考虑热力学非平衡效应的高马赫数超燃冲压发动机湍流燃烧数值研究  

Numerical study on turbulent combustion in high Mach number scramjet engine considering thermal non-equilibrium effect

作　　者：冯海 金台 吴坤 FENG Hai;JIN Tai;WU Kun(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China;Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]浙江大学航空航天学院,杭州310027 [2]中国科学院力学研究所,北京100190

出　　处：《实验流体力学》2025年第1期30-37,共8页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金项目(52076194);中央高校基本科研业务费专项资金项目(2021FZZX001–11);浙江省自然科学基金杰出青年基金项目(LR24E060001)。

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Ma=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Ttr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。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 scramjet engine.The turbulent combustion in the scramjet 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.

关 键 词：高超声速 热力学非平衡 超燃冲压发动机 波系结构 燃烧效率 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]