RU177796U1 - Jet engine - Google Patents

Jet engine Download PDF

Info

Publication number
RU177796U1
RU177796U1 RU2017121758U RU2017121758U RU177796U1 RU 177796 U1 RU177796 U1 RU 177796U1 RU 2017121758 U RU2017121758 U RU 2017121758U RU 2017121758 U RU2017121758 U RU 2017121758U RU 177796 U1 RU177796 U1 RU 177796U1
Authority
RU
Russia
Prior art keywords
disks
cylinders
hollow
electric
jet engine
Prior art date
Application number
RU2017121758U
Other languages
Russian (ru)
Inventor
Борис Андреевич Шахов
Original Assignee
Борис Андреевич Шахов
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Борис Андреевич Шахов filed Critical Борис Андреевич Шахов
Priority to RU2017121758U priority Critical patent/RU177796U1/en
Application granted granted Critical
Publication of RU177796U1 publication Critical patent/RU177796U1/en

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10Adaptations for driving, or combinations with, electric generators
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan

Abstract

A jet engine comprises a streamlined housing, combustion chambers secured to the housing, an electromagnetic cushion housed in the housing, consisting of hollow cylinders with stator electromagnets, a reversible electric machine, consisting of hollow cylinders with stator electromagnets and rotors. The utility model allows you to expand the capabilities of onboard or mounted electrical equipment, allowing you to use propulsion thrusters with electric drives on a jet engine or as airborne thrusters with electric drives on aircraft. 2 ill.

