Abstract: A method for producing a combustion chamber includes providing a combustion chamber wall; forming a plurality of milled recesses in the combustion chamber wall, along a longitudinal axis and in an area of the longitudinal axis transverse to the longitudinal axis; and forming a cooling channel having a substantially rectangular cross section and opposite web walls inside the combustion chamber wall along the longitudinal axis and configured to receive a flow a cooling medium along the longitudinal axis, wherein the plurality of milled recesses form depressions in the web walls.

Abstract: A method for producing a combustion chamber includes providing a combustion chamber wall; forming a plurality of milled recesses in the combustion chamber wall, along a longitudinal axis and in an area of the longitudinal axis transverse to the longitudinal axis; and forming a cooling channel having a substantially rectangular cross section and opposite web walls inside the combustion chamber wall along the longitudinal axis and configured to receive a flow a cooling medium along the longitudinal axis, wherein the plurality of milled recesses form depressions in the web walls.

Abstract: A combustion chamber for expelling a hot gas stream from a rocket engine includes a combustion chamber wall and a plurality of cooling channels arranged inside the combustion chamber wall and configured to receive a flow of a cooling medium. Each cooling channel defines a longitudinal axis, a depth direction, and a substantially rectangular cross section. At least one cooling channel includes a plurality of depressions configured to prevent a stratification of the cooling medium in the at least one cooling channel. The plurality of depressions are arrange transverse to a direction of the flow direction and transverse to the longitudinal axis in the depth direction.