les of kerosene spray combustion in rbcc ramjet/scramjet mode
- Paper number
IAC-09.C4.8.2
- Author
Mr. Man Zhang, China
- Coauthor
Prof. Guoqiang He, Northwestern Polytechnical University, China
- Year
2009
- Abstract
RBCC (Rocket Based Combined Cycle) is an advanced propulsion system concept proposed in the 1960’s. The concept combines advantages of both the conventional rocket and the air-breathing motor to form a multi-working mode (including rocket ejector, ramjet, scramjet and pure rocket). It is generally believed that after the flight Mach number surpassing 3, RBCC combustion chamber works in ramjet or scramjet mode. Therefore, it will be the precondition for successfully operating RBCC ramjet/scramjet mode to ensure stabilized and efficient combustion in hypersonic flow. Furthermore, in order to achieve high Thrust-Weight Ratio (TWR), aircraft usually carries liquid fuels. Unlike gaseous fuel burning directly after injection, liquid fuel must undergo atomization (including the primary atomization and the secondary aerodynamic atomization) and evaporation processes first, which increases the difficulty of the combustion control. As the mechanism of spray combustion in hypersonic flow is complex, studies of ram-jet/scramjet combustion process were usually conducted on the ground-based experiments. In recent years, development of CFD calculation method and widely application of high-performance parallel computer provide a reliable tool for the accurate numerical simulation of hypersonic turbulent combustion. The progress of numerical simulation of hypersonic spray combustion has been mainly constrained by the two-phase model, chemical dynamics, and computer resource. In order to obtain the precise and accurate distribution of the turbulent flame, time-accurate numerical simulations, such as direct numerical simulation (DNS), large-eddy simulation (LES) and detached-eddy simulation (DES), are carried out to solve the flow governing equations. And, in liquid-gas coupling calculation, atomization and evaporation process of the liquid fuel will influence the combustion response time significantly. For the medium discrete phase numerical terms in two-phase flow, Euler-Lagrangian particle tracking method is widely used. This method is based on the classical mechanics of Newton's law to carry out a droplet stress analysis, thus to calculate the trajectory of droplets. The combustion kinetic process is usually described by the models established by Westbrook\& Dryer. LES is used to investigate the multi-phases combustion performance in a generic geometry. Comparison of numerical results with experimental data indicated that high resolution numerical methods gave better description of the turbulent flow-dynamics. And，for kerosene spray combustion in ramjet mode of RBCC, the evaporation process may complete very quickly in high temperature region.
- Abstract document
- Manuscript document
IAC-09.C4.8.2.pdf (🔒 authorized access only).
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