Study on heat transfer of combustor and regenerative cooling channel based on two-way coupling
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摘要:
为研究超燃冲压发动机燃烧室与再生冷却通道的耦合传热特性，采用双向弱耦合迭代计算方法，研究燃烧室和冷却通道的特征参数对耦合传热特性的影响规律。结果表明：当量比的增加导致燃烧反应区域和壁面高温区域后移，当量比增大至0.75时，部分壁面高温区后移至超出燃烧段范围，在燃烧室的当量比设计时需考虑冷却通道范围的限制；喷射角度的增大会提高燃烧段壁面平均温度，喷射角度由30°增大到75°时，冷却通道出口裂解率由8%增长到11%；增大冷却剂的工作压力和流量能增强冷却剂的吸热能力，降低燃烧室内壁面温度，最大下降幅度约200 K。
Abstract:In order to investigate the heat transfer characteristics of regenerative cooling channels and scramjet combustors, a two-way weak-coupling iterative calculation method is adopted. The combustor settings and cooling channel impacts on heat transfer and N-decane pyrolysis were studied numerically using this information. The findings indicate that the burning region and the high-temperature area will move rearward when the equivalency ratio increases. When the equivalence ratio reaches 0.75, part of the high-temperature zone moves out of the combustion section and the cooling channel cannot effectively cool the combustor. Therefore, the limitation of cooling channel should be considered in the design of equivalence ratio of the combustor. Moreover, a larger fuel injection angle leads to an ascent of the average temperature of the wall. The cracking rate at the outlet of the cooling channel increases from 8% to 11% as the injection angle increases from 30° to 75°. The combustor's temperature can drop by up to 200 K as a result of improving the coolant's heat absorption capacity through increased operating pressure in the cooling channel and coolant flow.
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Key words:
- scramjet /
- combustor /
- regenerative cooling /
- coupling heat transfer /
- numerical study
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图 4 耦合换热结构简化模型示意图
Figure 4. Schematic diagram of simplified model of coupled heat transfer structure
图 8 平均流速和正癸烷质量分数计算结果与实验结果
Figure 8. Calculated results of average velocity of flow and mass fraction of N-decane with experimental data
图 9 静压计算结果与实验结果
Figure 9. Calculated results of static pressure with experimental data
图 10 气相燃烧温度计算结果与实验结果
Figure 10. Calculated results of temperature with experimental data for gaseous combustion
图 11 壁面温度和热流密度随迭代次数变化
Figure 11. Temperature and heat flux of walls vary with number of iterations
图 12 冷却通道中心截面正癸烷质量分数
Figure 12. Mass fraction of N-decane of central section in cooling channel
图 13 不同当量比下正癸烷质量分数随剖面位置变化
Figure 13. Mass fraction of N-decane varies with position of section under different equivalence ratios
图 14 燃烧室中心截面静压和密度分布
Figure 14. Static pressure and density distribution in central section of combustor
图 15 不同当量比下燃烧段内壁面温度分布
Figure 15. Temperature distribution of combustion section inner wall with different equivalence ratios
图 16 不同当量比冷却通道中心截面正癸烷质量分数分布
Figure 16. Mass fraction distribution of N-decane of central section in cooling channel with different equivalence ratios
图 17 不同当量比下正癸烷截面平均质量分数分布
Figure 17. Average mass fraction distribution of N-decane with different equivalence ratios
图 18 不同喷射角度下正癸烷质量分数随剖面位置变化
Figure 18. Mass fraction of N-decane varies with position of section under different spray angles
图 19 不同喷射角下燃烧段内壁面温度
Figure 19. Temperature of inner wall surface in combustion section with different injection angles
图 20 不同喷射角下正癸烷截面平均质量分数
Figure 20. Average mass fraction of N-decane cross-section with different injection angles
图 21 不同压力下燃烧室和冷却通道内壁面平均温度及热流密度
Figure 21. Average temperature and heat flux density of combustor and cooling channel inner wall under different pressures
图 22 不同压力下正癸烷导温系数随温度变化
Figure 22. Variable temperature dependence of thermal diffusivity of N-decane under different pressures
图 23 不同压力下正癸烷截面平均质量分数分布
Figure 23. Average mass fraction distribution of N-decane under different pressures
图 24 不同压力下燃烧室沿程截面平均总温相对变化
Figure 24. Variation of average total temperature along cross-section of combustor under different pressures
图 25 燃烧室和冷却通道内壁面平均温度及热流密度随冷却流量变化
Figure 25. Average temperature and heat flux of combustor and cooling channel inner wall varies with coolant flow rate
图 26 不同冷却流量下冷却通道沿程平均温度分布
Figure 26. Average temperature distribution along cooling channel under different coolant flow rates
图 27 不同冷却流量下正癸烷平均质量分数
Figure 27. Average mass fraction of N-decane distribution with different coolant flow rates
图 28 不同冷却流量下燃烧室沿程平均总温相对变化
Figure 28. Variation of average total temperature along combustor under different coolant flow rates
表 1 燃烧室和冷却通道边界条件
Table 1. Boundary conditions of combustor and cooling channel
工况 当量比 喷射角度/(°) 冷却通道压力/MPa 冷却剂流量/(kg·s−1) 1 0.15，0.35，0.55，0.75 90 3 0.045 2 0.15 30，45，60，75 3 0.045 3 0.7 90 3，4，5，6 0.045 4 1 90 3 0.035，0.045，0.055，0.065 
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表 2 冷却通道出口温度和正癸烷质量分数
Table 2. The temperature and N-decane mass fraction of cooling channel outlet
耦合方式 平均温度/K 正癸烷质量分数 单向耦合 544.93 0.919 8 双向耦合 558.69 0.891 3
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