Numerical analysis of Raptor engine's combustion chamber
Simulation numérique de la combustion du moteur fusée Raptor de SpaceX.
Résumé
In the present work, SpaceX’s Raptor engine combustion chamber has been investigated numerically to precisely understand the flow dynamics and variation of properties such as pressure, temperature and velocity distribution within the combustion chamber. The numerical results were compared to Raptor specifications, demonstrating a strong correspondence. This study shows that improving the correspondence between numerical results and Raptor technical specifications is possible by taking into account the influence of preburners on fuel and oxidizer inlet compositions. In this study, influence of equivalence ratio on engine performance has also been investigated. It has been shown that moving the equivalence ratio from 1.1 to 1.4 can improve engine performance by 5% but it also results in a 5% increase in pressure within the combustion chamber.
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