Rocket engine combustion chamber with enhanced heat transfer to cooling jacket
AssigneeAstrium GmbH
InventorsPeter Bichler, Hans Immich, Joachim Kretschmer, Günther Schmidt
Life of this patent
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Abstract
A combustion chamber for a rocket engine expels a hot stream of gas and has a cooling device. The inner wall of the combustion chamber adjoins the cooling device and contains depressions formed in such a way that the stable outer layer of the stream of gas that forms in the proximity of the inner wall of the combustion chamber during operation of the combustion chamber is destabilized in the area of the depressions.
Claims8
A combustion chamber for a rocket engine that expels a hot stream of gas, comprising a cooling device, and an inner combustion-chamber wall adjoining the cooling device, wherein the inner combustion-chamber wall includes depressions configured to result in flow destabilization of a stable outer layer of the hot stream of gas that forms in proximity to the inner combustion-chamber wall during combustion chamber operation, and wherein the depressions are configured as grooves slanted at a maximum angle of 45° relative to a circumferential direction of the combustion chamber.
A combustion chamber for a rocket engine that expels a hot stream of gas, comprising a cooling device, and an inner combustion-chamber wall adjoining the cooling device, wherein the inner combustion-chamber wall includes depressions configured to result in flow destabilization of a stable outer layer of the hot stream of gas that forms in proximity to the inner combustion-chamber wall during combustion chamber operation, wherein an area of the inner combustion chamber wall has depressions of varying densities.
Dependencies are inferred from the claim text.