RU2115816C1 - Built-up turbojet engine - Google Patents

Abstract

FIELD: manufacture of engines, aviation, cosmonautics, automotive industry, shipbuilding, new flying vehicles. SUBSTANCE: engine includes two TURBOJET engines located at angle relative to outer loop which operate simultaneously or in turn together with outer loop. Each TURBOJET engine includes turbo-compressors which are supplied with hydrogen and oxygen fed from electrolyzers; hydrogen and oxygen are mixed in ignition chamber where they are ignited by laser beam; engine contains also turbine, combustion chamber from which gas jet of flame passes to turbines of outer loop consisting of atmospheric air supply system, thermal heating system, turbines, turbogenerators for generation of electric power required for operation of laser, electrolyzer and on-board equipment. Outer loop is provided with steam condensers for reuse of water as propellant and separation of steam to obtain dry gas used jet entering the combustion chamber and nozzle which consists of many nozzles with flaps. EFFECT: enhanced efficiency. 1 dwg

Description

 The invention relates to engine manufacturing in aviation, astronautics, automotive, shipbuilding, and can also be used for new aircraft.

 Known turbojet engine (US patent N 5014508, class F 02 K 9/78, 1991, 13 s), powered by gas in a mixture of hydrogen and oxygen, having a free rotor and a control system for selecting a jet of exhaust gas, including a combustion chamber and adjustment means a gas having at least one turbine independent of external atmospheric air develops from infrasonic to supersonic speed.

 The drawing shows the proposed turbojet engine.

 A composite turbojet engine consists of a housing made of heavy-duty alloy, consisting of two small turbojet engines 1, 2 and an external circuit 3. Two turbojet engines are the same, you can use either one or two at the same time. Each consists of a turbocharger 4 (5), to which hydrogen and oxygen are supplied from the electrolyzer (not indicated in the drawing) through the inlet valves of the mixing and ignition chambers with a laser 10 (11), turbines 12 (13), and the combustion chamber 14 (15). The outer circuit 3 is located on a free rotor, where 17 is a turbofan; 18 - air intake; 19 - thermal heating; 22 - turbocharger; 23 and 25 - turbines; 24 - a turbogenerator; 21 and 26 - capacitors, 27 - combustion chamber; 20 - nozzle. Hydrogen and oxygen from electrolysis cells (not indicated in the drawing) are supplied through tubes through inlet valves 6, 7, 8 and 9 to turbocharger 4 and 5, from where it enters the gas mixing and ignition chamber with a laser 10, 11, and the gas-vapor jet rotates under high pressure turbines 12 and 13, then from the combustion chambers 14 and 15, enters the turbines 23 and 25 of the external circuit 3, rotating them, the jet exits the nozzle, the steam condenses from the jet to reuse water, and the dry gas stream exits, having previously connected to heated air cut the turbofan 17 of the external circuit 3, having passed the air intake 18, thermal heating 19, the turbopump 28, the turbocompressor 22 is fed to the turbine 23, where it is connected to the steam-gas jet of the main circuit 1, then the steam is condensed by passing the turbogenerator 24, the condenser 21, then a flame stream with heated air enters the turbine 25, where the gas-vapor stream of circuit 2 is connected to the gas air stream, then, passing the turbine generator, it condenses in the condenser 26 and the dry air-gas stream enters the combustion chamber 27 and emits outwardly through a nozzle 20 having a plurality of nozzles. With the fame of the execution of the output nozzle of the engine from many nozzles (Kudryavtsev V. M. Fundamentals of the theory and calculation of liquid jet engines. M: Higher school, 1975, S. 297 and 298, Fig. 10, 4). The cross section of each nozzle is initially changed in the direction of narrowing to a critical section, and then in the direction of expansion to the outlet section, moreover, in the present invention, with a plurality of nozzles, automatic shutters are used to control the pressure inside the combustion chamber.

 Thus, a jet of dry flame under high pressure is thrown out using the aforementioned dampers in the nozzles, which differs from the proposed nozzles.

 Turbine generators 24 generate an electric current, which is used for on-board electronic equipment. The engine develops supersonic, infrasonic and hypersonic speeds. Due to the use of two turbojet engines and an external circuit, as well as nozzles with dampers. The engine is safe because fuel is water, and the electrolyzer produces the exact amount of hydrogen and oxygen needed, and the laser is a reliable engine ignition system. The engine is environmentally friendly as steam is not thrown out. The main engine power is created by the steam-gas jet 1 and 2 of the turbojet engine, as well as heated atmospheric air under high pressure, through the turbines of the external circuit 3, and the steam, condensing, is reused as fuel.

Claims (1)

 A composite turbojet engine containing an external circuit with a compressor, turbines and a nozzle with an exhaust gas jet control damper and two turbojet engines with an oxygen and hydrogen supply system and a combustion chamber, characterized in that it contains an electrolyzer for generating oxygen and hydrogen and a laser included in the composition of turbojet engines located at an angle to the external circuit and connected respectively to the turbines of the external circuit, and steam condensers for reuse in odes, and the nozzle is made in the form of a plurality of nozzles with shutters.