Numerical study on turbulent combustion in high Mach number scram-jet engine considering thermal non-equilibrium effect
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摘要: 高超声速飞行过程中，随着马赫数升高，边界层内温度快速上升，分子振动能、电子能被激发，气体分子发生离解甚至电离，使得量热完全气体假设失效。针对高温热化学非平衡气体，采用热力学平衡模型及Park的双温度非平衡模型对飞行马赫数12条件下的超燃冲压发动机进行了数值模拟。研究结果表明：与平衡态计算结果相比，非平衡效应使得波系位置前移，激波间峰值压力升高，对冷场的影响更加明显；非平衡态平动温度场与平衡态差别不大，热力学非平衡效应使平动温度略微升高；非平衡态燃烧室出口截面燃烧效率更低，热力学非平衡效应会降低反应程度。Abstract: During hypersonic flight, the temperature inside the boundary layer rapidly increases with the increase of Mach number, leading to the excitation of molecular vibration and electron energy. Gaseous molecules undergo dissociation or even ionization, making the assumption of complete gas calorimetry invalid, and thereby affecting the characteristics of the scram-jet engine. The turbulent combustion in the scram-jet engine under the Ma 12 flight condition is numerically studied via a thermodynamic equilibrium model and the Park's dual temperature non-equilibrium model where the high-temperature thermal non-equilibrium effects are considered. The results indicate that compared to the equilibrium case, the non-equilibrium effect causes the position of the shock wave trains to shift forward, and the increase of the peak pressure between shock waves. This is more significant for the frozen flow field. The temperature field Ttr in the non-equilibrium case is not significantly different from that of the equilibrium case, and the thermodynamic non-equilibrium effect slightly increases Ttr. The combustion efficiency at the outlet section is lower in the non-equilibrium case, and the thermodynamic non-equilibrium effect slightly weakens the intensity of the reactions.
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图 4 计算域中间截面底壁压力与文献对比
Figure 4. Comparison of pressure on the bottom wall in the central plane of the computational domain with literature
图 5 计算域中间截面底壁上的压力
Figure 5. Pressure on the bottom wall of the central plane in the computational domain
图 10 波系结构对比，冷场（上）和反应场（下）
Figure 10. Comparison of shock wave structures, frozen (top) and reacting (bottom) field
图 11 中心截面底壁压力对比
Figure 11. Comparison of pressure close to bottom wall in the central plane
图 12 平动温度对比，冻结流（上）和反应流（下）
Figure 12. Comparison of trans-rotational temperature, frozen (top) and reacting (bottom) field
图 13 燃烧室出口截面的燃烧效率
Figure 13. Combustion efficiency at the exit section of the combustor
表 1 组分特征振动温度
Table 1. The characteristic vibrational temperature of the species
组分 θv,s/K N2 3371 O2 2256 H2 6215 H2O 2294、5180、5400 OH 5375 HO2 1577、2059 H2O2 1250、1970、2030、2070、4130、4910 
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表 2 空气和燃料边界条件
Table 2. Boundary conditions for air and fuel stream
马赫数Ma 流速u∞/(m·s−1) 静压p∞/Pa 平动温度Ttr/K 空气入口 10 3000 1450 227 燃料入口 1 1208 541778 249
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