3D miles simulation of a hybrid rocket with SWIRL injection
| Autor: | Messineo, Jérôme, Lestrade, Jean-Yves, Hijlkema, Jouke, Anthoine, Jérôme |
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| Přispěvatelé: | ONERA - The French Aerospace Lab [Mauzac], ONERA, André, Cécile |
| Jazyk: | angličtina |
| Rok vydání: | 2016 |
| Předmět: |
INJECTION TOURBILLONNAIRE COMBURANT
MOTEUR FUSEE HYBRIDE EFFICACITE COMBUSTION OSCILLATION PRESSION SIMULATION NUMERIQUE 3D [SPI.MECA.MEFL] Engineering Sciences [physics]/Mechanics [physics.med-ph]/Fluids mechanics [physics.class-ph] [SPI.MECA.MEFL]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Fluids mechanics [physics.class-ph] |
| Zdroj: | Space Propulsion 2016 Space Propulsion 2016, May 2016, ROME, Italy |
| Popis: | International audience; Oxidizer injection plays a major role in the behaviour of hybrid rocket engines, especially regarding combustion efficiency and stability. This study aims to compare two firing tests with associated numerical simulations based on gaseous oxidizer axial or swirl injection through a catalyzer. The oxidizer and fuel couple used was H2O2 (87.5 %)/HDPE. Numerical 3D MILES (Monotone Integrated Large Eddy Simulation) simulations of both configurations were performed and analyzed regarding on one side the combustion efficiency influenced by propellants mixing, and on the other side the pressure oscillations provoked by the formation of large scale vortices in the aft-combustion chamber. |
| Databáze: | OpenAIRE |
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