Experimental and numerical investigation of combustion and heat transfer in thrust chambers (K01*)

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It is foreseen to consolidate open issues of the GOX/GCH4 combustion studies and find an injector config-uration with sufficient performance, acceptable wall heat loads and minimum film cooling flow rates and a more detailed investigation of a natural combustion instability which occurred during phase 2. The adapta-tion of the facility with liquid oxygen and the repetition of selected tests with liquid oxygen will deepen the established data base for injector performance, wall heat transfer and film cooling efficiency. The main objective is a data base for the validation of detailed scientific approaches developed within the SFB TRR 40 in SP C1, and C5 and for the improvement of existing engineering design tools.