Description

The utility model relates to engine building and can be used as a jet engine with a reversible electric machine, as a generating system with electric potential, which makes it possible to use electric propulsion drives on a jet engine as additional traction. The efficiency of the generating system on a jet engine will expand the capabilities of on-board or mounted electrical equipment and the possibility of using on-board propulsion with an electric drive, as an additional traction in mechanical engineering and on aircraft.
The possibility of using thrusters with an electric drive on a jet engine, as an additional thrust, will allow the jet engine to be used as a modular aircraft with remote control or as modular thrusters on aircraft.
The use of a jet engine with a reversible electric machine as a generating system allows the use of a jet engine in the power system as a gas turbine generating unit.
A gas turbine engine (GTE) is known, containing compressor disks coaxially mounted for rotation, a turbine shaft installed in a turbine channel with an internal profiled shell along the inlet from the inlet guide apparatus to the jet nozzle, and the disks and turbine shaft are equipped with blades mounted with an angle of attack (see Polytechnical Dictionary. - M. 1976, p. 101).
The disadvantage of this technical solution is the limited efficiency due to limitations in the design of a gas turbine engine as a heat engine in terms of efficiency
The task solved by the utility model is to increase work efficiency.
The problem is achieved in that the jet engine containing the compressor disks coaxially rotatably mounted, a turbine, a profiled shell, combustion chambers and nozzles, compressor disks and a turbine are equipped with blades mounted with an angle of attack, characterized in that the jet engine contains a streamlined body, combustion chambers fixed to the housing, an electromagnetic cushion placed in the housing, consisting of hollow cylinders with stator electromagnets, a reversible electric machine, consisting of empty calving cylinders with stator and rotor electromagnets, an axis fixed to the housing, electric drive disks placed on the axis, consisting of hollow cylinders with stator electromagnets, and from cylinders with rotor magnets, an electric machine stator cylinder, coaxial shafts and a differential gearbox kinematically connecting to each other coaxial shafts placed on coaxial shafts profiled shaft and shell, consisting of disks, rotors of an electric machine, turbine consisting of hollow disks, made cylinders of electric drives, e of electromagnetic cushions and electric machines in the form of hollow cylinders on one side are blocked by bases and placed by bases of the rotors of the electric machine on coaxial shafts and gray hairs with disks of a profiled shaft and shell, and the stator cylinder is placed on the axis and is located in the electric machine between two rotor cylinders concentrically, and the cylinders the stator of the electric drives and the electromagnetic cushion are placed by the bases on the body, while the cylinders of the rotors of the electric drives are concentrically between the cylinders tator of electric drives and electromagnetic cushion, and placed on the base of the disks placed on the axis, with the disks placed on the axis of the electric drives and disks on the coaxial shafts mounted alternately with the possibility of opposite rotation and equipped with blades alternately with the opposite angle of attack, while the shell disks are additionally the blades are provided externally with an angle of attack, and the hollow turbine disks are provided inside with partitions installed with the angle of attack, hollow blades and channels connecting the hollow disks from voids open blades, while on the hollow blades placed gauge holes aimed at the jet stream.
Placing the disks of the profiled shaft and the shell with the possibility of opposite rotation in the compressor of the jet engine and installing alternately the disks of the profiled shaft and the shell with the opposite angle of attack of the blades and placing the blades on the outer part of the shell with the angle of attack creates the possibility due to the effect of increasing the speed of the flow twisted by the blades with opposite rotation and pumped by the blades on the outer part of the shell disks installed with an angle of attack, to seal the flow of the gaseous medium more efficiently projectively compressor, significantly increase the energy of the jet in the combustion chamber and a turbine jet engine. The increased energy of the jet in the turbine will increase the diameter of the turbine disks, thereby increasing the total component of the rotation of the turbine and compressor disks per unit time of the pressure of the jet on the blades.
Placing the disks in the turbine alternately with the possibility of opposite rotation and supplying the blades alternately with the opposite angle of attack allows the jet engine to operate with a jet stream and pressure in the turbine to repel the blades with the opposite angle of attack in opposite directions, creating the opposite rotation of the blades placed on the turbine disks, increasing per unit time of the jet pressure on the blades, the total component frequency and the rotation force of the turbine and compressor disks.
When the jet engine is running, the compressor efficiency and the presence of partitions installed with an angle of attack inside the hollow turbine disks will create pressure of the cold gas medium in the hollow turbine disks, preventing hollow turbine disks, channels and hollow blades with calibrated holes from overheating. The pressurized supply of cold gaseous medium through hollow turbine disks, channels, hollow blades and calibrated openings directed to the jet stream makes it possible, being repelled by the cold gaseous medium from the hot jet stream, to form an air cushion protecting the turbine blades from overheating, while repelling cold gas medium from a jet stream, increase the frequency and force of the opposite rotation of the turbine disks per unit of impact of the jet stream on the blades.
Placing the differential gearbox on the axis connecting the coaxial shafts to each other will provide the generator rotors, profiled shaft disks, shells and turbines located on the coaxial shafts when the jet engine is operating in a synchronous opposite rotation.
The opposite synchronous rotation of the disks of the jet engine makes it possible to evenly distribute the load on the blades and disks during the operation of the jet engine in load conditions, as well as to solve the problem of the gyroscopic effect in the jet engine.
