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Abstract

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.

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