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LOX Injector Geometry Changes to Reduce the Risk of Injection-Coupled Combustion Instabilities in a Cryogenic Rocket Thrust Chamber

Armbruster, Wolfgang and Hardi, Justin and Miene, Yannik and Suslov, Dmitry and Oschwald, Michael (2019) LOX Injector Geometry Changes to Reduce the Risk of Injection-Coupled Combustion Instabilities in a Cryogenic Rocket Thrust Chamber. In: 32nd International Symposium on Space Technology and Science. 32nd International Symposium on Space Technology and Science, 15. - 21. Jun. 2019, Fukui, Japan.

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Abstract

High-frequency combustion instabilities present a severe risk in the development of liquid propellant rocket engines. Since the detailed coupling mechanisms leading to the instabilities are still not fully understood today, the problem is usually addressed by adding damping elements such as injector baffles or resonators to the combustion chamber. However, their design is mostly based on experience and the damping characteristics are very difficult to predict. Therefore it is necessary tune the resonators and verify sufficient damping with expensive and complex full-scale engine tests. At the Institute of Space Propulsion of DLR the research combustion chamber BKD which shows self-excited combustion instabilities is used to gain a better understanding of the underlying coupling mechanism. As was found out in previous publications, in BKD the combustion instabilities are driven by injection-coupling. A phenomenon which has been reported to also lead to combustion instabilities in cryogenic full-scale engines using shear coaxial injection elements, as the LE-X or J-2S. An improved method to damp injection-coupled instabilities, by directly damping the injector acoustics instead of the chamber pressure oscillations has been developed and tested at representative operating conditions. The principle of the damping method is described in this paper. The damping elements have been installed in an additive manufactured part of the injector head and had no measurable influence on the performance. Test results are presented which imply that the flame dynamics were reduced by damping the injector resonance frequencies.

Item URL in elib:https://elib.dlr.de/132798/
Document Type:Conference or Workshop Item (Speech)
Title:LOX Injector Geometry Changes to Reduce the Risk of Injection-Coupled Combustion Instabilities in a Cryogenic Rocket Thrust Chamber
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Armbruster, WolfgangWolfgang.Armbruster (at) dlr.dehttps://orcid.org/0000-0002-4859-4173
Hardi, JustinJustin.Hardi (at) dlr.dehttps://orcid.org/0000-0003-3258-5261
Miene, YannikYannik.Miene (at) dlr.deUNSPECIFIED
Suslov, DmitryDmitry.Suslov (at) dlr.dehttps://orcid.org/0000-0002-5160-9292
Oschwald, MichaelMichael.Oschwald (at) dlr.dehttps://orcid.org/0000-0002-9579-9825
Date:2019
Journal or Publication Title:32nd International Symposium on Space Technology and Science
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Combustion Instability, Injector Coupling, Damping Device
Event Title:32nd International Symposium on Space Technology and Science
Event Location:Fukui, Japan
Event Type:international Conference
Event Dates:15. - 21. Jun. 2019
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:16 Dec 2019 08:50
Last Modified:19 Dec 2019 08:25

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