Influence of J and We Number on GH2/LOX Ignition Process

First results obtained from investigations of the transient ignition process of a cryogenic GH2/LOX spray in a model rocket combustion chamber are reported. Ignition of the propellants has been initiated with a pulsed laser and ignition and flame stabilization process 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 displancement velocimetry methods. During the ignition process four distinct phases could be observed.