LRE GAS PATH Russian patent published in 2016 - IPC F02K9/48 

FIELD: motors and pumps.

SUBSTANCE: this invention relates to liquid rocket engines (LRE) with the oxidizing afterburning gas generator. Gas path downstream of the gas generator and the turbine housing THA provided with electroplated nickel and copper coatings that increase the resistance of aggregates to the fire, a single end portion of the curved pipe of the engine in flight equipment is provided with an inspection hole and welded to it threaded socket inspection of the turbine wheel with installed plug and a sealing ring in the socket outlet of a single end portion of the curved conduit mounted threaded fittings with installed three thermocouples having different lengths sensing element and a sealing gasket on the straight sections of the branched curved pipe a heat exchanger, equipped with connections for supplying and removing gas turbocharging, wherein the pressurization gas feed nozzle situated downstream of the oxidation gas generator.

EFFECT: invention enhances the reliability of the junction of the gas generator with a single turbopump and the end portion of the curved pipe with the release of the turbine, as well as improving the reliability of the engine, its components, and the gas generator THA.

3 cl, 12 dwg