Abstract: A combustion chamber structure for a rocket engine includes a hot gas wall (12) that surrounds a combustion chamber (40) and has a plurality of first coolant channels (50) and a plurality of second coolant channels (52). The plurality of first (50) and second (52) coolant channels extend from a first longitudinal end (16) of the hot gas wall (12) to a second longitudinal end (18) of the hot gas wall (12) opposite to the first longitudinal end (16). The combustion chamber structure (10) further comprises a first manifold (20) forming a first coolant chamber (30) and a second manifold (22) forming a second coolant chamber (32) being fluidly separated from the first coolant chamber (30). The first (20) and second (22) manifolds are provided at the first longitudinal end (16) of the hot gas wall (12) and extend in a circumferential direction of the hot gas wall (12).

Abstract: A combustion chamber structure, particularly for a rocket engine, which comprises a liner surrounding a combustion chamber with an outer surface facing away from the combustion chamber on which coolant channels extending in a longitudinal direction of the liner are formed. The liner forms, at one longitudinal end, a coolant chamber extending in the circumferential direction of the liner for collecting and/or distributing a coolant. The combustion chamber structure further comprises a connecting structure that fluidly connects the coolant chamber to the coolant channels.

Abstract: A combustion chamber structure for a rocket engine includes a hot gas wall (12) that surrounds a combustion chamber (40) and has a plurality of first coolant channels (50) and a plurality of second coolant channels (52). The plurality of first (50) and second (52) coolant channels extend from a first longitudinal end (16) of the hot gas wall (12) to a second longitudinal end (18) of the hot gas wall (12) opposite to the first longitudinal end (16). The combustion chamber structure (10) further comprises a first manifold (20) forming a first coolant chamber (30) and a second manifold (22) forming a second coolant chamber (32) being fluidly separated from the first coolant chamber (30). The first (20) and second (22) manifolds are provided at the first longitudinal end (16) of the hot gas wall (12) and extend in a circumferential direction of the hot gas wall (12).

Abstract: A combustion chamber structure, particularly for a rocket engine, which comprises a liner surrounding a combustion chamber with an outer surface facing away from the combustion chamber on which coolant channels extending in a longitudinal direction of the liner are formed. The liner forms, at one longitudinal end, a coolant chamber extending in the circumferential direction of the liner for collecting and/or distributing a coolant. The combustion chamber structure further comprises a connecting structure that fluidly connects the coolant chamber to the coolant channels.