Ignition and pressurization of the combustion chamber are the most critical phases of a rocket's launch. The aim of this work is to study these phenomena for a coaxial GCH4/G02 injector representative of space applications. A simulation of this transient has been performed with a commercial CFD program, CFD++, using a one-equation LES and a model of real gas. Acoustic analysis performed during the transient determines the main oscillatory modes driving the coupling between combustion and fluid dynamics. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc.
|Publication status||Published - 2005|
|Event||43rd AIAA Aerospace Sciences Meeting and Exhibit - , United States|
Duration: 1 Jan 2005 → …
|Conference||43rd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||1/1/05 → …|
All Science Journal Classification (ASJC) codes
Ciparisse, J-F., Ierardo, N., Giacomazzi, E., & Bruno, C. (2005). Ignition and pressurization transient for a coaxial GCH4/GO2 injector in supercritical conditions. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, United States.