息

作者简介:
李笑靥（2002-），女，硕士生，研究领域为氢燃料燃烧。E-mail：lixydimple@buaa.edu.cn

通讯作者:
韩啸（1993-），男，副研究员，博士，研究领域为氢燃料燃烧、燃烧振荡机理及控制。E-mail：han_xiao@buaa.edu.cn

中图分类号: V231.2
计量
- 文章访问数: 679
- HTML浏览量: 294
- PDF量: 86
- 被引次数: 0
出版历程
- 收稿日期: 2024-08-14
- 网络出版日期: 2025-01-08

Impact of array micro-tube diffusion burner for hydrogen fuel on combustion instability characteristics

LI Xiaoye^{1, 2, 3, 4
,},
LI Jiayi^{1, 3, 4},
CHANG Yunxin^{1, 3, 4},
YANG Yiran^{1, 3, 4},
HAN Xiao^{1, 3, 4,*
, ,},
LIN Yuzhen^{1, 3, 4}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
2.
National Superior College for Engineers，Beihang University，Beijing 100191，China
3.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，Beihang University，Beijing 100191，China
4.
Collaborative Innovation Center for Advanced Aero-Engine，Beijing 100191，China

摘要

摘要:
研究了一种微扩散氢燃料喷嘴，数值仿真模拟了改变空气通道周向间距、氢气喷孔孔径、氢气喷孔位置等设计方案在冷态、热态工况下的流动燃烧特性，并在常温常压（300 K、101 kPa）和加温常压（300～533 K、101 kPa）工况下进行了燃烧性能实验，考察了3个参数及冷却孔设计对热声振荡特性的影响，获得了最优方案。研究结果表明：微扩散喷嘴发生热声振荡时会产生角涡回流区，增大空气流量和升高温度能够增强燃空掺混性，抑制燃烧振荡的发生。在533 K、101 kPa的进气条件下，喷嘴最优方案在宽当量比下能够稳定燃烧，振幅不高于12.5 Pa，噪声不大于101 dB，为氢燃料燃烧室设计等工程应用提供参考。
- 氢气 /
- 微混燃烧 /
- 燃烧振荡 /
- 频谱特征 /
- 燃烧噪声
Abstract:
A study on a micro-diffusion hydrogen fuel nozzle was conducted through numerical simulations to analyze the flow and combustion characteristics under cold and hot conditions by altering the circumferential spacing of the air injection holes, the diameter of the hydrogen fuel injection holes, and the position of the hydrogen fuel injection holes. Combustion performance experiments were carried out under ambient temperature and pressure (300 K, 101 kPa) and elevated temperature and pressure (300—533 K, 101 kPa) conditions. The effects of three parameters and the design of cooling holes on thermoacoustic oscillation characteristics were investigated, contributing to the identification of the optimal scheme. The research results indicated that the micro-diffusion nozzle generated a corner vortex recirculation zone during thermoacoustic oscillation. Increasing the airflow and temperature can enhance the mixing of air and fuel, thereby suppressing combustion oscillations. Under the intake conditions of 533 K and 101 kPa, the optimal nozzle scheme achieved stable combustion across a wide equivalence ratio, with an amplitude of less than 12.5 Pa and noise levels below 101 dB, providing a reference for the design of hydrogen fuel combustion chambers and other engineering applications.
- hydrogen /
- micro-mixed combustion /
- combustion oscillations /
- spectral characteristics /
- combustion noise

HTML

图 1 微扩散氢燃料喷嘴方案模型

Figure 1. Micro-diffusion hydrogen fuel nozzle design model

下载: 全尺寸图片幻灯片

图 2 YZ截面温度云图

Figure 2. YZ sectional temperature contour map

下载: 全尺寸图片幻灯片

图 3 XY截面温度云图

Figure 3. XY sectional temperature contour map

下载: 全尺寸图片幻灯片

图 4 YZ截面轴向速度云图

Figure 4. YZ cross-sectional axial velocity contour map

下载: 全尺寸图片幻灯片

图 5 YZ截面OH云图

Figure 5. Contour map of OH mole fraction distribution on the YZ cross-section

下载: 全尺寸图片幻灯片

图 6 模型燃烧室示意图

Figure 6. Schematic diagram of the combustion chamber model

下载: 全尺寸图片幻灯片

图 7 实验系统简图

Figure 7. Schematic diagram of the experimental system

下载: 全尺寸图片幻灯片

图 8 常温3%压降下火焰图片

Figure 8. Flame images under normal temperature with 3% pressure drop

下载: 全尺寸图片幻灯片

图 9 不同压降下压力脉动幅值随当量比变化图

Figure 9. Graph of pressure pulsation amplitude variation with equivalence ratio under different pressure drops

