发表机构
AeroMyne（AeroMyne）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
针对纯氢航空发动机燃烧室，通过三维模拟揭示拓扑火焰分岔与回火裕度，并建立NOx排放的多路径标度规律，为低碳燃烧室设计提供验证方法。
AI 中文摘要
在航空涡轮机中燃烧纯氢可消除碳排放，但快速反应速率会在飞行节流过程中引发喷嘴回火危险和高氮氧化物排放。本研究在当量比0.55至1.00范围内，考察了双旋流燃烧室中的气动热保持机制、回火安全裕度和排放路径。三维模拟结合了曲率修正的剪切应力输运湍流闭合、双速率有限速率和涡耗散化学动力学以及离散坐标辐射，并依据ASME网格标准，与实验激光基准进行了验证。推进发动机节流会触发拓扑火焰转变，从贫油怠速时附着于面板的M型火焰转变为当量比高于0.895时的提升V型火焰，而壁面回火安全指数始终超过3.42。氮氧化物排放从贫油怠速时水协助的氧化亚氮中间反应（28.01 ppm，EINOx = 1.85 g/kg）转变为起飞时热Zeldovich机制主导下的319.21 ppm（EINOx = 35.40 g/kg），受幂律指数4.92控制。这些发现提供了经过验证的可操作极限，并为实际零碳航空发动机燃烧室开发建立了一种基于工作站的易用筛选方法。
英文摘要
Burning neat hydrogen in aircraft turbines eliminates carbon emissions, yet rapid reaction rates trigger nozzle flashback hazards and high nitrogen oxide emissions across flight throttles. This study investigates aerothermal holding mechanisms, flashback safety margins, and emission pathways in a dual-swirl combustor across equivalence ratios from 0.55 to 1.00. Three-dimensional simulations combine curvature-corrected shear-stress transport turbulence closure, dual-rate finite-rate and eddy-dissipation chemical kinetics, and discrete ordinates radiation, validated against experimental laser benchmarks using ASME grid standards. Advancing engine throttle triggers a topological flame transition from a faceplate-attached M-flame at lean idle to a lifted V-flame above equivalence ratio 0.895, while wall flashback safety indices consistently exceed 3.42. Nitric oxide emissions transition from water-chaperoned nitrous oxide intermediate reactions at lean idle (28.01 ppm, EINOx = 1.85 g/kg), scaling to 319.21 ppm (EINOx = 35.40 g/kg) at takeoff under thermal Zeldovich dominance, governed by a power-law exponent of 4.92. These findings deliver validated operability limits and establish an accessible workstation-based screening methodology for practical zero-carbon aero-engine combustor development.
Comments17 pages, 12 figures, 4 tables. Formatted with APS RevTeX 4-2. Research data and simulation monitors available on Figshare (doi:10.6084/m9.figshare.33684790)