The kinetic energy of the mass of the opposite rotation of the parts of the jet engine will allow to increase the total torque of the jet engine, as well as to maintain a stable uniform opposite rotation of the parts of the jet engine.
Placing a reversible electric machine in a jet engine with the possibility of using it as an electric generator, the stator cylinder of which is located between two cylinders of opposite rotation rotors, will allow opposite rotor electromagnetic fields to cross opposite stator electromagnetic fields per unit time twice as often, which increases the amount of generated electricity per unit of time.
Placing a reversible electric machine in a jet engine makes it possible to use a reversible electric machine as an electric motor to start a jet engine.
The opposite synchronous rotation of the electric drives is ensured by the interaction of the same mutually attractive force by the opposites pluses of the electromagnets of the stator cylinders, mounted on the base with the opposite poles of the magnets of the rotor cylinders placed on the disks. The placement on the axis of the disks by electric drives in front of the jet engine compressor will allow to automatically maintain the pressure of the gas medium in front of the compressor, to seal the gas flow for favorable compressor operation. Significantly increase the energy of the jet in the combustion chambers and the turbine of the jet engine during operation in acceleration modes, at low speeds or placed stationary, or operated in a discharged environment.
An increase in the thrust of a jet engine and the efficiency of the generating system will provide, in addition to efficient thrust of a jet engine, a powerful electric potential, which will expand the capabilities of mounted and on-board electrical equipment and the possibility of using on-board propulsion systems with an electric drive, as an additional thrust in mechanical engineering and aircraft.
The powerful electric potential in the jet engine and the possibility of placing electric drives on the disks at the maximum distance from the center of rotation will allow increasing the drive power of the disks when increasing the diameter of the disks. The use of an electromagnetic cushion will reduce axial loads and buildup of the disks during active displacement or when the load increases, the diameters of the electric disks placed on the axis of the jet engine or placed as airborne propellers on aircraft.
The possibility of using propellers with an electric drive on a jet engine of a larger diameter, allowing the use of a part of the blade of the electric drive disks located outside the diameter section of the jet engine compressor as blades having the ability to pump or aerodynamic thrust, will allow the jet engine to be used as modular aircraft with remote control or as modular propulsion, on aircraft.
A powerful electric potential in a jet engine will increase the number of sequentially placed disks with electric drives on the axis or the power of electric drives placed on the disks.
Increasing the thrust of a jet engine and the efficiency of the generating system, and the possibility of using airborne propulsion engines with an electric drive, as an additional thrust on aircraft, makes it possible, when flying aircraft, to smoothly switch from the aerodynamic lifting force of the wing to the thrust of the onboard thrusters of the electric drive and to the jet thrust of the jet engine . Excluding the direct dependence of aircraft on the aerodynamic lift of the wing. During the flight and maneuvering in automatic mode, the opportunity is created to combine the lifting force of the aerodynamic wing of aircraft with the thrust of the onboard propulsion engines and the jet thrust of the jet engine.
These advantages make it possible to qualify the proposed technical solution as a solution that gives an over-overall effect.
The utility model is illustrated by drawings. Figure No. 1, 2, which shows a diagram of a jet engine, a longitudinal section.
The jet engine comprises a streamlined housing 1, a compressor 2, combustion chambers 3 fixed to the housing 1, a turbine 4, blades 5, an electromagnetic cushion consisting of hollow cylinders with stator electromagnets 6, a reversible electric machine 7, consisting of hollow cylinders with stator electromagnets 8 and rotors 9 and an axis 10 fixed to the housing 1. Disks 11, 12 with electric drives 13, 14 located on the axis 10, consisting of hollow cylinders with stator electromagnets 15 and cylinders with rotor magnets 16, stator cylinder 8 of electric machine 7, are coaxial shafts 17 and a differential gearbox 18 kinematically connecting the coaxial shafts 17. The profiled shaft disks 19 and the shell disks 20 located on the coaxial shafts 17, the rotor cylinders 9 of the electric machine 7, the turbine 4 consisting of hollow disks 21. The electromagnetic cylinders of the electric drives 13, 14 pillows and electric machines 7 in the form of hollow cylinders on one side are covered by bases 22 and placed by bases 22 cylinders of rotors 9 of electric machine 7 on coaxial shafts 17 and gray hairs with disks of profiled shaft 19 and shell 20 and cylinder the stator 8 is placed base on the axis 10 and is located concentrically in the electric machine 7 between the two cylinders of the rotors 9 and the cylinders of the stator 15 of the electric drives and the stator 6 of the electromagnetic cushion are placed by the bases on the housing 1. Moreover, the cylinders of the rotors 16 of the electric drives are located between the cylinders of the stator 15 of the electric drive and the stator cylinders 6 of the electromagnetic cushion are concentric, and are placed by the base 22 on the disks 11, 12 located on the axis 10. The electric disks 11, 12 located on the axis 10 and the disks of the profiled shaft 19 of the shell 20 and turbines 21 located on the coaxial shafts 17 are mounted alternately with the possibility of opposite rotation and are provided with blades 5 alternately with an opposite angle of attack, while the disks of the shell 20 are additionally provided outside with blades 23 with an angle of attack, and the hollow disks 21 of the turbine are provided with partitions (not shown) installed with an angle of attack, hollow vanes 24 and channels 25 connecting the hollow disks 21 with hollow vanes 24, while on the hollow vanes 24 there are gauge holes 26 directed to the reactive I'm blowing.
A jet engine operates as follows;
