Effect of injection scheme on asymmetric phenomenon in rectangular and circular scramjets  

作　　者：Guangwei MA Mingbo SUN Guoyan ZHAO Changhai LIANG Hongbo WANG Jiangfei YU 

机构地区：[1]Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China

出　　处：《Chinese Journal of Aeronautics》2023年第1期216-230,共15页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.11925207,12002381);the Scientific Research Plan of National University of Defense Technology in 2019,China(No.ZK19-02);the Postgraduate Scientific Research Innovation Project of Hunan Province,China(No.CX20200084);the Equipment Pre-research Foundation of Key Laboratory,China(No.6142703200311)。

摘　　要：The asymmetric separation has a crucial effect on the performance of the scramjet.In this study,the asymmetric separation and combustion in both rectangular and circular scramjets are investigated numerically,and the effect of injection scheme is analyzed.The characteristics of the flow field are analyzed based on sufficient code verification.In the rectangular scramjet,the separation tends to occur in the corner due to the corner boundary-layer effect.The separation is asym-metric and only two corners have serious separation.The fuel penetration depth in the separation zone increases and the combustion is intensified.When the injection scheme is uniform,both the combustion and separation become weak.In the circular scramjet,the separation and combustion are basically axisymmetric in the scramjet with one-row injection scheme.The asymmetric combustion becomes obvious in cases with multi-row injection scheme.When the injection orifices distribute intensively on the top and bottom sides,the strongest and weakest separations occur near these two sides respectively.When the distribution of orifices becomes uniform,the direction of separation cannot be predicted.For multi-row cases,the nonuniform injection scheme could result in violent combustion and asymmetric flow structures compared with the uniform injection scheme.

关 键 词：Asymmetric phenomenon CAVITY Combustion Injection scheme SCRAMJET SUPERSONIC 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]