Combustion chamber structure and methods for their preparation

The invention comprises a combustion-chamber structure, in particular for a rocket engine, a combustion chamber liner with cooling channels and at least one manifold for supplying and removing a coolant, in particular a cryogenic fuel, wherein the / manifold (s) is soldered to the combustion-chamber liner / are and of the / manifold (s) uncovered portion of the combustor liner is coated with a galvanically applied support casing. The invention also includes a method for their preparation.