Method of manufacturing a regeneratively cooled divergent nozzle of a rocket combustion chamber and nozzle

The method involves connecting the two walls of the rocket combustion chamber with each other by a form closure. The cooling duct bars of the former wall intervene in the corresponding recesses of the latter wall for forming the form closure. The form closure is manufactured by the deformation of the latter wall in the area of cooling channels. An independent claim is also included for a regenerative cooled nozzle extension for a rocket combustion chamber with an initial contour.