Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
Heat Transfer Analysis Of A Solid-Propellant Rocket Combustion Chamber
Submission Author:
José Felipe Alves Avelino , RJ
Co-Authors:
José Felipe Alves Avelino, Daniel Chalhub
Presenter: José Felipe Alves Avelino
doi://10.26678/ABCM.COBEM2021.COB2021-0529
Abstract
The present work aims to obtain the temperature profile of a rocket combustion chamber with solid propulsion without the need for experimental data. The rocket engine consists of a cylindrical chamber containing its respective propellant grain inside, which is a homogeneous mixture of fuel and an oxidizer. For this purpose, the heat of combustion was estimated using a total enthalpy of the chemical reaction. Thus, different portions of this value were considered to estimate the heat flow. It was also necessary to obtain the thermal properties of the propellant grain. Unlike the motor housing, these data are not listed. Their values were approximated proportionally depending on their composition. With these data, it was possible to determine the engine temperature profile. The method used was the Generalized Integral Transform Technique (GITT) for a moving boundary. The consumption of the propellant in the radial direction will be considered in the mathematical model, causing the eigenvalues and eigenfunctions to vary over time. The temperature distributions were analyzed and it was observed that the propellant acts as a strong thermal insulator for the combustion chamber.
Keywords
Integral Transforms, Moving boundary model, Heat transfer, Combustion, Rocket propulsion
