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

Lux, Johannes und 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). DOI: 10.2514/37308.

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Kurzfassung

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.

Dokumentart:Zeitschriftenbeitrag
Titel:Effect of recess in high pressure Liquid Oxygen (LOX)/Methane coaxial injection and combustion
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Lux, JohannesNICHT SPEZIFIZIERT
Haidn, OskarOskar.Haidn@dlr.de
Datum:Januar 2009
Erschienen in:Journal of Propulsion and Power
Referierte Publikation:Ja
In Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:Vol. 25
DOI :10.2514/37308
Herausgeber:
HerausgeberInstitution und/oder E-Mail-Adresse der Herausgeber
Yang, VigorNICHT SPEZIFIZIERT
Status:veröffentlicht
Stichwörter:high pressure liquid propellant rocket engines, liquid oxygen, LOX, methane CH4, subcritical, supercritical, coaxial injection, injector, recess, combustion chamber
HGF - Forschungsbereich:Verkehr und Weltraum (alt)
HGF - Programm:Weltraum (alt)
HGF - Programmthema:W RP - Raumtransport
DLR - Schwerpunkt:Weltraum
DLR - Forschungsgebiet:W RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):W - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (alt)
Standort: Lampoldshausen
Institute & Einrichtungen:Institut für Raumfahrtantriebe > Technologie
Hinterlegt von: Dr. Johannes Lux
Hinterlegt am:17 Sep 2008
Letzte Änderung:07 Feb 2013 20:34

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