Gurliat, O. and Schmidt, V. and Haidn, O. and Oschwald, M. (2003) Ignition of Cryogenic H2/LOX Sprays. Aerospace Science Technology, 7 (7), pp. 517-531.
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First results obtained during the transient ignition process in a cryogenic model rocket combustion chamber are reported. Ignition of the propellants LOX and GH2 has been initiated with a pulsed laser and ignition and flame stabilization processes have been analyzed using high-speed visualization methods. Local flame velocities as well as local convection velocities at the point of ignition are determined by image displacement velocimetry methods. Depending on the injection conditions of the propellants, some distinct phases of the transient start-up process could be observed and are discussed in terms of Weber and Reynolds number.
|Title:||Ignition of Cryogenic H2/LOX Sprays|
|Journal or Publication Title:||Aerospace Science Technology|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 517-531|
|Keywords:||Ignition, Hydrogen, LOX, Cryogenic Spray, Liquid rocket engine|
|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):||E -- no assignement|
|Institutes and Institutions:||Institute of Space Propulsion|
|Deposited By:||Monika Lohmiller|
|Deposited On:||16 Sep 2005|
|Last Modified:||06 Jan 2010 14:04|
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