RU2557793C1 - Gas turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: this engine comprises housing, cover sealing the engine inlet, electrolyte feed system composed of the nozzle with cavitator, compressor and turbine shaft arranged in said housing, electrolyser-cavitator and local channel contraction with central body. Said electrolyser-cavitator is sealed in separate case connected with combustion chamber to feed pressurized gas mix downstream of compressor via electrolyser-cavitator with central; body to combustion chamber with igniter. Combustion chamber outlet is provided with gas flow separator including supersonic nozzle, outer and inner coaxial tubes and channel to return subsonic flow back, into combustion chamber.

EFFECT: higher efficiency.

2 dwg

Description

The invention relates to energy and mechanical engineering and can be used in engine building.

The closest device of the same purpose to the claimed invention in terms of features is a gas turbine engine comprising a housing and a cover sealing the entrance to the housing, a compressor, a combustion chamber, an electrolyte (aqueous electrolyte) supply system through a nozzle with a cavitator, an ignition device, a turbine and an electrolyzer, a sealing cover entrance to the housing with the possibility of adjustable intake of air into the engine, an electrolyte supply system with the possibility of supplying electrolyte through a nozzle from Kavi an atomizer into the flow of air drawn into the engine and with the possibility of supplying fuel to the combustion chamber, the electrolyzer in this case is made in the form of a cavitator with a central body by supplying direct electric current from the power source to the elements of the cavitator and installed in a separate housing hermetically connected to the combustion chamber, the possibility of supplying the gas mixture under pressure behind the compressor through this electrolyzer-cavitator with a central body into the combustion chamber (see RF patent No. 2324831).

The reasons that impede the achievement of the technical result indicated below when using the known device adopted as a prototype include the fact that the known device does not use the energy of the gas stream economically and inefficiently.

The essence of the invention lies in the use of a device for separating a gas flow into subsonic and supersonic.

The technical result is the achievement of higher technical and economic characteristics of the engine.

The specified technical result during the implementation of the invention is achieved by the fact that in this gas turbine engine comprising a housing and a sealing entrance to the housing, a cover, a compressor, a combustion chamber, an electrolyte (aqueous electrolyte solution) supply system through a nozzle with a cavitator, an ignition device, a turbine and an electrolyzer sealing the entrance to the housing is a cover with the possibility of adjustable air intake into the engine, an electrolyte supply system with the ability to supply electrolyte through a nozzle with a cavitator into the flow air flowing into the engine and with the possibility of supplying fuel to the combustion chamber, an electrolyzer made in the form of a cavitator with a central body by supplying direct electric current from the power source to the cavitator elements and installed in a separate housing hermetically connected to the combustion chamber, with the possibility of supplying a gas mixture under pressure behind the compressor through the electrolyzer-cavitator with the central body into the combustion chamber, the peculiarity is that a device for eniya gas stream (based on the pipe Leontyeva) at subsonic and supersonic from the combustion chamber at subsonic and supersonic components.

The drawings show:

figure 1 is a prototype gas turbine engine;

figure 2 - the proposed gas turbine engine.

Information confirming the possibility of carrying out the invention with obtaining the above technical result are as follows.

The gas turbine engine comprises a housing 1, a sealing cover 2 entering the entrance to the housing, configured to take air into the engine by shutters 3, an electrolyte supply system made in the form of a nozzle 4 with a cavitator, local narrowing of its channel, supply of electrolyte to the air flow into the engine and nozzles 5 for supplying fuel to the combustion chamber 6, the shaft 7 of the compressor 8 and turbine 9 located in the housing 1, the cavitation cell 10, the local narrowing of the channel 11 with the central body 12, formed by supplying a constant electron current from the battery 13 to the elements of the cavitator, for example, to its local narrowing and to its central body. The electrolyzer-cavitator 10 is installed in a separate housing 14 hermetically, on bolts, connected to the combustion chamber 6 and with the possibility of supplying the gas mixture under pressure behind the compressor 8, through this electrolyzer-cavitator 10 with a central body 12 into the combustion chamber 6 with an ignition device 15. At the outlet of the combustion chamber 6, a device for separating the gas flow (based on the Leontief pipe) is installed, containing a supersonic nozzle 16, an external pipe 17, an internal pipe 18, coaxially located relative to each other, a recirculation channel 19 subsonic flow back to the combustion chamber 6.

