莫妲1,2,3, 林宇震1,2, 韩啸1,2(), 马宏宇3, 刘一雄3
收稿日期:
2023-05-15
修回日期:
2023-06-16
接受日期:
2023-07-11
出版日期:
2024-04-15
发布日期:
2023-07-21
通讯作者:
韩啸
E-mail:han_xiao@buaa.edu.cn
基金资助:
Da MO1,2,3, Yuzhen LIN1,2, Xiao HAN1,2(), Hongyu MA3, Yixiong LIU3
Received:
2023-05-15
Revised:
2023-06-16
Accepted:
2023-07-11
Online:
2024-04-15
Published:
2023-07-21
Contact:
Xiao HAN
E-mail:han_xiao@buaa.edu.cn
Supported by:
摘要:
氢燃料在航空发动机、空天推进系统和地面燃气轮机等领域的应用可以实现零碳排放,对于缓解全球气候变化和保护环境具有重要意义。但氢燃烧应用仍面临着许多技术挑战,若在传统燃烧室中燃烧氢气将面临回火和氮氧化物排放高的风险,需要探索新的氢燃烧技术和污染物控制措施,以满足氢能迫切发展的需要。微混燃烧技术通过成百上千个微通道结合氢气微喷射,使空气和氢气快速掺混,形成微小尺度火焰,缩短氮气在高温区的驻留时间到毫秒等级,可大幅度降低氮氧化物生成。本文回顾了氢燃料在燃气涡轮发动机中的应用发展历史,梳理了氢气特点、NO x 生成机理、微混燃烧原理、预混燃烧和扩散燃烧的掺混方式和头部结构特点,总结了国内外关于氢燃烧仿真和试验,以及热声不稳定问题的研究进展,讨论了微混燃烧室关键参数对气动热力过程和NO x 生成的影响,归纳了NO x 控制措施,为氢燃烧室工程设计提供理论和试验参考,并对氢燃烧技术未来的发展进行了展望。
中图分类号:
莫妲, 林宇震, 韩啸, 马宏宇, 刘一雄. 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): 28994-028994.
Da MO, Yuzhen LIN, Xiao HAN, Hongyu MA, Yixiong LIU. Research progress and future prospect of hydrogen micromix combustion technology[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 28994-028994.
表1
燃料特性对比[31-32]
Item | H2 | CH4 | Jet-A | JP-4 |
---|---|---|---|---|
Molecular weight | 2.016 | 16.04 | 168 | 132 |
Density/(kg·m-3) | 0.084 | 0.65 | 0.787 | 0.774 |
Heat of combustion (low)/(MJ·kg-1) | 119.93 | 50.02 | 42 | 42.8 |
Flammability limits in air/% | 4.0~75.0 | 5.3~15.0 | 0.6~4.7 | 0.8~5.8 |
Min. ignition energy/MJ | 0.02 | 0.29 | 0.25 | 0.25 |
Auto ignition temperature/K | 858 | 813 | >500 | >500 |
Flame temperature/K | 2 318 | 2 148 | 2 200 | 2 200 |
Burning velocity/(m·s-1) | 2.65~3.25 | 0.37~0.45 | 0.18 | 0.38 |
表2
微混燃烧仿真研究对比
Organization | Inlet conditions | Turbulence model | Method |
---|---|---|---|
University of Illinois[ | 0.1 MPa, 300 K | k-ε | Partially premixed combustion |
Funke[ | 0.1 MPa, 560 K | realizable k-ε | Eddy Dissipation Concept |
Cranfield University[ | 1.5 MPa, 600 K | k-ω SST (Shear Stress Transfer) | Flamelet Generated Manifold (FGM) |
NASA[ | 1.062 MPa, 800 K | Advanced nonlinear k-ε model | Intrinsically Low-Dimensional Manifold (ILDM) |
Chinese Academy of Sciences[ | 0.1 MPa, 277 K | Standard k-ε Realizable k-ε k-ω SST | Flamelet Generated Manifold (FGM) |
表3
氢燃烧机理对比
Mechanism | Species | Reaction steps | Advantages |
---|---|---|---|
Kéromnès-2013[ | 12 | 33 | Ignition delay time, flame velocity |
NUIG-NGM-2010[ | 11 | 21 | Ignition delay time |
ÓConaire-2004[ | 10 | 21 | Ignition delay time |
Konnov-2008[ | 10 | 33 | Flame velocity |
Li-2007[ | 11 | 25 | Flame velocity |
Starik-2009[ | 12 | 26 | JSR |
GRI3.0-1999[ | 10 | 29 | Flow reactor profiles |
表4
微混燃烧试验研究对比
Organization | Micro-mixing type | Injector shape and dimension | Hydrogen hole diameter | Inlet conditions | Test rig | NO x |
---|---|---|---|---|---|---|
University of Illinois at Urbana-Champaign[ | Premixed | Swirl and bluff body ∅7.5 mm | ∅0.25 mm | Atmosphere 40%H2-60%CH4 | 4×4 Burner array | |
West Virginia University[ | Non-premixed | Central fuel jet with 3 air lobes 166.4 mm2 | ∅0.99 mm | 1 600 kPa,600 K 100%H2 | 50 Array injectors | 4.4×10-6(15%含氧量) |
Aachen University Funke[ | Non-premixed | Jet-in-crossflow ∅1~3 mm | ∅0.8 mm | 1 600 kPa,600-700 K 100%H2 | 2 MW Class gas turbine | 35×10-6(15%含氧量) |
Cranfield University[ | Non-premixed | Jet-in-crossflow Air-hole area<10 mm2 | ∅0.3 mm | 1 500 kPa,600 K 100%H2 | 50 Array injectors | |
NASA[ | Premixed | LDI∅6.35 mm | ∅0.56 mm | 689.5 kPa,700 K 100%H2 | 7 Array injectors | 10×10-6 |
Chinese Academy of Sciences[ | Premixed | Multiple confluent turbulent round jets ∅10 mm | ∅2 mm | 101 kPa,288 K 0-60%H2 | 7 Array injectors | 10×10-6(15%含氧量) |
GE[ | Jet-in-crossflow | MT mixer millimeter scale | Millimeter scale | 1 700 kPa,650 K 66%H2/34%N2 20%N2/80% Air | Full can | 3×10-6(15%含氧量) |
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