@MastersThesis{Ferreira:2019:OtJaRe,
author = "Ferreira, Daniel Roberto",
title = "Otimiza{\c{c}}{\~a}o de jaqueta de refrigera{\c{c}}{\~a}o
aplicada a motor foguete a propelente l{\'{\i}}quido",
school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
year = "2019",
address = "S{\~a}o Jos{\'e} dos Campos",
month = "2019-04-22",
keywords = "Refrigera{\c{c}}{\~a}o regenerativa, jaqueta de
refrigera{\c{c}}{\~a}o, transfer{\^e}ncia de calor conjugada,
motor foguete a propelente l{\'{\i}}quido, computational fluid
dynamics, regenerative cooling, cooling jacket, conjugated heat
transfer, liquid propellant rocket engine, computational fluid
dynamics.",
abstract = "Este trabalho apresenta um estudo sobre otimiza{\c{c}}{\~a}o de
jaquetas de refrigera{\c{c}}{\~a}o t{\'{\i}}picas de motor
foguete a propelente l{\'{\i}}quido (MFPL). Inicialmente foi
escolhida uma geometria como caso padr{\~a}o e realizado o
c{\'a}lculo semi-emp{\'{\i}}rico. Esta etapa teve como objetivo
determinar as condi{\c{c}}{\~o}es de contorno de fluxo de calor
proveniente da combust{\~a}o. Posteriormente, a geometria e a
malha foram modeladas em software param{\'e}trico e ent{\~a}o
analisada a transfer{\^e}ncia de calor conjugada por
din{\^a}mica dos fluidos computacional (CFD) atrav{\'e}s do
software OpenFOAM. A partir de uma modelagem por CFD funcional,
programou-se o ciclo de otimiza{\c{c}}{\~a}o. Os par{\^a}metros
geom{\'e}tricos da jaqueta de refrigera{\c{c}}{\~a}o foram
variados, atrav{\'e}s de um algoritmo, at{\'e} se encontrar o
ponto {\'o}timo. Os objetivos da otimiza{\c{c}}{\~a}o foram,
diminuir as temperaturas nas paredes e perda de carga, levando-se
em considera{\c{c}}{\~a}o os crit{\'e}rios restritivos
estruturais e de m{\'a}xima temperatura do combust{\'{\i}}vel.
Os resultados permitiram obter uma jaqueta de
refrigera{\c{c}}{\~a}o otimizada e criar uma ferramenta de
an{\'a}lise de sistemas de refrigera{\c{c}}{\~a}o aplicados a
motores foguetes a propelente l{\'{\i}}quido. ABSTRACT: This
work presents a study of optimization of typical cooling jacket
for liquid propellant rocket engine (LPRE). Initially a geometry
was chosen as the standard case and the semi-empirical calculation
was performed. The purpose of this step was determine the heat
flux boundary conditions provide by combustion. Posteriorly, the
geometry and mesh were design on parametric software and then
analyzed the conjugated heat transfer by computational fluid
dynamics (CFD) in OpenFOAM software. From a functional CFD
modeling, the optimization cycle was programmed. The geometric
parameters of the cooling jacket were varied, through an
algorithm, until the optimum point was reached. The objectives of
the optimization were reduce the temperatures on the walls and
pressure loss, taking into account the structural criteria and the
maximum temperature of the fuel. The results allowed to obtain a
cooling jacket optimized and a tool of analysis of cooling systems
for liquid propellant rocket engine.",
committee = "Dourado, Wladimyr Mattos da Costa (presidente/orientador) and
Mendon{\c{c}}a, M{\'a}rcio Teixeira de and Sias, Daniel Fraga",
englishtitle = "Optimization of cooling jacket applied in liquid propellant rocket
engine",
language = "pt",
pages = "173",
ibi = "8JMKD3MGP3W34R/3T3EGEB",
url = "http://urlib.net/ibi/8JMKD3MGP3W34R/3T3EGEB",
targetfile = "publicacao.pdf",
urlaccessdate = "19 mar. 2024"
}