Ignition modeling in methane-oxygen rocket engines

Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics

Master thesis (2017)

Authors

C. Akkermans Aerospace Engineering

Contributors

B.T.C. Zandbergen Space Systems Egineering (mentor)
E.K.A. Gill Space Systems Egineering (graduation committee member)
A.H. van Zuijlen Aerodynamics - Aerospace Engineering (coach)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2017 Christ Akkermans
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Published Date

31-08-2017

Language

English

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Faculty

Aerospace Engineering

Abstract

The influence of using different chemistry model and different chemical kinetics schemes on modeling combustion inside a rocket engine igniter are investigated. An igniter for a LOX/CH4 rocket engine is designed and a CFD model is developed which is used to model the designed igniter. Verification and validation methods are discussed.


Files

Report_V1.0.1.pdf
(.pdf | 16.8 Mb)