The demand of a more comprehensive engineering tool for parametric investigations of rocket thrust chambers thermal environment is pushing the improvement of hot-gas side heat transfer prediction tools. In this work, the capability of predicting the heat transfer characteristics of a literature test case for a liquid oxygen / gaseous methane single element combustion chamber is assessed by means of 2D axis-symmetric Reynolds-Averaged Navier-Stokes simulations. A simplied approach is proposed, where combustion is not simulated, but combustion products enter the chamber through a pseudo-injector. The numerical results show a good agreement with the experimental data, except in the near injection region.
Heat Flux Evaluation in Oxygen/Methane Thrust Chambers by RANS Approach / Betti, Barbara; E., Martelli; Nasuti, Francesco. - ELETTRONICO. - (2010), pp. 1-9. (Intervento presentato al convegno 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit tenutosi a Nashville, TN, USA nel 25 - 28 luglio 2010).
Heat Flux Evaluation in Oxygen/Methane Thrust Chambers by RANS Approach
BETTI, BARBARA;NASUTI, Francesco
2010
Abstract
The demand of a more comprehensive engineering tool for parametric investigations of rocket thrust chambers thermal environment is pushing the improvement of hot-gas side heat transfer prediction tools. In this work, the capability of predicting the heat transfer characteristics of a literature test case for a liquid oxygen / gaseous methane single element combustion chamber is assessed by means of 2D axis-symmetric Reynolds-Averaged Navier-Stokes simulations. A simplied approach is proposed, where combustion is not simulated, but combustion products enter the chamber through a pseudo-injector. The numerical results show a good agreement with the experimental data, except in the near injection region.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.