When starting a jet engine, an electric machine in a jet engine is used as an electric motor for starting a jet engine. The voltage of the on-board generator or other source of electricity is supplied to the electromagnets of the stator 8 and rotors 9 of the reversible electric machine. An electromagnetic field is formed on the electromagnets of the cylinders of the stator 8 and rotors 9, 7. Mutually attracted by the opposite poles of the electromagnets of the rotors 9 with the opposite poles of the electromagnets of the stator 8, the opposite rotation of the rotors 9 is created. connected to the disks of the profiled shaft 19 and the shell 20. The opposite rotation of the disks of the profiled shaft 19 and the shell 20 is created placed alternately with blades 5 mounted on each subsequent disk of the profiled shaft 19 and the shell 20 at an opposite angle of attack, as well as the rotation of the blades 23 placed on the outer part of the disks of the shell 20 with an angle of attack. Due to the effect of increasing the speed of the gaseous medium, twisted by the blades 5, 23, and the geometry of the profiled channel, the flow of the gaseous medium is compressed by the compressor 2, the pressure is created in the combustion chamber 3, and in the turbine 4. After reaching the active flow of the gaseous medium and pressure in the combustion chamber 3 fuel is supplied to the combustion chamber 3, ignition is created by a glow plug. The jet stream and the pressure generated during ignition in the combustion chamber 3 presses on the hollow blades 24 of the turbine disks 21, placed alternately on each subsequent disk 21 with an opposite angle of attack. By repelling the blades 24 with the jet stream and pressure, placed alternately on each subsequent disk 21 from each other in opposite directions, rotation of the turbine disks 21 in opposite directions is created. An effective compressor 2 of the jet engine and partition, (not shown) located inside the hollow disks of the turbine 21 at an angle of attack, provides a jet engine with cold gas pressure to cool the hollow disks of the turbine 21 and hollow blades 24 with calibrated openings 26 directed in the direction of the hot jet stream. The gas medium, passing under pressure through the hollow disks 21, channels 25, hollow blades 24 and calibrated openings 26 directed to the jet stream, will create an air cushion that protects the turbine blades 24 from overheating by repelling the cold gas stream from the jet, , repelled by a cold gas jet from a jet stream, will increase the speed and strength of the opposite rotation of the turbine disks 21.
After the jet engine enters the operating mode, the voltage of the on-board generator or other source of electricity is supplied to excite the windings of the electromagnets of the stator 8 and rotors 9 of the electric machine using a reversible electric machine 7 when operating the jet engine as an electric generator. When the rotation is opposite, the opposite fields of the electromagnets of the rotors 9 of the generator, intersecting with the opposite fields of the stator 8, create an electric current. Entering through control systems, electric power is supplied to the electromagnets of the stator cylinders 15 of the electric drives 11, 12 and to the electromagnets of the stator cylinders 6 of the electromagnetic cushion, electromagnetic fields are created. The magnets of the cylinders of the rotors 16, the electric drives mutually attracted with the opposite poles of the stator 15, the electric drives will create a synchronous opposite rotation of the rotors 16, fixed by the base on the disks 11, 12. Electromagnetic fields of the cylinders of the stator 6 of the electromagnetic cushion, mutually repelling with the same fields of the cylinders of the rotors 16 of the electric drive, form an electromagnetic a pillow for the cylinders of the rotors 16 of the electric drive 13, 14, limiting due to the electromagnetic cushion the axial buildup of the disks 13, 14 and the load on the bearings claims 13, 14. Having reached certain turns of the opposite rotation of the blades 5 on the disks 11, 12 located on the axis 10, they will take the opposite angle of attack and, based on the effect of the increase in the speed of the flow, twisted by the blades with the opposite rotation, will create a pressure of the gas medium for the favorable operation of the compressor 2, which, together with the geometry of the profiled channel of the compressor 2 and based on the effect of increasing the flow velocity twisted by the blades 5 located on the disks of the profiled shaft 19 and the shell 20, will increase the energy in the combustion chamber 3, a turbine 4, increasing the jet engine thrust. Part of the blade 5 of the electric drive disks 11, located outside the diameter of the disks of the profiled shaft 19 and the shell 20, will create additional thrust for the jet engine, as well as generate air pressure around the jet stream, limiting the dispersion of the jet stream leaving the turbine 4. Placing the differential gearbox 18 on the axis 10, kinematically connecting the coaxial shafts 17, during operation of the jet engine provides a synchronous opposite rotation of the coaxial shafts 17. The opposite synchronous rotation This makes it possible to evenly redistribute the load on the blades 5.23, 24, disks 11, 12, 19, 20, 21 and coaxial shafts 17 during operation of the jet engine, as well as solve the problem of the gyroscopic effect in the jet engine.
Increasing the thrust of a jet engine and the efficiency of a reversible electric machine 7, as a generating system, will provide, in addition to efficient traction, a jet engine with powerful electric potential, which will expand the capabilities of mounted and on-board electrical equipment and the possibility of using onboard propulsion systems with electric drives as additional thrusters on aircraft and in mechanical engineering . The listed advantages of a jet engine will expand the possibilities of using a jet engine as a modular aircraft with remote control, with the possibility of using thrusters with an electric drive 13, 14 for additional thrust, to use disks with an electric drive 13 of larger diameter, allowing the use of part of the blades located outside the compressor diameter section 2 like blades with a pump or aerodynamic traction. The powerful thrust and electric potential of a jet engine when used on aircraft makes it possible, during a flight, to smoothly switch from the aerodynamic lifting force of a wing to the aerodynamic or pumping thrust of airborne propulsors by an electric drive and to the jet thrust of a jet engine. During the flight and maneuvering in automatic mode, the opportunity is created to combine the lifting force of the aerodynamic wing of aircraft with the aerodynamic or forcing thrust of the onboard propulsors with an electric drive and with the jet thrust of the jet engine. These advantages will exclude the direct dependence of aircraft on the lift force of the aerodynamic wing.
Industrial applicability is provided by modern technologies for the production of jet engines and electric machines.

