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). 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.
|Title:||Effect of recess in high pressure Liquid Oxygen (LOX)/Methane coaxial injection and combustion|
|Journal or Publication Title:||Journal of Propulsion and Power|
|In Open Access:||No|
|In ISI Web of Science:||Yes|
|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)|
|Institutes and Institutions:||Institute of Space Propulsion > Technologie|
|Deposited By:||Dr. Johannes Lux|
|Deposited On:||17 Sep 2008|
|Last Modified:||07 Feb 2013 20:34|
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