A numerical platform that is being developed for the simulation of high pressure combustion in liquid rocket engines is described in this paper. It will be able to solve Navier Stokes equations with non-equilibrium chemistry for generic mixtures with both Reynolds-average and Large Eddy Simulation methods. Real gas model was implemented to deal with high pressure gases in supercritical regime. Combustion is treated solving Arrhenius approach or Eddy Dissipation Model formulation. Several classical test cases were performed for both solvers; the RANS code exhibits a reasonable accuracy, that will be improved with more advanced modelling that is being developed. The LES code was tested so far only with cold test cases, showing very good accuracy and performances.
Development and validation of numerical solvers for the analysis of high-pressure combustion in liquid rocket engines / A., Schettino; L., Cutrone; S., Di Benedetto; Capuano, Francesco; A., Mastellone; G., Saccone; G., Di Lorenzo. - (2015). (Intervento presentato al convegno 8th European Symposium on Aerothermodynamics for Space Vehicles tenutosi a Lisbona nel 2-6 Marzo 2015).
Development and validation of numerical solvers for the analysis of high-pressure combustion in liquid rocket engines
CAPUANO, FRANCESCO;
2015
Abstract
A numerical platform that is being developed for the simulation of high pressure combustion in liquid rocket engines is described in this paper. It will be able to solve Navier Stokes equations with non-equilibrium chemistry for generic mixtures with both Reynolds-average and Large Eddy Simulation methods. Real gas model was implemented to deal with high pressure gases in supercritical regime. Combustion is treated solving Arrhenius approach or Eddy Dissipation Model formulation. Several classical test cases were performed for both solvers; the RANS code exhibits a reasonable accuracy, that will be improved with more advanced modelling that is being developed. The LES code was tested so far only with cold test cases, showing very good accuracy and performances.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
