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Analysis of High Amplitude Acoustic Pressure Field Dynamics in a LOX/H2 rocket combustor

Armbruster, Wolfgang and Gröning, Stefan and Hardi, Justin and Oschwald, Michael (2016) Analysis of High Amplitude Acoustic Pressure Field Dynamics in a LOX/H2 rocket combustor. [Other]

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Abstract

High frequency combustion instabilities present a serious problem for liquid propellant rocket engines. These interactions between combustion chamber acoustics and variations of the heat release rate are difficult to predict, because the underlying coupling mechanisms are still not fully understood. For this reason self-excited combustion instabilities are investigated with a cryogenic research combustor at DLR Lampoldshausen. In order to get a better understanding of the coupling mechanisms the acoustic pressure field inside the combustion chamber needs to be described precisely. Due to the highly turbulent nature of the processes in a rocket combustor it can be expected that also the acoustic pressure field shows some variation during unstable combustion. The framework of this report new methods with high time resolution were applied to experimental data to analyze the dynamics of the pressure field for different types of instability. The results reveal that the applied methods give further insight into the excited pressure field and may help to identify the coupling mechanisms in the future.

Item URL in elib:https://elib.dlr.de/109000/
Document Type:Other
Title:Analysis of High Amplitude Acoustic Pressure Field Dynamics in a LOX/H2 rocket combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Armbruster, WolfgangWolfgang.Armbruster (at) dlr.deUNSPECIFIED
Gröning, StefanInstitut für Raumfahrtantriebe, DLR LampoldshausenUNSPECIFIED
Hardi, JustinJustin.Hardi (at) dlr.dehttps://orcid.org/0000-0003-3258-5261
Oschwald, MichaelMichael.Oschwald (at) dlr.deUNSPECIFIED
Date:2016
Journal or Publication Title:SFB/TRR 40 Annual Report 2016
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 203-214
Status:Published
Keywords:rocket combustor, combustion intability
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:06 Dec 2016 09:25
Last Modified:06 Dec 2016 09:25

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