Thermodynamic performance modeling,optimization and numerical simulation of RBCC ejector mode  

作　　者：Feiteng Luo Zhenming Qu Yaosong Long Wenjuan Chen Jinli Hou Baoxi Wei 

机构地区：[1]School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhan 430074,China [2]Science and Technology of Scramjet Laboratory,Beijing Power Machinery Research Institute,Beijing 100074,China

出　　处：《Propulsion and Power Research》2024年第2期207-232,共26页推进与动力（英文）

基　　金：supported by the National Natural Science Foundation of China (Grant No.52076094).

摘　　要：Ejector mode is a unique and critical phase of wide-range rocket-based combined cycle(RBCC)engine.In this paper,a quasi-one-dimensional thermodynamic performance modeling method,with more detailed model treatments for the inlet-diffuser system,pri-mary/secondaryflow interaction,and pressure feedback matching,was developed for operating characteristics studies and multi-objective optimization analysis of the ejector mode of an actual RBCC engine.A series of three-dimensional simulations of separate inlet and fullflowpath was completed to validate the modeling study and provide further insight into the operating charac-teristics.The primary/secondary equilibrium pressure ratio functions a significant effect on ejector mode performance,a higher performance augmentation can be obtained by lower rocket pressure ratio,larger mixing section area ratio,smaller throttling throat and higher equivalence ratio,within an appropriate range.The positive performance augmentation can be realized at lowflight Mach conditions,the coordination and trade-off relationships between specific im-pulse,performance augmentation ratio and thrust-to-area ratio during ejector mode are present by the Pareto-front from MOP analysis.It is further verified by CFD simulation that,the operating back-pressure at the exit of inlet-diffuser system functions a decisive influence on the airbreathing characteristics,the pressure feedback and matching should be well-controlled for secondaryflowrate and performance augmentation.The thermodynamic modeling analysis re-sults are basically consistent with those of numerical simulation,to validate the rationality and effectiveness of the modeling method.

关 键 词：Rocket-based combined cycle(RBCC) Ejector mode Performance modeling OPTIMIZATION Numerical simulation 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]