下载: 全尺寸图片幻灯片

图 10 同压降下压力脉动幅值随当量比变化对比图

Figure 10. Comparison graph of pressure pulsation amplitude variation with equivalence ratio under the same pressure drop

下载: 全尺寸图片幻灯片

图 11 常温3%压降下0.65当量比火焰图片

Figure 11. Flame images at 0.65 equivalence ratio under 3% pressure drop

下载: 全尺寸图片幻灯片

图 12 压力脉动幅值和噪声随当量比变化图（空气压降为3%）

Figure 12. Graph showing variation of pressure pulsation amplitude and noise with equivalence ratio（air pressure drop is 3%）

下载: 全尺寸图片幻灯片

图 13 3%压降下0.65当量比压力脉动频谱图

Figure 13. Pressure pulsation spectrum plot at 0.65 equivalence ratio under 3% pressure drop

下载: 全尺寸图片幻灯片

图 14 不同压降下压力脉动幅值图

Figure 14. Graph showing pressure pulsation amplitude under different pressure drops

下载: 全尺寸图片幻灯片

图 15 同压降下压力脉动幅值随当量比变化对比图

Figure 15. Comparison graph showing pressure pulsation amplitude variation with equivalence ratio under the same pressure drop

下载: 全尺寸图片幻灯片

图 16 1%压降下0.65当量比压力脉动频谱图

Figure 16. Pressure pulsation spectrum plot at 0.65 equivalence ratio under 1% pressure drop

下载: 全尺寸图片幻灯片

图 17 HB01方案发生热声振荡前后火焰对比图

Figure 17. Comparison of flame images before and after thermoacoustic oscillation occurrence in the HB01 scheme

下载: 全尺寸图片幻灯片

图 18 3%压降下压力脉动幅值随当量比变化图

Figure 18. Graph showing variation of pressure pulsation amplitude with equivalence ratio under 3% pressure drop

下载: 全尺寸图片幻灯片

图 19 3%压降下火焰图像对比图

Figure 19. Comparison of flame images under 3% pressure drop

下载: 全尺寸图片幻灯片

图 20 Case 0方案全工况压力脉动幅值随当量比变化图

Figure 20. Graph showing variation of pressure pulsation amplitude with equivalence ratio across all operating conditions in Case 0

下载: 全尺寸图片幻灯片

表 1 数值模拟工况表

Table 1. Numerical simulation operating conditions table

工况	数据
进口空气总温/K	常温
进口空气总压/MPa	常压
空气流量/（kg/s）	0.0131
氢气当量比	0.45
氢气流量/ （kg/s）	0.0002
氢气温度/K	300
有效面积/mm²	155

下载: 导出CSV

表 2 喷嘴数值模拟参数变化方案

Table 2. Numerical simulation schemes for nozzle parameter variations

研究参数	方案名称（HB01-）
空气通道周向间距	W2、W3、W4
氢气喷孔孔径	D0.6、D0.7、D0.8
氢气喷孔位置	H1、H2、H3

下载: 导出CSV

表 3 实验工况参数

Table 3. Experimental condition parameters

进口温度/K	进口压力/Pa	压降/%	当量比范围
300	当地大气压	1	0.3～0.8 间隔0.05
300	当地大气压	2	0.3～0.8 间隔0.05
300	当地大气压	3	0.3～0.8 间隔0.05
373	当地大气压	3	0.3～0.8 间隔0.05
453	当地大气压	3	0.3～0.8 间隔0.05
533	当地大气压	3	0.3～0.8 间隔0.05

下载: 导出CSV

参考文献(36)