Claims (1)

  1. A jet engine comprising compressor disks coaxially mounted for rotation, a turbine, a shaped shell, combustion chambers and nozzles, compressor disks and a turbine equipped with vanes mounted with an angle of attack, characterized in that the jet engine contains a streamlined housing, combustion chambers fixed to the housing placed in the housing an electromagnetic pillow consisting of hollow cylinders with stator electromagnets, a reversible electric machine consisting of hollow cylinders with electromagnets stat ora and rotors, an axis fixed to the housing, electric drive disks placed on the axis, consisting of hollow cylinders with stator electromagnets, and of cylinders with rotor magnets, electric machine stator cylinder, coaxial shafts and differential gearbox kinematically connecting coaxial shafts located on coaxial shafts, a profiled shaft and a shell consisting of disks, electric machine rotors cylinders, a turbine consisting of hollow disks, made cylinders of electric drives, electromagnetic cushions and electric machines in the form of hollow cylinders, on one side, the cylinders of the rotors of the electric machine on the coaxial shafts and the joints with the disks of the profiled shaft and the shell are blocked by the bases and the stator cylinder is placed on the axle base and is located in the machine between the two cylinders of the rotors concentrically, and the stator cylinders of the electric drives and electromagnetic the pillows are placed by bases on the housing, while the cylinders of the rotors of the electric drives are concentrically between the cylinders of the stator of the electric drives and the electromagnet cushion, and placed on the base of the disks placed on the axis, with the electric disks placed on the axis and the disks on the coaxial shafts mounted alternately with the possibility of opposite rotation and equipped with blades alternately with the opposite angle of attack, while the shell disks are additionally provided with outside vanes with an angle of attack, and the hollow disks of the turbine are provided inside with partitions installed with the angle of attack, hollow blades and channels connecting hollow disks with hollow blades, while on hollow blades placed gauge holes aimed at the jet stream.
RU2017121758U 2017-06-20 2017-06-20 Jet engine RU177796U1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2017121758U RU177796U1 (en) 2017-06-20 2017-06-20 Jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2017121758U RU177796U1 (en) 2017-06-20 2017-06-20 Jet engine

