Experimental and Numerical Investigation of Atomization in LOX/GH2-Rocket Combustors

Abstract

This paper summarizes experimental and computational results of researh on propellant mixing and combustion in high pressure LOX/GH2 rocket combustion chambers done at DLR Lampoldshausen. Hot fire tests and numerical experiments are utilized to get more detailed information about the physics of mixing and combustion under high pressure (transcritical) conditions. The identification of the relevant mechanisms and their time and length scales is necessary for the development of a straightforward model of the injecstion process. Qualitative and quantitative data about the flow field (morphology, velocity, species distribution etc.) at different boundary conditions are available and suited to test atomization and mixing models for their applicability to high pressure transcritical injection processes under hot fire conditions.