[1]	项目综合报告编写组. 《中国长期低碳发展战略与转型路径研究》综合报告[J]. 中国人口·资源与环境,2020,30(11): 1-25. Project Comprehensive Report Writing Group. Comprehensive report on “China’s long-term low-carbon development strategy and transition pathways”[J]. China Population,Resources and Environment,2020,30(11): 1-25. (in Chinese Project Comprehensive Report Writing Group. Comprehensive report on “China’s long-term low-carbon development strategy and transition pathways”[J]. China Population, Resources and Environment, 2020, 30(11): 1-25. (in Chinese)
[2]	AMPAH J D,JIN Chao,RIZWANUL FATTAH I M,et al. Investigating the evolutionary trends and key enablers of hydrogen production technologies: a patent-life cycle and econometric analysis[J]. International Journal of Hydrogen Energy,2023,48(96): 37674-37707. doi: 10.1016/j.ijhydene.2022.07.258
[3]	林宇震,许全宏,刘高恩. 燃气轮机燃烧室[M]. 北京: 国防工业出版社,2008. LIN Yuzhen,XU Quanhong,LIU Gaoen. Cas turbine combustor[M]. Beijing: National Defense Industry Press,2008. (in Chinese LIN Yuzhen, XU Quanhong, LIU Gaoen. Cas turbine combustor[M]. Beijing: National Defense Industry Press, 2008. (in Chinese)
[4]	张弛,林宇震,徐华胜,等. 民用航空发动机低排放燃烧室技术发展现状及水平[J]. 航空学报,2014,35(2): 332-350. ZHANG Chi,LIN Yuzhen,XU Huasheng,et al. Development status and level of low emissions combustor technologies for civil aero-engine[J]. Acta Aeronautica et Astronautica Sinica,2014,35(2): 332-350. (in Chinese ZHANG Chi, LIN Yuzhen, XU Huasheng, et al. Development status and level of low emissions combustor technologies for civil aero-engine[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(2): 332-350. (in Chinese)
[5]	莫妲,林宇震,韩啸,等. 氢气微混燃烧技术研究现状和未来展望[J]. 航空学报,2024,45(7): 36-62. MO Da,LIN Yuzhen,HAN Xiao,et al. Current status and future prospects of hydrogen micro-mixed combustion technology research[J]. Acta Aeronautica et Astronautica Sinica,2024,45(7): 36-62. (in Chinese MO Da, LIN Yuzhen, HAN Xiao, et al. Current status and future prospects of hydrogen micro-mixed combustion technology research[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 36-62. (in Chinese)
[6]	赵钦新,王宗一,邓世丰,等. 氢气燃烧技术及其进展[J]. 科学技术与工程,2022,22(36): 15870-15880. ZHAO Qinxin,WANG Zongyi,DENG Shifeng,et al. Hydrogen combustion technology and progress[J]. Science Technology and Engineering,2022,22(36): 15870-15880. (in Chinese doi: 10.3969/j.issn.1671-1815.2022.36.003 ZHAO Qinxin, WANG Zongyi, DENG Shifeng, et al. Hydrogen combustion technology and progress[J]. Science Technology and Engineering, 2022, 22(36): 15870-15880. (in Chinese) doi: 10.3969/j.issn.1671-1815.2022.36.003
[7]	MAREK C,SMITH T,KUNDU K. Low emission hydrogen combustors for gas turbines using lean direct injection[C]//Proceedings of the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston,Virigina: AIAA,2005: 3776 .
[8]	YORK W D,ZIMINSKY W S,YILMAZ E. Development and testing of a low NOX hydrogen combustion system for heavy duty gas turbines[C]//Proceedings of ASME Turbo Expo 2012: Turbine Technical Conference and Exposition,2013: 1395-1405.
[9]	KIM D,JOO S,YOON Y. Effects of fuel line acoustics on the self-excited combustion instability mode transition with hydrogen-enriched laboratory-scale partially premixed combustor[J]. International Journal of Hydrogen Energy,2020,45(38): 19956-19964. doi: 10.1016/j.ijhydene.2020.05.074
[10]	ASAI T,DODO S,KARISHUKU M,et al. Multiple-injection dry low-NOx combustor for hydrogen-rich syngas fuel: testing and evaluation of performance in an IGCC pilot plant[J]. Mechanical Engineering Journal,2014,1(5): 14-24.
[11]	DODO S,ASAI T,KOIZUMI H,et al. Combustion characteristics of a multiple-injection combustor for dry low-NO_x combustion of hydrogen-rich fuels under medium pressure[C]//Proceedings of ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition,New York,US: American Society of Mechanical Engineers,2012: 467-476.
