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Full-length visualisation of liquid oxygen disintegration in a single injector sub-scale rocket combustor

Suslov, Dmitry and Hardi, Justin and Oschwald, Michael (2019) Full-length visualisation of liquid oxygen disintegration in a single injector sub-scale rocket combustor. Aerospace Science and Technology, 86, pp. 444-454. Elsevier. DOI: 10.1016/j.ast.2018.12.027 ISSN 1270-9638

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Official URL: https://www.sciencedirect.com/science/article/pii/S127096381831664X

Abstract

This work presents results of an effort to create an extended experimental database for the validation of numerical tools for high pressure oxygen-hydrogen rocket combustion. A sub-scale thrust chamber has been operated at nine load points covering both sub- and supercritical chamber pressures with respect to the thermodynamic critical pressure of oxygen. Liquid oxygen and gaseous hydrogen were injected through a single, shear coaxial injector element at temperatures of around 120 K and 130 K, respectively. High-speed optical diagnostics were implemented to visualise the flow field along the full length of the combustion chamber. This work presents the analysis of shadowgraph imaging for characterising the disintegration of the liquid oxygen jet. The large imaging data sets are reduced to polynomial profiles of shadowgraph intensity which are intended to provide a more direct means of comparison with similarly reduced numerical results. Comparing half-lengths of these profiles across operating conditions show clear groupings of load points by combustion chamber pressure and mixture ratio. All load points appear to collapse to an inverse dependence of length on impulse flux ratio.

Item URL in elib:https://elib.dlr.de/131447/
Document Type:Article
Title:Full-length visualisation of liquid oxygen disintegration in a single injector sub-scale rocket combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Suslov, DmitryDmitry.Suslov (at) dlr.dehttps://orcid.org/0000-0002-5160-9292
Hardi, JustinJustin.Hardi (at) dlr.dehttps://orcid.org/0000-0003-3258-5261
Oschwald, MichaelMichael.Oschwald (at) dlr.dehttps://orcid.org/0000-0002-9579-9825
Date:March 2019
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:86
DOI :10.1016/j.ast.2018.12.027
Page Range:pp. 444-454
Publisher:Elsevier
ISSN:1270-9638
Status:Published
Keywords:Co-axial injector; Rocket combustion chamber; Combustion visualisation
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 - Antriebsystemtechnik - Schubkammertechnologie
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Rocket Propulsion
Deposited By: Hanke, Michaela
Deposited On:28 Nov 2019 09:19
Last Modified:23 Mar 2020 12:08

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