实验流体力学2025，Vol.39Issue(1)：30-37,8.DOI:10.11729/syltlx20230158
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
摘要
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 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Key words
hypersonic/thermodynamic non-equilibrium/scramjet/shock wave structure/combustion efficiency/numerical simulation分类
航空航天引用本文复制引用
冯海,金台,吴坤..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[J].实验流体力学,2025,39(1):30-37,8.基金项目
国家自然科学基金项目(52076194) （52076194）
中央高校基本科研业务费专项资金项目(2021FZZX001-11) （2021FZZX001-11）
浙江省自然科学基金杰出青年基金项目(LR24E060001) （LR24E060001）
