Ignition of cryogenic H2/LOX sprays

O. Gurliat, V. Schmidt, O. J. Haidn, M. Oschwald

Research output: Contribution to journalArticlepeer-review

30 Scopus citations


First results obtained during the investigation of 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.

Original languageEnglish
Pages (from-to)517-531
Number of pages15
JournalAerospace Science and Technology
Issue number7
StatePublished - Oct 2003
Externally publishedYes


  • Cryogenic spray
  • Flame propagation
  • Hydrogen
  • Ignition
  • LOX
  • Liquid rocket engine
  • Shear coaxial injector


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