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Ignition of Cryogenic H2/LOX Sprays

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.

Full text not available from this repository.

Abstract

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.

Document Type:Article
Additional Information: LIDO-Berichtsjahr=2003,
Title:Ignition of Cryogenic H2/LOX Sprays
Authors:
AuthorsInstitution or Email of Authors
Gurliat, O.UNSPECIFIED
Schmidt, V.UNSPECIFIED
Haidn, O.UNSPECIFIED
Oschwald, M.UNSPECIFIED
Date:2003
Journal or Publication Title:Aerospace Science Technology
Refereed publication:Yes
In ISI Web of Science:Yes
Volume:7
Page Range:pp. 517-531
Status:Published
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
Location: Lampoldshausen
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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