Abstract: A pressure surface of a first metal material for receiving a pressure therethrough is fabricated to have a directional component parallel to a pressure-application direction and a directional component perpendicular to the pressure-application direction, and an electrically-conductive core is fabricated to have a surface along the pressure surface and a surface perpendicular to the pressure-application direction. An assembly comprising the first metal material, the second metal material and the core is set in a pulse electric-current bonding unit to perform a pulse electric-current bonding process.

Abstract: A pressure surface of a first metal material for receiving a pressure therethrough is fabricated to have a directional component parallel to a pressure-application direction and a directional component perpendicular to the pressure-application direction, and an electrically-conductive core is fabricated to have a surface along the pressure surface and a surface perpendicular to the pressure-application direction. An assembly comprising the first metal material, the second metal material and the core is set in a pulse electric-current bonding unit to perform a pulse electric-current bonding process.

Abstract: A method of producing rocket combustors wherein in forming an outer cylin by a powder metallurgical method on the outer side of a cylinder provided on its outer periphery with a cooling wall of channel construction having a plurality of grooves, a low-melting alloy is used as a filler to be filled into the grooves. It is also possible to form the outer cylinder after forming a Cu plating shell on the periphery of the inner cylinder filled with the low-melting alloy.

Abstract: A method of producing rocket combustors wherein in forming an outer cylin by a powder metallurgical method on the outer side of a cylinder provided on its outer periphery with a cooling wall of channel construction having a plurality of grooves (14), an Ni electroforming layer is formed on the outer side of the outer cylinder, and also a method of producing rocket combustors wherein an outer cylinder is of multilayer construction having two or more layers.

Abstract: The present invention is directed particularly to an improved method using owder metallurgy for the manufacture of the grooved cooling wall of a liquid-propellant rocket combustion chamber. The surface of an inner cylinder constituting the cooling wall is formed with cooling grooves, and these grooves are densely filled up with a filler such as paraffin wax. Thereafter, metal powder which will provide an outer cylinder is compression-molded to a predetermined thickness around the inner cylinder. This metal powder is the same material as the material of the inner cylinder. After the paraffin wax which is the filler is evaporated and removed, the compression-molded metal powder body is sintered in a furnace. During this sintering heat treatment, the inner and outer cylinders are rigidly joined together by the sintering reaction between the atoms of the inner cylinder and the atoms of the metal powder.