RBCC发动机引射模态进气道特性研究  

Investigation of RBCC engine ejector mode inlet characteristics

作　　者：刘晓伟[1] 石磊[1] 刘佩进[1] 何国强[1] LIU Xiao-wei SHI Lei LIU Pei-jin HE Guo-qiang(College of Astronautics, Northwestern Polytechnical University, Xi＇an 710072, China)

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2016年第5期601-605,611,共6页Journal of Solid Rocket Technology

摘　　要：为了研究RBCC发动机引射模态的进气道特性,基于二元混压式进气道,建立了二维RBCC发动机流道构型。利用数值模拟获得不同来流马赫数和主火箭流量时发动机的流场结构和进气道性能。研究发现,不同来流马赫数时,发动机流动特征和进气道特性差异较大,可划分为几个典型区间。只有在低亚声速区间,火箭引射才可影响发动机的进气道性能。来流马赫数和进气道喉道面积是影响RBCC发动机引射模态进气道性能的主要因素,发动机设计时,应尽可能增大进气道的喉道面积。In order to study RBCC engine ejector mode inlet characteristics, a 2D RBCC engine configuration was established based on a 2D mixed pressure inlet. Inlet performance and flow field of RBCC engine were obtained by numerical simulation, with different entrance Mach numbers and RBCC rocket fluxes. Results show that the flow field and the inlet character are different at four typical entrance Mach number intervals. The inlet character could be influenced by the RBCC rocket only during the low sub- sonic interval. The influence of inlet throat area on the inlet character is evident, and inlet throat area should be enlarged as far as possible during RBCC engine design.

关 键 词：RBCC发动机 引射模态 进气道 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]