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Laser ignition of a multi-injector LOX/methane combustor

Börner, Michael and Manfletti, Chiara and Hardi, Justin and Suslov, Dmitry and Kroupa, Gerhard and Oschwald, Michael (2018) Laser ignition of a multi-injector LOX/methane combustor. CEAS Space Journal, 10 (2), pp. 273-286. Springer. DOI: 10.1007/s12567-018-0196-6 ISSN 1868-2502

Full text not available from this repository.

Official URL: https://doi.org/10.1007/s12567-018-0196-6

Abstract

This paper reports the results of a test campaign of a laser-ignited combustion chamber with 15 shear coaxial injectors for the propellant combination LOX/methane. 259 ignition tests were performed for sea-level conditions. The igniter based on a monolithic ceramic laser system was directly attached to the combustion chamber and delivered 20 pulses with individual pulse energies of $${33.2 \backslashpm 0.8 \backslash,\backslashtext{ mJ }}$$33.2±0.8mJ at 1064 nm wavelength and 2.3 ns FWHM pulse length. The applicability, reliability, and reusability of this ignition technology are demonstrated and the associated challenges during the start-up process induced by the oxygen two-phase flow are formulated. The ignition quality and pressure dynamics are evaluated using 14 dynamic pressure sensors distributed both azimuthally and axially along the combustion chamber wall. The influence of test sequencing on the ignition process is briefly discussed and the relevance of the injection timing of the propellants for the ignition process is described. The flame anchoring and stabilization process, as monitored using an optical probe system close to the injector faceplate connected to photomultiplier elements, is presented. For some of the ignition tests, non-uniform anchoring was detected with no influence onto the anchoring at steady-state conditions. The non-uniform anchoring can be explained by the inhomogeneous, transient injection of the two-phase flow of oxygen across the faceplate. This characteristic is verified by liquid nitrogen cold flow tests that were recorded by high-speed imaging. We conclude that by adapting the ignition sequence, laser ignition by optical breakdown of the propellants within the shear layer of a coaxial shear injector is a reliable ignition technology for LOX/methane combustors without significant over-pressure levels.

Item URL in elib:https://elib.dlr.de/123955/
Document Type:Article
Title:Laser ignition of a multi-injector LOX/methane combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Börner, MichaelMichael.Boerner (at) dlr.dehttps://orcid.org/0000-0002-3441-2869
Manfletti, ChiaraUNSPECIFIEDUNSPECIFIED
Hardi, JustinUNSPECIFIEDUNSPECIFIED
Suslov, DmitryUNSPECIFIEDUNSPECIFIED
Kroupa, GerhardUNSPECIFIEDUNSPECIFIED
Oschwald, MichaelUNSPECIFIEDUNSPECIFIED
Date:10 February 2018
Journal or Publication Title:CEAS Space Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:10
DOI :10.1007/s12567-018-0196-6
Page Range:pp. 273-286
Publisher:Springer
ISSN:1868-2502
Status:Published
Keywords:Ignition, Laser ignition, LOX/CH4, Methane, Green propellants, Rocket engine
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: Börner, Michael
Deposited On:30 Nov 2018 08:17
Last Modified:14 Dec 2019 04:28

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