Joint design and simulation of GOX-GCH4 combustion and cooling in an experimental water-cooled subscale rocket engine

This paper presents the authors’ most recent research regarding the feasibility of cooling a 1 kN scaled-down experimental rocket engine, running on gaseous oxygen and gaseous methane, for a ground test. The cooling segment of a rocket engine has always been a delicate problem, increasing the develo...

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Vydané v:INCAS bulletin Ročník 15; číslo 4; s. 159 - 167
Hlavní autori: MEREU, Alexandru, ISVORANU, Dragos
Médium: Journal Article
Jazyk:English
Vydavateľské údaje: Bucharest INCAS - National Institute for Aerospace Research "Elie Carafoli" 02.12.2023
National Institute for Aerospace Research “Elie Carafoli” - INCAS
Predmet:
cfd analysis
Combustion chambers
Cooling
Cooling systems
Engines
Ground tests
Heat transfer
Methane
Oxygen
pdf combustion
Real gases
real-fluid
rocket engine
Rocket engines
Rockets
Simulation
Temperature
test bench water cooling
Viscosity
ISSN:2066-8201, 2247-4528
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Shrnutí:This paper presents the authors’ most recent research regarding the feasibility of cooling a 1 kN scaled-down experimental rocket engine, running on gaseous oxygen and gaseous methane, for a ground test. The cooling segment of a rocket engine has always been a delicate problem, increasing the development time and costs of development. Since a series of problems can occur during the first ignition of a rocket engine prototype, removing as many potential issues from the initial test, such as using liquid methane for the cooling system, could result in a more stable experiment. Using water as the cooling agent can contribute to a more accelerated TRL increase of the engine’s subcomponents while reducing the risks taken for a whole assembly test. Thus, the combustion chamber, nozzle, and injector can be tested separately from the final cooling method, which can be added subsequently. In the present work, both a steady and transient CFD combustion simulation of a multicomponent compound, consisting of gaseous oxygen and gaseous methane was conducted in the combustion chamber of a small-scale rocket engine. The simulation is based on PDF-flamelet approach for the oxygen and methane combustion, along with real gas equations for the cooling agent.
Bibliografia:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:2066-8201
2247-4528
DOI:10.13111/2066-8201.2023.15.4.13