Comptes Rendus
no. 1-2
Combustion, flow and spray dynamics for aerospace propulsion
Large-Eddy Simulation of combustion instabilities in a variable-length combustor
[Simulation aux grandes échelles des instabilités de combustion dans un brûleur de longueur variable]
Romain Garby1, 2  ; Laurent Selle1, 2 ; Thierry Poinsot1, 2
1 Institut de Mécanique des Fluides, UMR CNRS/INP-UPS 5502, Allée du Professeur Camille Soula, 31400 Toulouse, France
2 CNRS; IMFT; 31400 Toulouse, France
Comptes Rendus. Mécanique, Volume 341 (2013) no. 1-2, pp. 220-229.

Cet article présente la simulation dʼun injecteur expérimental de type moteur-fusée dont les propriétés acoustiques peuvent varier continûment grâce à un tube dʼinjection de longueur variable. Des simulations aux grandes échelles (LES) sont réalisées à lʼaide du code AVBP. Un mécanisme de stabilisation de la flamme original montrant le rôle important de la recirculation de gaz chauds en entrée de chambre est observé. Un point de fonctionnement instable est ensuite choisi pour étudier le mécanisme de lʼinstabilité. Les simulations numériques sont comparées aux mesures du banc dʼessai en termes de fréquence de lʼinstabilité et de structure du mode instable. Une simulation 2D axi-symétrique est comparée à une simulation 3D avec pour objectif de tester lʼhypothèse de symétrie pour la prédiction de lʼécoulement moyen et instationnaire de cette configuration. Bien que la description en 2D dʼun coulement turbulent soit une simplification importante, pour cette configuration et dans le cas du point de fonctionnement choisi, le calcul axi-symétrique reproduit qualitativement certaines caractéristiques de lʼinstabilité.

This article presents a simulation of a model rocket combustor with continuously variable acoustic properties thanks to a variable-length injector tube. Fully compressible Large-Eddy Simulations are conducted using the AVBP code. An original flame stabilization mechanism is uncovered where the recirculation of hot gases in the corner recirculation zone creates a triple flame structure. An unstable operating point is then chosen to investigate the mechanism of the instability. The simulations are compared to experimental results in terms of frequency and mode structure. Two-dimensional axi-symmetric computations are compared to full 3D simulations in order to assess the validity of the axi-symmetry assumption for the prediction of mean and unsteady features of this flow. Despite the inaccuracies inherent to the 2D description of a turbulent flow, for this configuration and the particular operating point investigated, the axi-symmetric simulation qualitatively reproduces some features of the instability.

Publié le :
DOI : 10.1016/j.crme.2012.10.020
Keywords: Combustion instabilities, Large-Eddy Simulation, Rocket propulsion
Mot clés : Instabilités de combustion, Simulation aux Grandes Echelles, Moteur-fusée
Romain Garby 1, 2 ; Laurent Selle 1, 2 ; Thierry Poinsot 1, 2

1 Institut de Mécanique des Fluides, UMR CNRS/INP-UPS 5502, Allée du Professeur Camille Soula, 31400 Toulouse, France
2 CNRS; IMFT; 31400 Toulouse, France 
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Romain Garby; Laurent Selle; Thierry Poinsot. Large-Eddy Simulation of combustion instabilities in a variable-length combustor. Comptes Rendus. Mécanique, Volume 341 (2013) no. 1-2, pp. 220-229. doi : 10.1016/j.crme.2012.10.020. https://comptes-rendus.academie-sciences.fr/mecanique/articles/10.1016/j.crme.2012.10.020/

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