火箭出口面积对RBCC发动机引射模态影响规律分析  

Analysis of the influence of rocket exit area in RBCC engine under the ejector mode

作　　者：姚轶智 孙明波[1] 黄玉辉 李佩波[1] 安彬 顾瑞[3] 王教儒 李梦磊 王泰宇 陈纪凯 YAO Yizhi;SUN Mingbo;HUANG Yuhui;LI Peibo;AN Bin;GU Rui;WANG Jiaoru;LI Menglei;WANG Taiyu;CHEN Jikai(Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Center for Project Management of Equipment Development Department,Beijing 110000,China;The PLA Unit 94710,Wuxi 214141,China)

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙410073 [2]装备发展部装备项目管理中心,北京110000 [3]中国人民解放军94710部队,江苏无锡214141

出　　处：《国防科技大学学报》2023年第2期155-163,共9页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(11925207)。

摘　　要：火箭基组合循环发动机引射模态飞行状态复杂,为了提高发动机的整体性能,研究了火箭出口面积对发动机引射模态的影响规律。通过数值模拟研究,引射流量在低飞行马赫数条件下,主要受引射性能影响,火箭出口面积越大,引射性能越好。然而,随着飞行马赫数的提升,引射空气的动能提升,隔离段内出现壅塞情况,引射流量主要受限于隔离段几何尺寸,与火箭出口面积无关。在亚声速工况下,火箭出口面积越小,发动机比冲越低,且出口无量纲面积为3.15时,火箭羽流膨胀撞壁,会引起性能骤减,需要予以避免;在超声速工况下,选择面积较小的火箭出口面积,燃烧室内压越高,发动机性能提升越明显。In order to improve the performance of the rocket-based combined-cycle engine,the influence of the rocket exit area under the ejector mode was studied.Through numerical simulation research,the mass flow of captured air was mainly affected by the entrainment performance under the condition of low flight Mach number.The larger the rocket exit area,the better the entrainment performance.However,with the increase of flight Mach number,the kinetic energy of the entrainment air increases,and there is flow choking in the isolator.The mass flow of captured air was mainly limited by the geometric size of the isolator,independent of the rocket exit area.Under subsonic conditions,the smaller the rocket exit area is,the lower the specific impulse of the engine is,and when the exit dimensionless area is 3.15,the rocket plume will expand and impact the wall,which can cause a sudden reduction in performance.Under supersonic conditions,the smaller the rocket exit area,the higher pressure in the combustor,and the better performance of the rocket-based combined cycle engine.

关 键 词：火箭基组合循环 引射模态 火箭出口面积 比冲 引射性能 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]