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Numerical Simulation of Al/Mg Propellant Combustion Flow in Secondary Combustion Chamber for Ramjet Assisted Range Projectile

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2011年03期
Page:
359-364
Research Field:
Publishing date:

Info

Title:
Numerical Simulation of Al/Mg Propellant Combustion Flow in Secondary Combustion Chamber for Ramjet Assisted Range Projectile
Author(s):
ZHANG LeiZHOU Chang-shengJU Yu-taoHU Zhi-gang
School of Mechanical Engineering,NUST,Nanjing 210094,China
Keywords:
ramjet assisted range projectiles.TIF Secondary combustion chamber Al/Mg propellants flow numerical simulation
PACS:
V430
DOI:
-
Abstract:
To research the effects of Mg on the combustion in secondary combustion chamber,the Al/Mg propellant combustion flow in secondary combustion chamber for the ramjet assisted range projectile is three-dimensionally and numerically simulated by using the probability density function(PDF) model and particle trajectory model.Al particle combustion is controlled by a diffusion-vaporization model.The turbulent model is a stand k-ε two-equation model.Considering the effects of Mg mass fraction and Al particles diameter,the trends of engine parameters such as resultant species and temperature are obtained.The results indicate that two diffusion flame peaks are at the entrance of secondary combustion chamber,and they are mixed into a diffusion flame peak in the middle of secondary combustion chamber.The combustion efficiency of Al particles increases from 15% to 35% when the Mg mass fraction increases from 0% to 15%.With the same Mg mass fraction,the combustion efficiency of Al particles decreases with the increase of Al particle diameters.

References:

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Last Update: 2012-06-30