Experimental investigation of transient injection phenomena with flash evaporation in rocket combustors at vacuum conditions (B04)

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When igniting cryogenic upper stage rocket engines or reaction and control system engines under vacuum conditions propellants are injected in a superheated state into the combustor. Under these conditions the propellants evaporate violently, which is referred to a flash evaporation. In the project B4 the parameters controlling the flash evaporation of liquid oxygen are analysed in a detailed experimental investigation. The results can be used to develop and verify models for the description of the transient start-up of rocket combustion chambers that are operated with cryogenic fuels.