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Effect of recess in high pressure Liquid Oxygen (LOX)/Methane coaxial injection and combustion

Lux, Johannes and Haidn, Oskar (2009) Effect of recess in high pressure Liquid Oxygen (LOX)/Methane coaxial injection and combustion. Journal of Propulsion and Power, Vol. 25 (Nr.1). American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/37308

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The effect of a recessed liquid oxygen tube in shear coaxial injection has been investigated experimentally using an optically accessible subscale rocket combustor operated at pressures between 40 and 60 bar. Different single-shear coaxial injectors have been used to inject liquid oxygen and methane at relevant operating conditions covering sub-, near-, and supercritical pressures with respect to the critical point of oxygen. Liquid oxygen was injected at 120 K and the injection temperature of gaseous methane was about 275 K. Detection of spontaneous OH and CH chemiluminescene has been performed to characterize the flame-anchoring zone near the liquid oxygen post tip. In addition, the influence of the injector geometry on the combustion roughness and stability has been investigated during steady-state operating points. An increased flame expansion was observed with a recessed injector element. At low momentum flux ratio, the pressure drop accross the injector increases with a recessed liquid oxygen tube compared with a flush tube. Furthermore, a recessed liquid oxygen tube led to be a smoother combustion in general; however, this configuration also led to additional resonant frequencies in the chamber acoustics.

Item URL in elib:https://elib.dlr.de/54327/
Document Type:Article
Title:Effect of recess in high pressure Liquid Oxygen (LOX)/Methane coaxial injection and combustion
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Haidn, OskarOskar.Haidn (at) dlr.deUNSPECIFIED
Date:January 2009
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Volume:Vol. 25
DOI :10.2514/37308
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:high pressure liquid propellant rocket engines, liquid oxygen, LOX, methane CH4, subcritical, supercritical, coaxial injection, injector, recess, combustion chamber
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Lux, Dr. Johannes
Deposited On:17 Sep 2008
Last Modified:08 Mar 2018 18:44

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