Abstract: A gas generator is produced of separate units, including a mixing head, a casing and an outlet branch pipe, which are interjoined by welding. The mixing head is welded to the outlet branch pipe through a spacer and a structural spherical casing. The spacer and the outlet branch pipe are made of two inter-brazed envelopes, the inner envelopes of the spacer and the branch pipe are welded at their end faces by electron-beam welding, and the outer structural envelopes are welded by electron-arc welding using a split ring. The spacer is joined to the mixing head by automatic gas-shielded welding. The spherical casing of the gas generator is welded to the outlet branch pipe and the mixing head after the spacer is welded to the mixing head and the outlet branch pipe.

Abstract: A gas generator in particular for driving liquid-propellant rockets, having, a structural envelope, an outlet pipe, a cover connected to the structural envelope from the side opposite to the outlet pipe. A bush is made on the inner side of the cover. An injector face is mounted on the bush end to form a space between the injector face and the cover. Chambers are made in the injector face and the cover. A spacer, mounted inside the structural envelope, is fastened on the outlet pipe and the bush to form an annular space there between. Mixing modules are fastened in the cover and in the injector face chambers. A propellent feed inlet pipe is fastened to the outer surface of the cover inside which a propellant space is made. An oxidizer feed inlet pipe is fastened inside the structural envelope and communicates with the annular space. The annular space communicates with the space between the cover and the injector face via ports made in the bush.

Abstract: The invention relates to the field of power machine building and may be used in mixing devices of gas generators for driving gas turbines, in particular, for liquid-propellant rocket engines. A gas generator comprises a cover with a hole, a bottom with a mixing chamber, a housing with an axial duct communicating with the hole in the cover. The housing is fastened in the cover hole and/or in the mixing chamber of the bottom. Grooves are made uniformly along the circumference of the cross section of the housing in the bottom and/or on the housing. The hole in the cover and the axial duct are designed to supply propellant, and the space between the cover and the bottom and the grooves in the bottom and/or on the housing are designed to supply an oxidizer. A propellant space is made in the cover, and the axial duct communicates through the propellant space with the hole in the cover by means of tangential propellant supply holes.

Abstract: A combustion chamber for a liquid-propellant rocket engine includes an injector head jointed to a combustion chamber casing having an exhaust head on a nozzle output. The casing is made of a steel jacket and a bronze-steel internal fire wall, which are joined with each other and contain shells connected in series. The exhaust head with shells of the casing, jointed to the exhaust head, are brazed using a solder on the basis of nickel, chromium and manganese. Parts of the injector head and other members of the combustion chamber casing are brazed using a copper-silver solder. Shells of the fire wall are connected by an electron-beam welding, directing an electron beam into axial gaps left while brazing between shells of the jacket. The shells of the jacket are then sequentially connected by an automatic gas-shielded arc welding through corresponding ring spacers.