Publications (1)

Publication Number Publication Date
RU177796U1 true RU177796U1 (en) 2018-03-13

Family

ID=61628760

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2017121758U RU177796U1 (en) 2017-06-20 2017-06-20 Jet engine

Country Status (1)

Country Link
RU (1) RU177796U1 (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2743375A (en) * 1953-09-18 1956-04-24 Louis W Parker Turbo-generator
US4253031A (en) * 1978-05-27 1981-02-24 Robert Bosch Gmbh Directly driven dynamo electric machine-gas turbine generator structure
EP0305763A1 (en) * 1987-08-06 1989-03-08 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Energy-delivering installation
RU2014482C1 (en) * 1990-12-29 1994-06-15 Варюхин Александр Сергеевич Device for control of gas-turbine engine thrust
US5376827A (en) * 1993-05-27 1994-12-27 General Electric Company Integrated turbine-generator
GB2288642A (en) * 1994-04-19 1995-10-25 David Johnston Burns Air driven generator

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2743375A (en) * 1953-09-18 1956-04-24 Louis W Parker Turbo-generator
US4253031A (en) * 1978-05-27 1981-02-24 Robert Bosch Gmbh Directly driven dynamo electric machine-gas turbine generator structure
EP0305763A1 (en) * 1987-08-06 1989-03-08 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Energy-delivering installation
RU2014482C1 (en) * 1990-12-29 1994-06-15 Варюхин Александр Сергеевич Device for control of gas-turbine engine thrust
US5376827A (en) * 1993-05-27 1994-12-27 General Electric Company Integrated turbine-generator
GB2288642A (en) * 1994-04-19 1995-10-25 David Johnston Burns Air driven generator

Similar Documents

Publication Publication Date Title
EP2985901B1 (en) Hybrid electric pulsed-power propulsion system for aircraft
US20150345501A1 (en) Electromagnetic Propulsive Motor
RU109233U1 (en) Turbine
EP2977314B1 (en) Propeller in-hub power generation and control
US10967984B2 (en) Hybrid aircraft
RU177796U1 (en) Jet engine
JP2017534021A (en) Exhaust section for aircraft gas turbine engines
CN107701312A (en) A kind of hypersonic jets
CN103629011B (en) Motor
US20110268581A1 (en) Propulsion system and method
EP3588750A1 (en) Electric fan
CN112368207A (en) Aircraft propulsion system and aircraft powered by such a propulsion system incorporated in the rear part of the aircraft fuselage
GB2565886B (en) Electric engine
US10125609B2 (en) Device for obtaining mechanical work from a non-thermal energy source (variants)
US9677415B2 (en) Gas turbine electrical machine arrangement
CN107842442A (en) A kind of aero-engine
CN203547987U (en) Engine
BG110826A (en) Gasterwork engine
RU2276739C1 (en) Method and device for creating reactive thrust made in form of centrifugal ramjet engine
RU2379523C2 (en) Aircraft propfan engine
JP2020083062A (en) Power supply device and air vehicle
CN205064122U (en) Aviation air injection motor
JP2020520429A (en) Method for constructing an engine or motor housed in a cylindrical casing
RU2307257C2 (en) Method of operation of supersonic combination air-space jet power plant
RU2013630C1 (en) Aircraft engine