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Modeling of H2/O2 single-element rocket thrust chamber combustion at sub- and supercritical pressures with different computational fluid dynamics tools

Riedmann, Hendrik and Banuti, Daniel and Ivancic, Blazenko and Knab, Oliver and Hannemann, Klaus (2019) Modeling of H2/O2 single-element rocket thrust chamber combustion at sub- and supercritical pressures with different computational fluid dynamics tools. In: EUCASS Book Series - Advances in Aerospace Sciences: Progress in Propulsion Physics EUCASS book series - Advances in AeroSpace Sciences, 11. EDP Sciences. pp. 247-272. ISBN 978-5-94588-228-7. ISSN 2493-3503

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Official URL: https://doi.org/10.1051/eucass/201911247

Abstract

This paper derives from the cooperation between DLR and Airbus within the work package "CFD Modeling of Combustion Chamber Pro-cesses" conducted in the frame of the Propulsion 2020 project. In a joint strategy, DLR Göttingen and Airbus DS Ottobrunn have identified a number of test cases with gradually growing complexity where adequate test data are available for proper successive validation of the computational fluid dynamics (CFD) tools to be used in an industrial environment. This work highlights the simulation results for the Mascotte A-10 and A-60 test cases as presented at the 2nd International Workshop on Rocket Combustion Modeling in Lampoldshausen 2001 by ONERA and SNECMA. These two test cases are characterized by different chamber pressures (10 and 60 bar) and, consequently, by oxygen injection conditions which are subcritical in one case and transcritical in the other case. The test cases are treated with three different CFD codes: the DLR TAU Code (only A-60 case), the Airbus DS in-house tool Rocflam3, and the commercial CFD tool ANSYS CFX incorporating several modeling extensions by Airbus DS. To the knowledge of the authors, this paper is the first one which covers both the A-10 and the A-60 test cases.

Item URL in elib:https://elib.dlr.de/118198/
Document Type:Contribution to a Collection
Title:Modeling of H2/O2 single-element rocket thrust chamber combustion at sub- and supercritical pressures with different computational fluid dynamics tools
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Riedmann, HendrikAirbus Defence and Space, MünchenUNSPECIFIED
Banuti, DanielAS-GO-RFZhttps://orcid.org/0000-0002-5469-5704
Ivancic, BlazenkoBlazenko.Ivancic (at) airbus.comUNSPECIFIED
Knab, OliverAirbus Defence and Space, MünchenUNSPECIFIED
Hannemann, KlausKlaus.Hannemann (at) dlr.deUNSPECIFIED
Date:8 February 2019
Journal or Publication Title:EUCASS Book Series - Advances in Aerospace Sciences: Progress in Propulsion Physics
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Volume:11
DOI :10.1051/eucass/201911247
Page Range:pp. 247-272
Editors:
EditorsEmail
Bonnal, ChristopheUNSPECIFIED
Calabro, MaxUNSPECIFIED
Frolov, Sergey M.UNSPECIFIED
Galfetti, LucianoUNSPECIFIED
Maggi, FilippoUNSPECIFIED
Publisher:EDP Sciences
Series Name:EUCASS book series - Advances in AeroSpace Sciences
ISSN:2493-3503
ISBN:978-5-94588-228-7
Status:Published
Keywords:computational fluid dynamics, rocket thrust chamber, fuel injection, subcritical fluid behaviour, supercritical fluid behaviour
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - ProTAU + Prop2020 Hochleistungstriebwerke
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Hannemann, Prof. Dr. Klaus
Deposited On:26 Jul 2019 14:55
Last Modified:31 Jul 2019 20:15

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