Numerical Simulation of Vortex Cold-wall Rocket Combustor

SUN  Dechuan; BAI  Rongbo; LIU  Shang

doi:10.15892/j.cnki.djzdxb.2011.02.030

Journal of Projectiles, Rockets, Missiles and Guidance >

2011 , Vol. 31 >Issue 2: 111 - 113,116

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.02.030

ROCKETS TECHNOLOGY

Numerical Simulation of Vortex Cold-wall Rocket Combustor

SUN Dechuan ,
BAI Rongbo ,
LIU Shang

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National Key Laboratory of Combustion, Flow and Thermo-structure, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2010-09-25

Online published: 2025-05-30

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Abstract

In order to study the flow field of vortex cold-wall rocket combustor, two turbulent models were used and compared by using CFD software, RSM turbulent models can simulate the pressure distribution, swirl velocity and bidirectional vortex very well. The Rankine vortex structure was obtained through numerical simulation. The results show that the calculation results even more agree better real combustor than the theoretical model, and the 3-D effect is apparent in the free vortex but smaller in the forced vortex and will not influence the structure of bidirectional vortexes.

Key words： vortex cold-wall combustor; bidirectional vortexes; numerical simulation; RSM model

Cite this article

SUN Dechuan , BAI Rongbo , LIU Shang . Numerical Simulation of Vortex Cold-wall Rocket Combustor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011 , 31(2) : 111 -113,116 . DOI: 10.15892/j.cnki.djzdxb.2011.02.030

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