Optimization of Nozzle Shape of Hydrogen-Oxygen Rocket Engine

Valeriy Matveev, Vasilii Zubanov, Leonid Shabliy, Anastasia Korneeva

2018

Abstract

The article presents a technique of parametric optimization of nozzle supercritical part of liquid-propellant rocket engine. Main approaches for parametric optimization were given. Two optimizers were mentioned. Thrust and specific impulse were chosen as optimization criteria. Simulation of chamber process was performed in ANSYS CFX with combustion model Eddy Dissipation. Two variants of combustion were considered: one global reaction and detailed chemical system with 8 components and 18 reactions. Comparison of results gives more smooth contours of parameters for set with detailed system against variant with one reaction for simulation of liquid-propellant rocket engine working with “hydrogen-oxygen” propellants. In result of optimization the nozzle length was shortened up to 15% virtually without thrust loss (0.18% reduction in thrust). Also the Pareto set in axis “thrust”-“nozzle length” was obtained.

Paper Citation

in Harvard Style

Matveev V. and Korneeva A. (2018). Optimization of Nozzle Shape of Hydrogen-Oxygen Rocket Engine.In Proceedings of 8th International Conference on Simulation and Modeling Methodologies, Technologies and Applications - Volume 1: SIMULTECH, ISBN 978-989-758-323-0, pages 365-370. DOI: 10.5220/0006890003650370

in Bibtex Style

@conference{simultech18,
author={Valeriy Matveev and Anastasia Korneeva},
title={Optimization of Nozzle Shape of Hydrogen-Oxygen Rocket Engine},
booktitle={Proceedings of 8th International Conference on Simulation and Modeling Methodologies, Technologies and Applications - Volume 1: SIMULTECH,},
year={2018},
pages={365-370},
publisher={SciTePress},
organization={INSTICC},
doi={10.5220/0006890003650370},
isbn={978-989-758-323-0},
}

in EndNote Style

TY - CONF

JO - Proceedings of 8th International Conference on Simulation and Modeling Methodologies, Technologies and Applications - Volume 1: SIMULTECH,
TI - Optimization of Nozzle Shape of Hydrogen-Oxygen Rocket Engine
SN - 978-989-758-323-0
AU - Matveev V.
AU - Korneeva A.
PY - 2018
SP - 365
EP - 370
DO - 10.5220/0006890003650370