Numerical study of the impact of hydrogen addition, swirl intensity and equivalence ratio on methane-air combustion

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-07-07 DOI:10.1515/tjj-2021-0048

M. Elbayoumi, F. Garnier, P. Seers

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Abstract

Abstract Hydrogen-blended fuel is a promising resource for future generations of gas turbine engines, due to its capability of reducing carbon-based emissions. This paper presents a numerical study to assess hydrogen-enriched combustion in a laboratory-scale burner operating at a high turbulence level and under lean and stoichiometric burning conditions. Moreover, a wide range of H2 (up to 90 %) is used for enriching CH4-air combustion in combination with two different swirl levels. The results show that a high swirl intensity results in shorter flames, due to the increased turbulent intensity, which reduces the flame surface area and uniformness the reacting zone. Besides, increasing swirl intensity further increase flame temperature for a given H2-blended fuel. Overall, the results suggest that high swirl intensity in combination to lean mixtures is favorable when using H2-blended fuel with high H2 concentrations. The simulation results also demonstrate that considering radiation heat loss is influential, as it yields a reduction of the outlet temperature by not less than 100 K, bringing down NO x emissions by half.

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氢气添加量、涡流强度和当量比对甲烷-空气燃烧影响的数值研究

摘要氢混合燃料具有减少碳排放的能力，是未来几代燃气轮机发动机的一种很有前途的资源。本文介绍了一项数值研究，以评估实验室规模的燃烧器在高湍流水平和贫燃和化学计量燃烧条件下的富氢燃烧。此外，H2的范围很宽（高达90 %) 用于与两个不同的涡流水平相结合来富集CH4空气燃烧。结果表明，涡流强度越大，火焰越短，这是由于湍流强度的增加，火焰表面积越小，反应区越均匀。此外，对于给定的H2混合燃料，增加涡流强度会进一步提高火焰温度。总体而言，结果表明，当使用具有高H2浓度的H2混合燃料时，高涡流强度与贫混合物相结合是有利的。模拟结果还表明，考虑辐射热损失是有影响的，因为它会使出口温度降低不小于100 K、将NOx排放量降低一半。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.