The objective of this research is to probe further into the propulsion applications of a bidirectional swirl chamber by simulating the combustive vortex flows inside multiple configurations of liquid rocket engines. The present work initially tested the combustion inside a two-dimensional, axisymmetric combustion chamber to validate the computational methods. Three-dimensional geometries were then modeled and tested based on the swirl chamber concept. ANSYS FLUENT was used to simulate the flow region numerically. A viscous, turbulent, non-premixed combustion model with radiation at steady state was adopted. The results were justified by making qualitative comparisons to previous research conducted by other investigators.
Numa, Nadia M.
"Computational Analyses of Combustive Vortex Flows in Liquid Rocket Engines,"
McNair Scholars Research Journal: Vol. 2
, Article 2.
Available at: http://commons.erau.edu/mcnair/vol2/iss1/2