Influence of injection position on combustion of multi-component fuel scramjet
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摘要:
为研究含铝高能量密度碳氢燃料在超燃冲压发动机中的燃烧组织细节，使用离散相模型（DPM）和简化反应机理对不同燃料喷注位置下燃烧流动过程进行了数值模拟。结果表明：使用七喷注器从上壁面进行燃料喷注时，出口截面处温度场形成了以近上壁面轴线为中心低温-升至最高温-降至较低温度的分布特征，氧浓度在中心处的含量也较低，这都将影响燃烧反应的进程。在研究工况下随着喷注器与燃烧室入口距离增大，燃料比冲呈先增大后减小的变化趋势，在研究工况中实现燃料最大比冲11092 m/s，可以通过改变燃料从上壁面喷入燃烧室的喷注位置和优化喷注器布局等提升燃烧室性能，优化后最大比冲提升了12.68%。
Abstract:In order to investigate the details of the combustion organization of aluminum-containing high-energy-density hydrocarbon fuels in scramjet engine, a discrete phase model (DPM) and simplified reaction mechanism were used to numerically simulate the combustion flow process at different fuel injection positions. The results showed that when the seven injectors were used to inject fuel from the upper wall, the exit section formed a temperature distribution near the center of the upper wall from inside to outside, namely, relatively low temperature-warming-up to the highest temperature-cooling down. The lower oxygen concentration of the upper wall near the center area affected the progress of the reaction. Under the research conditions, as the distance between the injector and the inlet of the combustion chamber increased, the fuel specific impulse first increased and then decreased. In the research condition, the maximum specific impulse of fuel was 11092 m/s. The performance of the combustion chamber can be improved by changing the injection position of the fuel injected into the combustion chamber from the upper wall and optimizing the injector layout. After optimization, the maximum specific impulse increased by 12.68%.
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图 3 壁面压力分布曲线的数值模拟和实验结果
Figure 3. Numerical simulation and experimental results of wall pressure distribution curve
图 4 凹腔附近燃烧室壁面温度云图
Figure 4. Temperature contour of the combustion chamber wall near the cavity
图 5 燃烧室对称截面凹腔附近温度云图
Figure 5. Temperature contour near the cavity of the symmetrical section of the combustion chamber
图 6 凹腔附近燃烧室壁面速度云图
Figure 6. Velocity contour of the combustion chamber wall near the cavity
图 7 燃烧室对称截面凹腔附近速度云图
Figure 7. Velocity contour near the cavity of the symmetrical section of the combustion chamber
图 9 凹腔内部分组分质量分数分布图
Figure 9. Distribution of mass fractions of some components in the cavity
图 10 燃料喷注下游燃烧室壁面温度云图
Figure 10. Temperature contour of the combustion chamber wall downstream of the fuel injection
图 11 距离燃烧室入口截面不同距离及出口截面温度云图
Figure 11. Temperature contour of different distances from the entrance section of the combustion chamber and the exit section
图 12 与燃烧室底部壁面不同距离水平截面O2质量分数分布图
Figure 12. O2 mass fraction distribution in horizontal section at different distances from the bottom wall of the combustion chamber
图 13 与燃烧室底部壁面不同距离水平截面CO质量分数分布图
Figure 13. CO mass fraction distribution in horizontal section at different distances from the bottom wall of the combustion chamber
图 14 与燃烧室底部壁面不同距离水平截面CO2质量分数分布图
Figure 14. CO2 mass fraction distribution of horizontal cross section at different distances from the bottom wall of the combustion chamber
图 15 不同位置喷注燃料时下壁面压力
Figure 15. Pressure on the bottom wall when fuel is injected at different positions
图 16 从与入口截面不同距离喷注燃料时凹腔温度图
Figure 16. Temperature diagram of the cavity when fuel is injected from a different distance from the inlet section
图 17 不同喷注位置燃料和氧气消耗率及出口组分比较
Figure 17. Comparison of fuel and oxygen consumption rates and outlet components at different injection positions
图 20 距离为L1=150 mm、L2=160 mm时燃烧室底部壁面和凹腔局部的温度
Figure 20. Temperature of the bottom wall of the combustion chamber and the local cavity when the distance is L1=150 mm and L2=160 mm
图 21 改变喷注布局前后燃料和氧气消耗率对比
Figure 21. Comparison of fuel and oxygen consumption rates before and after changing the injection layout
图 22 改变喷注布局前后出口组分对比
Figure 22. Comparison of outlet components before and after changing the injection layout
图 23 改变喷注布局前后比冲对比
Figure 23. Comparison of specific impulse before and after changing the injection layout
表 1 C10H16的10组分11步反应机理
Table 1. The 10-component 11-step reaction mechanism of C10H16
编号 反应 1 C10H16+O2→10CH+6H+O2 2 CH+O2→CO+OH 3 CH+O→CO+H 4 2H$\longleftrightarrow $H2 5 H2+O2$\longleftrightarrow $H2O+O 6 H2+O$\longleftrightarrow $H+OH 7 H+O2$\longleftrightarrow $O+OH 8 H2O+O2$\longleftrightarrow $2O+H2O 9 CO+OH$\longleftrightarrow $CO2+H 10 CO+H2O$\longleftrightarrow $CO2+H2 11 CO+H2+O2$\longleftrightarrow $CO2+H2O 
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表 2 实验入口参数
Table 2. Experimental entrance parameters
马赫数 总温/K 总压/MPa 空气总质量
流率/（kg/s）燃料
当量比$ \varphi $2.0 1700 0.70 0.60 0.73
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表 3 两排燃料喷注器与燃烧室入口截面的距离
Table 3. Distance between the two rows of fuel injectors and the entrance section of the combustion chamber
距离/mm 1 2 3 4 5 6 L1 90 110 130 150 170 190 L2 100 120 140 160 180 200
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