TUBULAR COMBUSTION CHAMBER OF ROCKET ENGINE WITH REGENERATIVE COOLING AND METHOD OF MAKING OF COOLING PASSAGE Russian patent published in 2006 - IPC F02K9/64 

FIELD: rocket engines.

SUBSTANCE: method provides making of cooling passage of rocket engine combustion chamber. According to proposed method, set of tubes is formed shaped to suit outline of engine nozzle, said tubes widening in cross section in upper part of chamber. When forming cooling passage, inlet and outlet manifolds are used which provided with holes for ends of tubes. Solder frame is fitted in each said hole and each tube is fitted by its first end part into inlet manifold, and by its second end part, in outlet manifold with provision of arrangement of one frame around first end part and other frame around second end part, after which inlet and outlet manifolds are connected with tubes by soldering. Group of soldered joints is formed between tubes and manifolds. Application of layer of coating on outer parts of tubes and forming of jacket of non-detachable design around tubes is provided additionally. Proposed tubular combustion chamber with regenerative cooling and de Laval nozzles contains set of tubes for coolant shaped to outline of de Laval nozzle, inlet and outlet manifolds, layer of coating on outer parts of tubes, non-detachable jacket enclosing tubes with layer of coating and connected with tubes, each tube being soldered by first end part to inlet manifold and by second part to outlet manifold.

EFFECT: provision of tubular combustion chamber by forming set of tubes with possibility of checking their arrangement and connection and checking of soldered joints before mounting of non-detachable jacket of combustion chamber.

17 cl, 7 dwg