CAJ | 학술논문

为探索旋转爆轰发动机燃烧室内气体射流冷流掺混的情况，采用高精度高分辨率迎风通量分裂格式(AUSMPW+)，求解三维欧拉方程。以环缝/小孔喷注方式的发动机模型为基础，在保证当量比不变情况下，分析了燃料喷注位置、喷注角度、单侧孔或双侧孔喷注、入口总压及出口反压对冷流掺混效果的影响。研究结果表明：随着 H2喷注位置的前移，掺混效果有明显提高；喷注角度的改变对 H2/Air 的掺混效果有很大的影响；顺喷的掺混均匀度变化幅度较大，在燃烧室的头部，顺喷的掺混效果比垂直喷注和逆喷差，在燃烧室尾部的掺混效果优于其他2种；对单侧孔或双侧孔喷注而言，双侧孔喷注方式的掺混效果明显高于单侧孔喷注方式；掺混效果与入口总压成反比，与出口反压成正比。
위탐색선전폭굉발동궤연소실내기체사류랭류참혼적정황，채용고정도고분변솔영풍통량분렬격식(AUSMPW+)，구해삼유구랍방정。이배봉/소공분주방식적발동궤모형위기출，재보증당량비불변정황하，분석료연료분주위치、분주각도、단측공혹쌍측공분주、입구총압급출구반압대랭류참혼효과적영향。연구결과표명：수착 H2분주위치적전이，참혼효과유명현제고；분주각도적개변대 H2/Air 적참혼효과유흔대적영향；순분적참혼균균도변화폭도교대，재연소실적두부，순분적참혼효과비수직분주화역분차，재연소실미부적참혼효과우우기타2충；대단측공혹쌍측공분주이언，쌍측공분주방식적참혼효과명현고우단측공분주방식；참혼효과여입구총압성반비，여출구반압성정비。
In order to research the mixing effect of the gas j et in the combustion of rotating detonation engine,three dimensional Euler equations were solved by high-resolution upwind flux split scheme(AUSMPW+).Based on an engine model with slot/hole inj ection mode,the effects of j etting parameters on mixing effectiveness were analyzed under the same equivalence ratio,such as different fuel inj ection position,inj ection angle,and unilateral or bilateral inj ection,inlet stagnation pressure and back pressure.As the injection position moves forward,the H2/Air mixing effect obviously improves.The change of the inj ection angle has a great influence on mixing effectiveness.Due to the large variations of the mixing uniformity with forward inj ection, the mixing effect in the first half of distance of the combustion chamber is worse than that of vertical inj ection and reverse inj ection,but it is better than the other two in the second half.For the inj ection method through unilateral and bilateral inj ection holes,the mixing effect of inj ection with holes from double side is significantly better than that of the unilateral inj ection.The mixing effectiveness is inversely related to inlet stagnation pressure,and it is proportional to back pres-sure.