Impact of fuel injection schemes on combustion characteristics in supersonic combustors with non-symmetric inflow
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摘要:
针对一种S形隔离段-超声速燃烧室构型开展了不同喷注方案下的燃烧流场数值模拟研究，并与作为基准的等直隔离段-超声速燃烧室进行了对比，分析了S形隔离段对燃烧特性影响及隔离段内的反压前传过程，比较了不同构型和喷注方案的燃烧室冷态流场，燃烧流场与燃烧性能。研究结果表明：冷态条件下，S形隔离段对燃料的混合特性影响不大；但在燃烧条件下，强耦合的非线性系统会放大来流的非对称程度，进而造成燃烧场非均匀程度极具变化，同时降低了燃烧效率，由82%下降到65%。针对燃烧条件下的非均匀来流，优化了喷注方案，结合支板喷注，在燃烧室壁面增加了额外的喷注位置，提高了燃烧场的均匀性与燃烧效率。燃烧室的出口燃烧效率由65%达到了85%，总温分布系数由64%下降到26%，达到了均匀来流下的燃烧效率和燃烧场均匀程度。
Abstract:A numerical simulation study of combustion flow fields under different fuel injection schemes was conducted for an S-shaped isolator-supersonic combustor configuration. The results were compared with those of a baseline straight isolator-supersonic combustor to analyze the effects of the S-shaped isolator on combustion characteristics and the backpressure transmission process within the isolator. Additionally, the cold flow fields, combustion flow fields, and combustion performance of different configurations and injection schemes were compared. The study revealed the following: Under cold conditions, the S-shaped isolator had little impact on fuel mixing characteristics; however, under combustion conditions, the strongly coupled nonlinear system amplified the asymmetry of the inflow, leading to significant non-uniformity in the combustion field. At the same time, it reduced the combustion efficiency from 82% to 65%. To address the non-uniform inflow under combustion conditions, the injection scheme was optimized by combining rail injection and adding additional injection positions on the combustor wall. This improved both the uniformity and efficiency of the combustion field. The combustion efficiency at the combustor exit increased from 65% to 85%, and the total temperature distribution coefficient decreased from 64% to 26%, achieving nearly the same combustion efficiency and uniformity as under uniform inflow conditions.
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图 7 方案1马赫数云图及流线图（对称面）
Figure 7. Mach number map and streamline diagram（symmetry plane） of Case 1
图 10 方案1煤油质量分数云图（对称面）
Figure 10. Kerosene mass fraction map （symmetry plane） of Case 1
图 11 方案1煤油质量分数云图（不同轴向位置）
Figure 11. Kerosene mass fraction map （different axial positions） of Case 1
图 12 方案2马赫数云图及流线图（对称面）
Figure 12. Mach number map and streamline diagram（symmetry plane） of Case 2
图 15 方案2 煤油质量分数云图（对称面）
Figure 15. Kerosene mass fraction map （symmetry plane） of Case 2
图 16 方案2 煤油质量分数云图（不同轴向位置）
Figure 16. Kerosene mass fraction map （different axial positions） of Case 2
图 17 弯曲隔离段出口静压云图
Figure 17. Static pressure map at the outlet of the curved isolation section
图 18 弯曲隔离段出口静温云图
Figure 18. Static temperature map at the outlet of the curved isolation section
图 19 弯曲隔离段出口轴向速度云图
Figure 19. Axial velocity map at the outlet of the curved isolation section
图 21 方案1 燃烧状态静压云图（对称面）
Figure 21. Static pressure map of combustion state （symmetry plane） of Case 1
图 22 方案1 燃烧状态静温云图（对称面）
Figure 22. Static temperature map of combustion state （symmetry plane） of Case 1
图 23 方案1 燃烧状态马赫数云图（对称面）
Figure 23. Mach number map of combustion state （symmetry plane） of Case 1
图 24 方案1 燃烧状态不同轴向位置截面总温云图
Figure 24. Total temperature map at different axial positions of combustion state of Case 1
图 25 方案2 燃烧状态静压云图（对称面）
Figure 25. Static pressure map of combustion state （symmetry plane） of Case 2
图 26 方案2 燃烧状态静温云图（对称面）
Figure 26. Static temperature map of combustion state （symmetry plane） of Case 2
图 27 方案2 燃烧状态马赫数云图（对称面）
Figure 27. Mach number map of combustion state （symmetry plane） of Case 2
图 28 方案2 燃烧状态不同轴向位置截面总温云图
Figure 28. Total temperature map at different axial positions of combustion state of Case 2
图 29 S型隔离段在不同反压作用下的流动分离情况
Figure 29. Flow separation of S-shaped isolation section under different back pressures
图 30 S型隔离段在不同反压作用下马赫数云图
Figure 30. Mach number map of S-shaped isolation section under different back pressures
图 32 方案3 燃烧状态静压云图（对称面）
Figure 32. Static pressure map of combustion state（symmetry plane） of Case 3
图 33 方案3 燃烧状态静温云图（对称面）
Figure 33. Static temperature map of combustion state （symmetry plane） of Case 3
图 34 方案3 燃烧状态马赫数云图（对称面）
Figure 34. Mach number map of combustion state（symmetry plane） of Case 3
图 35 方案3 燃烧状态不同轴向位置截面总温云图
Figure 35. Total temperature map at different axial positions of combustion state of Case 3
表 1 燃烧室构型几何特征
Table 1. Geometric characteristics of combustion chamber configuration
几何参数 方案1 方案 2 L1/D1 6.0 6.0 L2/D1 2.0 2.0 L3/D1 2.0 2.0 D1/D1 1.0 1.0 D2/D1 1.0 1.0 D3/D1 1.7 1.7 D4/D1 1.3 1.3 D5/D1 1.7 1.7 H/D1 0.3 
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表 2 飞行马赫数6对应的隔离段进口参数
Table 2. Isolation section inlet parameters corresponding to flight Mach 6
隔离段进口参数 数值 Mai 2.8 T/K 700 p/kPa 51 Tt/K 1600 pt/MPa 1.49 Tf/K 300
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表 3 燃烧室出口燃烧效率和总温分布系数
Table 3. Combustion efficiency and total temperature distribution coefficient at the outlet of the combustion chamber
% 方案 ηc FOTD 1 82 31 2 65 64 3 85 26
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