The work of the proposed gas turbine engine is as follows.

To start the engine, its shaft 7 is untwisted and a constant electric current is supplied from the accumulator 13 to the electrodes of the cavitator-cavitator 10 with the central body 12. The compressor 8 creates a vacuum at its inlet, due to which atmospheric air regulated by the blinds 3 is drawn into the engine housing 1. An electrolyte, for example, an aqueous solution of caustic potassium, is fed into a stream of air drawn into the engine by a nozzle 4 with a cavitator. Due to cavitation in the cavitator of nozzle 4, the water partially dissociates, ionizes to a limit not hazardous to the compressor, its droplets are finest atomized and mixed with air. Further, due to the vacuum at the compressor inlet, the electrolyte turns into steam. Then this mixture is compressed by compressor 8 and under pressure behind the compressor it is supplied to a separate housing 14 of the electrolytic cavitator 10 and is driven through a local restriction 11 with a central body 12, where due to cavitation and due to the flow of direct current through the electrolyte, the nozzles 4 are partially dissociated in the cavitator water vapor present in the stream decomposes completely into hydrogen and oxygen. Then this gas mixture enters the combustion chamber 6, where a small amount of fuel is also supplied through the nozzle 5 and the resulting air-fuel mixture enriched with hydrogen and oxygen is ignited by the ignition device 15. Further, the temperature of the combustion products is normalized in the mixing zone of the combustion chamber 6. Then the gas stream is separated at the inlet to the device for separating the gas stream (based on the Leontief pipe) into two streams - one is sent to the outer pipe 17 and is subsonic, the second is accelerated to supersonic speed in the supersonic nozzle 16 and sent to the inner pipe 18. Surface temperature from the supersonic flow side will be lower than the surface temperature from the subsonic flow side. The resulting temperature difference leads to a heat flux from the subsonic part of the flow to the supersonic. The subsonic flow, giving heat to the supersonic flow, is directed through the subsonic flow recirculation channel 19 back to the combustion chamber 6. A supersonic flow at the outlet of the flow separation device, warmer and with a higher pressure, enters and expands in the turbine 9, rotates the motor shaft 7 and is released into the atmosphere. Thus, due to the use of a device for separating the gas flow into subsonic and supersonic due to the creation of gasdynamic temperature stratification, the pressure and temperature of the working fluid (supersonic gas flow) increase and, consequently, the efficiency of the gas turbine engine increases, because for modern gas turbines, one of the main factors affecting the efficiency of gas turbine plants is the continuous increase in gas temperature in front of the turbine (see Thermal Protection of Turbine Blades / B.M. Galitseysky, V.D. Perfect, V.F. Formalev, M. S. Cherny; Under the editorship of B.M. Galitseysky. In addition, subsonic flow recycling will reduce fuel consumption and increase engine efficiency.

Claims (1)

A gas turbine engine comprising a housing that seals the entrance to the housing cover, an electrolyte supply system made in the form of a nozzle with a cavitator, a compressor and turbine shaft located in the housing, an electrolytic cavitator, local narrowing of the channel with a central body, an electrolytic cavitator is installed in a sealed housing connected to the combustion chamber and with the possibility of supplying the gas mixture under pressure behind the compressor, through a cavitation electrolyzer with a central body into the combustion chamber with an ignition device, from ichayuschiysya in that at the outlet of the combustion chamber device is installed to separate a gas stream comprising a supersonic nozzle, the outer tube, an inner tube coaxially disposed relative to each other, the recirculation channel subsonic flow back into the combustion chamber.

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