Influence of injection structure on the mixing characteristics of CH4-O2 rotating detonation engine
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摘要:
为了探究不同喷注结构下的旋转爆轰发动机环形燃烧室的燃料掺混特性，采用商业软件FLUENT对冷态掺混流场进行数值仿真，采用密度基求解三维Navier-Stokes（N-S）方程，选取环缝-双侧喷孔对撞喷注结构作为基础模型，在保持进口条件一致的条件下，探究燃料喷注角度及其轴向位置对冷态流场掺混特性的影响。研究结果表明：随着喷注角度的增大，掺混不均匀度升高，总压损失增大，在喷注角度60°～180°范围内，60°的掺混不均匀度最低，总压损失最小；随着甲烷喷注轴向位置向上游移动，掺混距离增加，掺混不均匀度降低；结合流动特征分析可知，甲烷小孔射流在扩张段诱发复杂多变的涡系结构，继而促进甲烷-氧气的掺混效果。
Abstract:In order to investigate the influence of different injection structures on the fuel mixing characteristics inside the annular combustion chamber of a rotating detonation engine, numerical simulation analysis of the cold-state mixing flow field was conducted using the commercial software FLUENT, and the three-dimensional Navier-Stokes （N-S） equations were solved using a density-based scheme. Based on the annular gap-both sides orifice injection structure taken as the basic model, and under the same inlet conditions, the impacts of fuel injection angle and position on the mixing characteristic of the cold-state flow field were analyzed. The research results indicated as the injection angle increased, the unevenness of blending rised and the total pressure loss increased. Within the range of 60° to 180° for the injection angle, 60° exhibited the best mixing effect and minimum total pressure loss. As the methane injection position moved forward, the distance between the injection point and the combustion chamber increased, and the blending distance increased, leading to an enhancement in the mixing effect. Under non-premixed conditions, due to the influence of lateral methane jets, a complex and varied vortex structure was generated in the expansion section, enhancing the mixing effect of methane-oxygen.
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图 5 不同燃料喷注角度中心截面处马赫数云图与流线图
Figure 5. Mach number contour and streamlines on the central section at different fuel injection angles
图 6 不同燃料喷注角度扩张段处马赫数分布与流线特征
Figure 6. Mach number distribution and streamline characteristics on the expansion section at different fuel injection angles
图 7 不同燃料喷注角度中心截面处甲烷质量分数分布
Figure 7. Methane mass fraction distribution on the central section with different fuel injection angles
图 8 不同燃料喷注角度甲烷质量分数分布
Figure 8. Methane mass fraction distribution at different fuel injection angles
图 9 不同燃料喷注角度下平均甲烷质量分数
Figure 9. Average methane mass fraction at different fuel injection angles
图 10 不同燃料喷注角度下甲烷掺混不均匀度
Figure 10. Blending uniformity of methane mass fraction at different fuel injection angles
图 11 不同燃料喷注位置扩张段处流线图
Figure 11. Streamline diagram of the expansion section at different fuel injection locations
图 12 不同燃料喷注位置的中心截面处甲烷质量分数分布
Figure 12. Methane mass fraction distribution on the center section at different fuel injection locations
图 13 不同燃料喷注位置下甲烷掺混不均匀度
Figure 13. Non-uniformity of methane blending at different fuel injection positions
图 16 燃料喷注角度 θ =60°流场速度梯度着色的 Q 准则等值面（Q=107）
Figure 16. Q criterion iso-surface for the coloring of the velocity gradient of the flow field at the fuel injection angleθ =60° （Q=107）
图 17 燃料喷注角度 θ =60°流场温度着色的Q准则等值面（Q=107）
Figure 17. Q criterion iso-surface for temperature coloration of fuel injection angle θ = 60° flow field （Q=107）
表 1 数值计算边界条件
Table 1. Numerical calculation boundary conditions
$p_{{\mathrm{O}}_2} $/Pa $p_{{\mathrm{CH}}_4} $/Pa pout/Pa T/K 405 300 405 300 0 300 
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表 2 不同燃料喷注角度下总压恢复系数
Table 2. Total pressure recovery coefficient at different fuel injection angles
喷注角度/（°） 总压恢复系数σ 60 0.325 9 90 0.303 8 120 0.297 1 150 0.307 6 180 0.295 3
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表 3 不同燃料喷注位置下总压恢复系数
Table 3. Total pressure recovery coefficient at different fuel injection angles
喷注位置 总压恢复系数σ L = 1.25D 0.302 7 L = 2.5D 0.295 3 L = 5D 0.286 9
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表 4 不同喷注位置的动量比
Table 4. Momentum ratios at different injection locations
喷注位置 动量比q L = 1.25D 38.71 L = 2.5D 34.78 L = 5D 20.2
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