[12]	RAJASEGAR R,MITSINGAS C M,MAYHEW E K,et al. Development and experimental characterization of metal 3D-printed scalable swirl stabilized mesoscale burner array[C]//Proceedings of ASME 2017 International Mechanical Engineering Congress and Exposition,New York,US: American Society of Mechanical Engineers,2018: 58417.
[13]	CHOI J,RAJASEGAR R,LEE W,et al. Hydrogen enhancement on a mesoscale swirl stabilized burner array[J]. International Journal of Hydrogen Energy,2021,46(46): 23906-23915. doi: 10.1016/j.ijhydene.2021.04.157
[14]	FUNKE H H W,BECKMANN N,KEINZ J,et al. 30 years of dry-low-NO_x micromix combustor research for hydrogen-rich fuels—an overview of past and present activities[J]. Journal of Engineering for Gas Turbines and Power,2021,143(7): 071002. doi: 10.1115/1.4049764
[15]	FUNKE H H,BORNER S,ROBINSON A,et al. Low NOx H₂ combustion for industrial gas turbines of various power ranges[R]Brussels: European Turbine Network,2010.
[16]	FUNKE H H W,BECKMANN N,ABANTERIBA S. An overview on dry low NOx micromix combustor development for hydrogen-rich gas turbine applications[J]. International Journal of Hydrogen Energy,2019,44(13): 6978-6990. doi: 10.1016/j.ijhydene.2019.01.161
[17]	FUNKE H H W,BOERNER S,KREBS W,et al. Experimental characterization of low NOx micromix prototype combustors for industrial gas turbine applications[C]//Proceedings of ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition,New York,US: American Society of Mechanical Engineers,2012: 343-353.
[18]	SUN Xiaoxiao,AGARWAL P,CARBONARA F,et al. Numerical investigation into the impact of injector geometrical design parameters on hydrogen micro-mix combustion characteristic[C]// Turbo Expo: Power for Land,Sea,and Air. New York,US: American Society of Mechanical Engineers,2020,84119.
[19]	MCCLURE J,ABBOTT D,AGARWAL P,et al. Comparison of hydrogen micromix flame transfer functions determined using RANS and LES[R]. New York,US: Turbo Expo: Power for Land,Sea,and Air,2019.
[20]	ZGHAL M,SUN Xiaoxiao,GAUTHIER P,et al. Comparison of tabulated and complex chemistry turbulent-chemistry interaction models with high fidelity large eddy simulations on hydrogen flames[R]. New York,US: Turbo Expo: Power for Land,Sea,and Air,2020.
[21]	林宇震,李林,张弛,等. 液体射流喷入横向气流混合特性研究进展[J]. 航空学报,2014,35(1): 46-57. LIN Yuzhen,LI Lin,ZHANG Chi,et al. Progress on the mixing of liquid jet injected into a crossflow[J]. Acta Aeronautica et Astronautica Sinica,2014,35(1): 46-57. (in Chinese LIN Yuzhen, LI Lin, ZHANG Chi, et al. Progress on the mixing of liquid jet injected into a crossflow[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 46-57. (in Chinese)
[22]	彭瀚,黄玥,刘晨,等. 横向射流影响缓燃向爆震转捩过程的实验研究[J]. 航空学报,2017,39(2): 121412. PENG Han,HUANG Yue,LIU Chen,et al. Experimental study on the influence of transverse jet on the deflagration-to-detonation transition process[J]. Acta Aeronautica et Astronautica Sinica,2017,39(2): 121412. (in Chinese PENG Han, HUANG Yue, LIU Chen, et al. Experimental study on the influence of transverse jet on the deflagration-to-detonation transition process[J]. Acta Aeronautica et Astronautica Sinica, 2017, 39(2): 121412. (in Chinese)
[23]	KEINZ J,KUSTERER K,HAJ A A,et al. Development and testing of a low NOx micromix combustion chamber for industrial gas turbines[J]. International Journal of Gas Turbine,Propulsion and Power Systems,2017,9(1): 27-36. doi: 10.38036/jgpp.9.1_27
[24]	FUNKE HARALD H W,NILS B,JAN K,et al. Numerical and experimental evaluation of a dual-fuel dry-low-NOx micromix combustor for industrial gas turbine applications[J]. Journal of Thermal Science and Engineering Applications,2019,11(1): 011015. doi: 10.1115/1.4041495
[25]	ZIEMANN J,SHUM F,MOORE M,et al. Low-NOx combustors for hydrogen fueled aero engine[J]. International Journal of Hydrogen Energy,1998,23(4): 281-288. doi: 10.1016/S0360-3199(97)00054-2
[26]	FADOK J. Advanced hydrogen turbine development phase 1 final technical report[R]. Orlando,US: Siemens Power Generation,Incorporated,2008.
[27]	LIU X W,SHAO W W,TIAN Y,et al. Investigation of H2/CH₄-air flame characteristics of a micromix model burner at atmosphere pressure condition[R]. New York,US: Proceedings of ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition,2018.
