Abstract: A circular-shaping device for a rotating part, especially an exhaust housing of a turbo engine is disclosed. The device includes a lower unit with two shaping rollers mounted movably along an axis X1 and one shaping roller mounted movably along an axis Y1; an upper unit with two shaping rollers mounted movably along an axis X2 and one shaping roller mounted movably along an axis Y2; a turntable disposed between the lower unit and the upper unit; and a blocking device for the rotating part on the turntable.

Abstract: A circular-shaping device for a rotating part (16), especially an exhaust housing of a turbo engine. It comprises a lower unit (4) comprising two shaping rollers (32) mounted movably along an axis X1 and one shaping roller (38) mounted movably along an axis Y1; an upper unit (8) comprising two shaping rollers (48) mounted movably along an axis X2 and one shaping roller (50) mounted movably along an axis Y2; a turntable (12) disposed between the lower unit (4) and the upper unit (8); blocking means (26, 28) for the rotating part on the turntable (12).

Abstract: A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first position and an operating second position, the piston comprising a piston head and a piston rod, and subdividing the chamber body bore into a combustion chamber in front of the piston, and at least one injection chamber surrounding the piston rod, the chamber body further including a flow section that is closed in said rest position to prevent any propellant being fed from the injection chamber(s) and that is opened when the piston moves from said rest position to said operating position in order to allow the injection chamber(s) to be filled via said flow section directly from the feed duct(s), the propellant(s) being injected into the combustion chamber via injection channels formed between the combustion chamber and the inject

Abstract: A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first position and an operating second position, the piston comprising a piston head and a piston rod, and subdividing the chamber body bore into a combustion chamber in front of the piston, and at least one injection chamber surrounding the piston rod, the chamber body further including a flow section that is closed in said rest position to prevent any propellant being fed from the injection chamber(s) and that is opened when the piston moves from said rest position to said operating position in order to allow the injection chamber(s) to be filled via said flow section directly from the feed duct(s), the propellant(s) being injected into the combustion chamber via injection channels formed between the combustion chamber and the inject