Mixing and combustion characteristics in a scramjet combustor with different distances between cavity and backward-facing step  

作　　者：Mingjiang LIU Mingbo SUN Daoning YANG Guoyan ZHAO Tao TANG Bin AN Hongbo WANG 

机构地区：[1]Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China [2]Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China

出　　处：《Chinese Journal of Aeronautics》2023年第7期400-411,共12页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.11925207 and 12002381);the Scientific Research Plan of the National University of Defense Technology in 2019,China(No.ZK19-02);the Science and Technology Foundation of State Key Laboratory,China(No.6142703200311).

摘　　要：The mixing and combustion characteristics in a cavity flameholding combustor under inlet Mach number 2.92 are numerically investigated with ethylene injection.Dimensionless distance is defined as the ratio of the actual distance to the height of the combustor entrance.The cavity shear-layer mode,the lifted cavity shear-layer mode,and jet wake mode with upstream separation are observed respectively with dimensionless distance equals to 1.5,4.5,and 7.5.In both non-reacting and reacting flow fields,the numerical results are essentially in agreement with the schlieren photography,flame chemiluminescence images,and wall pressure,which verify the reliability of the numerical method.The results of non-reacting flow fields show that the BackwardFacing Step(BFS)can promote the flow separation downstream at a fixed distance.The more forward the separation position is,the larger the separation zone is in the non-reacting flow field.Furthermore,the larger the separation zone is,the higher the intensity of combustion in the reacting flow field is.A reasonable distance can reduce the total pressure loss generated by the shock waves in the combustor.The flame presents remarkable three-dimensional characteristics in the reacting flow fields.When dimensionless distance equals to 4.5,there are flames near the side wall above the cavity and it is difficult for the flame stabilization in the center of the combustor,while the combustion intensity in the center of the combustor is higher than that near the side wall when dimensionless distance equals to 7.5.In the cavity flameholding combustors with a backward-facing step,the higher combustion intensity may bring much total pressure loss to the combustor.Thus,it is a good choice to achieve better thrust performance when dimensionless distance equals to 4.5 compared to the other two combustors.

关 键 词：Backward-facing step CAVITY COMBUSTION Scramjet combustor Supersonic flow 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]