[28]	刘勋伟. 含氢燃料多微混射流火焰的燃烧特性与稳焰机制研究[D]. 北京: 中国科学院大学(中国科学院工程热物理研究所),2021. LIU Xunwei. Study on the combustion characteristics and stable flame mechanism of multi-micro-mixed jet flames with hydrogen-containing fuels[D]. Beijing: University of Chinese Academy of Sciences (Institute of Engineering Thermophysics,Chinese Academy of Sciences),2021. (in Chinese LIU Xunwei. Study on the combustion characteristics and stable flame mechanism of multi-micro-mixed jet flames with hydrogen-containing fuels[D]. Beijing: University of Chinese Academy of Sciences (Institute of Engineering Thermophysics, Chinese Academy of Sciences), 2021. (in Chinese)
[29]	LIU Xunwei,SHAO Weiwei,LIU Ce,et al. Numerical study of a high-hydrogen micromix model burner using flamelet-generated manifold[J]. International Journal of Hydrogen Energy,2021,46(39): 20750-20764. doi: 10.1016/j.ijhydene.2021.03.157
[30]	刘贵闯. 稀释剂对合成气微混合燃烧特性影响的数值模拟研究[D]. 哈尔滨: 哈尔滨工业大学,2020. LIU Guichuang. Numerical simulation study on the influence of diluent on the combustion characteristics of syngas micro-mixing[D]. Harbin: Harbin Institute of Technology,2020. (in Chinese LIU Guichuang. Numerical simulation study on the influence of diluent on the combustion characteristics of syngas micro-mixing[D]. Harbin: Harbin Institute of Technology, 2020. (in Chinese)
[31]	张永生,张海龙,田龙,等. 稀释合成气微混合燃料喷射燃烧火焰特性研究[J]. 动力工程学报,2015,35(1): 45-49,69. ZHANG Yongsheng,ZHANG Hailong,TIAN Long,et al. Characteristic study on syngas flames with combined CO₂ dilution and micro-mixing injection combustion[J]. Journal of Chinese Society of Power Engineering,2015,35(1): 45-49,69. (in Chinese ZHANG Yongsheng, ZHANG Hailong, TIAN Long, et al. Characteristic study on syngas flames with combined CO₂ dilution and micro-mixing injection combustion[J]. Journal of Chinese Society of Power Engineering, 2015, 35(1): 45-49, 69. (in Chinese)
[32]	田龙. 合成气微混合火焰燃烧及流场特性研究[D]. 北京: 华北电力大学,2014. TIAN Long. Study on combustion and flow field characteristics of syngas micro-mixed flame[D]. Beijing: North China Electric Power University,2014. (in Chinese TIAN Long. Study on combustion and flow field characteristics of syngas micro-mixed flame[D]. Beijing: North China Electric Power University, 2014. (in Chinese)
[33]	莫妲,林宇震,马宏宇,等. 基于钝体扰流的氢气微混扩散燃烧组织研究[J]. 航空学报,2024,45(8): 128928. MO Da,LIN Yuzhen,MA Hongyu,et al. Investigation on hydrogen micromix diffusive combustion organization based on bluff body disturbance[J]. Acta Aeronautica et Astronautica Sinica,2024,45(8): 128928. (in Chinese MO Da, LIN Yuzhen, MA Hongyu, et al. Investigation on hydrogen micromix diffusive combustion organization based on bluff body disturbance[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128928. (in Chinese)
[34]	STEINBERG A M,SADANANDAN R,DEM C,et al. Structure and stabilization of hydrogen jet flames in cross-flows[J]. Proceedings of the Combustion Institute,2013,34(1): 1499-1507. doi: 10.1016/j.proci.2012.06.026
[35]	莫妲,尚守堂,林宇震,等. 一种氢燃料微尺度非预混燃烧室数值模拟[J]. 航空动力学报,2023,38(11): 2701-2710. MO Da,SHANG Shoutang,LIN Yuzhen,et al. Numerical simulation investigation on a hydrogen micromix combustor[J]. Journal of Aerospace Power,2023,38(11): 2701-2710. (in Chinese MO Da, SHANG Shoutang, LIN Yuzhen, et al. Numerical simulation investigation on a hydrogen micromix combustor[J]. Journal of Aerospace Power, 2023, 38(11): 2701-2710. (in Chinese)
[36]	昌运鑫,宋恒,韩猛,等. 掺氢功率比对富氢甲烷燃烧振荡特性的影响[J]. 推进技术,2023,44(1): 210673. CHANG Yunxin,SONG Heng,HAN Meng,et al. Effects of hydrogen power ratio on combustion oscillation characteristics of hydrogen-enriched methane[J]. Journal of Propulsion Technology,2023,44(1): 210673. (in Chinese CHANG Yunxin, SONG Heng, HAN Meng, et al. Effects of hydrogen power ratio on combustion oscillation characteristics of hydrogen-enriched methane[J]. Journal of Propulsion Technology, 2023, 44(1): 210673. (in Chinese)