4 March 2015 Study on numerical simulation of flowfield in afterburner for ducted rocket
Author Affiliations +
Proceedings Volume 9521, Selected Papers from Conferences of the Photoelectronic Technology Committee of the Chinese Society of Astronautics 2014, Part I; 95211K (2015) https://doi.org/10.1117/12.2178241
Event: Selected Proceedings of the Photoelectronic Technology Committee Conferences held August-October 2014, 2014, China, China
Abstract
Ducted rocket has been widely concerned on account of its high specific impulse, combustion stability and convenient maintenance which mixes the exhaust from a fuel gas generator with air from air inlet, and burns to produce thrust. It is necessary to establish two-dimensional or three-dimensional numerical models based on computational fluid dynamics to study on the flowfield in afterburner which is the key of ducted rocket because of expensive experiments, which is aimed at providing theoretical foundation for ducted rocket’s development. In this paper, the gas-phase turbulent combustion process in afterburner with dual inlet three-dimensional mode was simulated numerically by solving Favre-averaged compressible turbulent N-S equations, the renormalization group (RNG) k-ε turbulence model was applied to simulate the turbulent flow, and Eddy-Dissipation Model (EDM) was applied to simulate gas combustion. Through simulation, situation analysis of flowfield in afterburner was done, and the influence of mixing combustion on afterburner was studied by taking air inlet angles and air-fuel ratio into account respectively. The results indicate that the distribution of temperature in afterburner is nonuniform, the backflow and axial swirl produced by gas mixing have an important influence on afterburner combustion. As air inlet angle is increased, the intensity of gas mixing is enhanced which is beneficial for afterburner combustion. That increasing air-fuel ratio is able to strength contact of oxygen with fuel gas, so that more fuel gas is consumed in the same location which is more beneficial for afterburner combustion.
© (2015) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Xiaoyu Ding, Xiaoyu Ding, Xing Jin, Xing Jin, Peng Zhang, Peng Zhang, } "Study on numerical simulation of flowfield in afterburner for ducted rocket", Proc. SPIE 9521, Selected Papers from Conferences of the Photoelectronic Technology Committee of the Chinese Society of Astronautics 2014, Part I, 95211K (4 March 2015); doi: 10.1117/12.2178241; https://doi.org/10.1117/12.2178241
PROCEEDINGS
7 PAGES


SHARE
Back to Top