Abstract : This work taking place in the framework of the Research Group « Combustion in Rocket Engines » joining CNES, CNRS, ONERA and SNECMA concerns the study of secondary atomization and turbulent vaporization in spray combustion. The main goal of this study is to provide reliable models for computational codes, reproducing accurately the elementary processes in cryogenic combustion for rocket engines.
These models are taken from previous experimental studies at LCSR, which have permitted to establish databases.
The numerical computations are mainly based on the simulation of the ONERA's MASCOTTE (Montage Autonome Simplifié pour la Cryocombustion dans l'Oxygène et Toutes Techniques Expérimentales) test bench. The results highlight first, the influence of droplet breakup on spray and flame structures. Second, computations considering turbulent vaporization, highlight the influence of turbulence on drop properties.