Effects of injector configuration on mixing characteristics in the combustion chamber of a hollow-core rotating detonation engine
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摘要:
为了探究燃料与超声速来流的掺混特性，基于空桶型旋转爆轰冲压发动机燃烧室，以环缝-小孔型喷注结构为基础模型，开展了燃料喷注角度、喷注方式以及喷注环轴向位置对燃料和超声速来流掺混特性影响的数值模拟研究。结果表明：燃料喷注角度的增大，会提高燃料掺混的均匀度，降低总压损失，横向射流之间碰撞更为剧烈。将燃料非对撞喷注，掺混均匀度增大，超声速来流与燃料的碰撞面积增大。喷注环向上游移动，能提高燃料的掺混均匀度，横向射流与超声速来流的掺混距离变长。结合流场结构分析可知：超声速来流与乙烯横向射流在扩张段内发生圆柱绕流，形成向下游张开的一个扇形连续膨胀区，进入燃烧室后掺混主流形成一连串的破碎小涡结构，进而促进了乙烯-空气的掺混效果。
Abstract:To investigate the mixing characteristics of fuel and supersonic inflow, a numerical simulation study was conducted based on the annular-slot-orifice injection structure in the combustion chamber of an open-barrel-type rotating detonation ramjet engine. The study explored the effects of fuel injection angle, injection method, and axial position of the injection ring on the mixing characteristics of fuel and supersonic inflow. The results showed that increasing the fuel injection angle improves the uniformity of fuel mixing, reduces total pressure loss, and leads to more intense collisions between transverse jets. When the fuel is injected in a non-colliding manner, the mixing uniformity increases, and the collision area between the supersonic inflow and the fuel enlarges. Moving the injection ring upstream enhances the uniformity of fuel mixing, and the mixing distance between the transverse jet and the supersonic inflow becomes longer. Analysis of the flow field structure revealed that the supersonic inflow and ethylene transverse jets undergo cylindrical wake flow within the expansion section, forming a fan-shaped continuous expansion region extending downstream. Upon entering the combustion chamber, the primary mixing flow forms a series of fragmented small vortex structures, thereby promoting the mixing effect of ethylene and air.
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图 2 燃烧室典型截面结构示意图
Figure 2. Schematic diagram of typical cross-section structures of combustion chamber
图 6 θ=180°流场速度梯度和温度着色的 Q 准则等值面（Q=108）
Figure 6. Q criterion contour of flow field velocity gradient and temperature coloring （Q=108） at θ=180°
图 7 不同喷注角度的内流场结构云图
Figure 7. Contours of internal flow-field structure at different injection angles
图 8 不同喷注角度截面乙烯质量分数分布云图
Figure 8. Contours of ethylene mass-fraction distribution on cross-sections at different injection angles
图 9 不同喷注角度的乙烯沿程掺混均匀度
Figure 9. Blending uniformity of ethylene with different injection angles along the way
图 10 不同喷注方式中心截面处的内流场结构云图
Figure 10. Nephogram of internal flow field structure at the central section of different injection modes.
图 11 不同喷注方式乙烯组分分布云图
Figure 11. Distribution nephogram of ethylene components in different injection methods.
图 12 乙烯沿程掺混均匀度曲线图
Figure 12. Mixing-uniformity curve of ethylene along the axial direction
图 13 不同喷注环位置中心截面处马赫数云图与流线图
Figure 13. At the central section of different injection ring positions Mach number nephogram and streamline diagram
图 14 不同喷注环位置乙烯组分分布云图
Figure 14. Distribution nephogram of ethylene components at different injection ring positions
图 15 不同喷注环位置乙烯沿程掺混均匀度曲线图
Figure 15. Curves of ethylene axial mixing-uniformity at various injection-ring locations
表 1 入口参数
Table 1. Boundary condition
Tair/K pair/MPa TC2H4/K PC2H4/MPa pout/MPa Ma 860 0.60 300 1.70 0.10 1.99 
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表 2 不同喷注角度的总压恢复系数
Table 2. Total pressure recovery coefficient at different injection angles
喷注角度/（°） 总压恢复系数 90 0.2185 135 0.2273 180 0.2425
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表 3 不同喷注方式的总压恢复系数
Table 3. Total pressure recovery coefficient of different injection methods
喷注方式 总压恢复系数 90°非对撞 0.2361 180°非对撞 > 0.2469 90°对撞 0.2185 180°对撞 0.2425
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表 4 不同喷注环位置总压恢复系数
Table 4. Total pressure recovery coefficient at different injection ring positions
喷注位置 总压恢复系数 x=7D 0.2501 x=9D 0.2469 x=11D 0.2421
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