Film cooling as a thermal protection for the walls of liquid rocket engines is studied numerically for hydrogen and methane thrust chamber tests. The aim is to verify the capability of the Reynolds Average Navier-Stokes model to capture the basic characteristics of film-cooled thrust chambers, considering a simplified approach, named pseudo-injector approach, which does not model propellant injection and combustion. This assumption allows a great saving in computational time, in particular when considering 3D simulations. The present study takes its origin from the European Community In-Space Propulsion 1 (ISP-1) program where, among various projects, an experimental campaign has been designed to study the film cooling technique in an oxygen/methane thrust chamber and to provide a database for computational fluid dynamics validation. The results show that the present approach gives good results in terms of heat flux characterization, in particular when dealing with test cases of high chamber pressure. © 2012 by B. Betti, E. Martelli, F. Nasuti, M. Onofri.
Numerical study of heat transfer in film cooled thrust chambers / Betti, Barbara; Emanuele, Martelli; Nasuti, Francesco; Onofri, Marcello. - STAMPA. - 3:(2012), pp. 2002-2016. (Intervento presentato al convegno 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 tenutosi a Atlanta, GA nel 30 July 2012 through 1 August 2012) [10.2514/6.2012-3907].
Numerical study of heat transfer in film cooled thrust chambers
BETTI, BARBARA;NASUTI, Francesco;ONOFRI, Marcello
2012
Abstract
Film cooling as a thermal protection for the walls of liquid rocket engines is studied numerically for hydrogen and methane thrust chamber tests. The aim is to verify the capability of the Reynolds Average Navier-Stokes model to capture the basic characteristics of film-cooled thrust chambers, considering a simplified approach, named pseudo-injector approach, which does not model propellant injection and combustion. This assumption allows a great saving in computational time, in particular when considering 3D simulations. The present study takes its origin from the European Community In-Space Propulsion 1 (ISP-1) program where, among various projects, an experimental campaign has been designed to study the film cooling technique in an oxygen/methane thrust chamber and to provide a database for computational fluid dynamics validation. The results show that the present approach gives good results in terms of heat flux characterization, in particular when dealing with test cases of high chamber pressure. © 2012 by B. Betti, E. Martelli, F. Nasuti, M. Onofri.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.