RBCC在模态转换过程中的内流场特性  

Research on internal flow field characteristics of RBCC during mode transition

作　　者：李梦磊 杨雪[2] 杨一言 李佩波[1] 石磊[2] LI Menglei;YANG Xue;YANG Yiyan;LI Peibo;SHI Lei(School of Aerospace Sciences,National University of Defense Technology,Changsha 410073,China;Science and Technology on Combustion,Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]国防科技大学空天科学学院,湖南长沙410073 [2]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《火箭推进》2021年第6期39-45,共7页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51976171)。

摘　　要：为了获得火箭基组合循环(RBCC)发动机在模态转换过程中的工作特性,对基于宽调节比火箭的引射-亚燃模态转换过程中流场进行数值仿真计算。研究了特定几何构型的RBCC隔离段和后段燃烧室在火箭射流和背压综合影响下的波系结构和参数分布规律。研究表明:在火箭射流和背压调节综合作用下,流场可分为主流区、背压影响区和火箭射流影响区,主流会在燃烧室下壁面发生流动分离或气体回流,这恰好为稳定燃烧提供了物理条件;模态转换中,火箭调至小流量工作状态最有利于维持流场参数的稳定,此时特征点处的压力和马赫数值的最大方差仅为0.087和0.003,最大波动幅度为27.44%和8.29%。In order to obtain the working characteristics of RBCC(rocket-based combined cycle)engine in the process of model transition,the numerical simulation of the flow field in the process of ejector-ramjet mode transition based on wide adjustment ratio rocket was carried out.The wave system structure and parameter distribution of RBCC isolator and rear combustor with specific geometry under the combined influence of rocket jet and back pressure were studied.Results show that affected by the rocket jet and back pressure,the flow field can be divided into three areas:the mainstream area,the back pressure influence area and the rocket jet influence area.Mainstream flow separation or gas recirculation occurs on the lower wall of combustor,which provides physical conditions for stable combustion.In the process of mode transition,it is most beneficial to maintain the stability of the flow field parameters by adjusting the rocket to a small flow state.At this point,the maximum variances of the pressure and mach number at the feature point are only 0.087 and 0.003 respectively,and the maximum volatility are 27.44%and 8.29%respectively.

关 键 词：火箭基组合循环发动机 引射/亚燃模态 数值模拟 分离涡模拟 调控 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]