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Otkrytoe Aktsionernoe Obschestvo Nauchno-proizvodstvennoe Obiedinenie

Stanislav Dmitrievich Kamensky

Boris Ivanovich Katorgin

Vladimir Konstantinovich Chvanov

Alexandr Alexandrovich Vasin

Vladimir Vladimirovich Fedorov

Gennady Grigorievich Derkach

Viktor Nikonorovich Semenov

Jury Vasilievich Movchan

Anatoly Ivanovich Grigoriev

Vladimir Jurievich Bogushev

Alexandr Nikolaevich Vycherov

Galina Andreevna Babaeva

Jury Alexandrovich Pestov

Nikolai Kondratievich Dudkin

Nikolai Fedorovich Molev

Nikolai Mikhailovich Grigorkin

Leonid Alexeevich Tumanov

Viktor Petrovich Nosov

Anatoly Ivanovich Stavrulov

Vladimir Veniaminovich Sagalovich

Evgeny Ivanovich Baranov

Raisa Vasilievna Chernikova

Galina Vasilievna Shashelova

Ljudmila Alexandrovna Anosova

Jury Alexandrovich Bedov

Oleg Ivanovich Studenikin

Alexei Ivanovich Kolesnikov

The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing. A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an external bottom. Bipropellant injectors are fixed in the internal injector face and the middle bottom. A portion of the bipropellant injectors are mounted projecting from the internal injector face, while another portion are recessed in the internal injector face. The ignition means are made from jet injectors mounted in a structural casing behind the internal injector face. Axes of diverging ports of jet injectors are positioned at an acute angle to an outlet from the structural casing and deflected in a circle in a lateral plane from the longitudinal axis of the structural casing in an identical direction. The chamber casing comprises a combustion chamber and a nozzle, made from an external structural envelope and an internal fire wall. A regenerative cooling passage is positioned between the external structural envelope and the internal fire wall. A ring-like slot of a gas-screen belt is made in the internal fire wall before the nozzle throat. The regenerative cooling passage of the chamber is made with a branched inlet. One of its branches communicates with the space of the chamber regenerative cooling passage between the nozzle throat and its scarf, a second branch&mdash;with the space of the chamber regenerative cooling passage before the nozzle throat, and a third&mdash;with the space of the chamber regenerative cooling passage before the ring-like slot of the gas-screen belt.

Liquid-propellant rocket engine chamber and its casing

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.

Method for producing a welded-brazed combustion chamber

Growing community of inventors

Khimki, Russia

Stanislav Dmitrievich Kamensky