Combustion chamber cooling structure for a rocket engine

A combustion chamber structure (1) comprising an outer structure (11);

• a single-part partial body (18) of the combustion chamber in contact with the outer structure (11) at an outer surface (22) comprised of a basic structure (16) and a rib structure (19) with ribs reaching into the combustion chamber, said ribs repeating themselves in the peripheral direction of the combustion chamber;
• and the combustion chamber structure (1) with the exception of the single part partial body (18) is rotationally symmetrical in relation to an axis (4);
• a plurality of cooling ducts (31, 41) extending in longitudinal direction of the combustion chamber structure (1), at least one first cooling duct (31) extends in the interior of the ribs (25) from a free end (34) of the respective rib (25) facing away from the outer structure (11), up to the outer surface (22) of the single-part partial body (18) and whereby the rib (25) forms a boundary area of the first cooling duct (31) and the cooling duct (31) rests open against the outer surface (22) of the single-part partial body (18) and is covered by the outer structure (11);
• and
• at least one second cooling duct (41), said second cooling duct is arranged in the basic structure (16) between each two ribs (25) and covered on the side of the outer structure (11) by said outer structure.