CN113357046A - Turbo-electric aircraft engine - Google Patents
Turbo-electric aircraft engine Download PDFInfo
- Publication number
- CN113357046A CN113357046A CN202010168392.8A CN202010168392A CN113357046A CN 113357046 A CN113357046 A CN 113357046A CN 202010168392 A CN202010168392 A CN 202010168392A CN 113357046 A CN113357046 A CN 113357046A
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- China
- Prior art keywords
- stator
- fixed
- steel sheet
- silicon steel
- bolts
- Prior art date
- Legal status (The legal status 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 status listed.)
- Pending
Links
- 229910000976 Electrical steel Inorganic materials 0.000 claims abstract description 30
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 28
- 239000003921 oil Substances 0.000 claims description 35
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 20
- 229910052799 carbon Inorganic materials 0.000 claims description 20
- 239000004020 conductor Substances 0.000 claims description 18
- 229910052802 copper Inorganic materials 0.000 claims description 14
- 239000010949 copper Substances 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 8
- 210000002310 elbow joint Anatomy 0.000 claims description 7
- 244000185238 Lophostemon confertus Species 0.000 claims description 6
- 210000001503 joint Anatomy 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 238000004804 winding Methods 0.000 abstract description 9
- 238000000034 method Methods 0.000 abstract description 3
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 239000010687 lubricating oil Substances 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 230000006698 induction Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 230000003203 everyday effect Effects 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 238000003915 air pollution Methods 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
A method for combining a motor and a turbine aero-engine is adopted, a silicon steel sheet is installed on a shaft, a plurality of grooves are formed in the silicon steel sheet, copper wire windings are installed in the grooves and form a magnetic field after being electrified, the silicon steel sheet is installed on the inner diameter of a stator, the grooves are formed in the silicon steel sheet, the copper wire windings are installed in the grooves and form the magnetic field after being electrified, 16 groups of turbine blades are installed on the outer diameter of the stator, the rear 6 groups of turbine blades are compression bin blades and compress air generated by the front turbine blade group into compressed air with pressure, the diameter of a check ring is larger than that of the check ring, and the process from the 5 th group to the 9 th group of the check ring is that the air speed is converted into the compressed air. When current passes through the copper wire winding on the shaft and the copper wire winding on the stator, a magnetic field is generated, and the stator drives the turbine blade group to rotate to generate air flow when the two magnetic fields are cut mutually.
Description
The technical field is as follows:
the invention relates to a turbine electric aircraft engine, which is a novel technical aircraft engine adopting an electric driving mode and realizing that the turbine engine can generate power.
Background art:
every country in the world has hundreds of thousands of airplanes to fly in the air every day, the airplanes are all fuel oil engines, nearly millions of people are transported every day, the burning aviation fuel oil can reach more than 150 thousands of tons, the second killer of air pollution is realized, a large amount of petroleum energy is wasted, the environmental hazard is brought to human beings, the hidden danger is brought to the safety of a large number of passenger planes flying for a long time and in a month-to-month period, once the passenger planes have accidents, the serious consequences caused by burning due to leakage of a large amount of fuel oil are mostly destroyed and people die.
The invention content is as follows:
in order to solve the problem that an aircraft engine does not burn fuel oil and does not bring pollution to the environment, a method for combining a motor and a turbine aircraft engine is adopted, an asynchronous induction type motor is adopted, a silicon steel sheet is arranged on a rotor shaft, a plurality of grooves are formed in the silicon steel sheet, copper wire windings are arranged in the grooves, an induction magnetic field can be generated after the silicon steel sheet is electrified, the silicon steel sheet is arranged on the inner diameter of a stator, a plurality of grooves are formed in the silicon steel sheet, the copper wire windings are arranged in the grooves, a magnetic field can be formed after the silicon steel sheet is electrified, the copper wire windings and the induction magnetic field generate magnetic force cutting with the induction magnetic field on the rotor, torque is generated, then the stator rotates, 16 groups of turbine blades and 15 gaskets are arranged on the outer diameter of the stator, when current passes through the copper wire windings on the shaft and the copper wire windings on the stator, the two magnetic fields are mutually cut, the stator drives the turbine group to rotate to push air to flow to generate power, and a turbine electric aircraft engine shell is arranged on the outer diameter of the turbine blades, the two ends of the shell are fixed with the rear support of the front support chain through bolts and nuts, the front support and the center of the rear support are fixed on the main shaft and fixed through fixing nuts, the bearing seat is fixed on the stator through bolts, a bearing in the bearing seat is installed on a rotor shaft, the stator can rotate, the stator drives turbine blades to rotate at a high speed in the shell to push gas to generate strong thrust, the turbine electric aircraft engine has the leading technical world, the turbine electric aircraft engine has the core technology of the turbine electric aircraft engine, the turbine electric aircraft engine is the combination of a motor and the aviation technology, the manufacturing cost is low, the economic benefit is high, the service life is long, the maintenance is convenient, and the turbine electric aircraft engine does not burn any fuel, is a green, clean and pollution-free environment-friendly passenger plane, and protects the safety of passengers to the maximum extent.
The technical scheme adopted by the invention for solving the technical problems is as follows: the guide cover is fixed on the shell by bolts and nuts, the guide cone is fixed on the front support and the rear support by bolts, the central shaft of the front support is fixed on the main shaft and is fixed by fixing nuts, the outer diameter of the guide cone is installed on the shell and is fixed by bolts and nuts, the joint is connected with a bent joint and is fixed on the end surface of the main shaft and leads to the bearing, one end of the bent joint is connected with a copper pipe, the other end of the copper pipe is connected with an oil tank and an oil pump to form a circulating system with the bearing, a fixing ring is fixed on the main shaft by bolts, the position of the bearing is controlled, the inner diameter of the bearing is installed on the main shaft, the outer diameter of the bearing is installed in a bearing seat and is fixed by a bearing cover, two ends of the bearing seat are sealed by a sealing ring to prevent lubricating oil in the bearing from leaking, the bearing seat is fixed on the stator by bolts, a silicon steel sheet is fixed by a key pin, a plurality of copper coils are installed in the middle of the silicon steel sheet, the inner diameter of the stator is installed with the silicon steel sheet, fixing with key pin, installing several copper coils in the middle of silicon steel sheet, connecting the wire of coil with copper conductor, connecting carbon brush with power supply connector on power supply box, installing carbon brush in carbon brush box, fixing with bolt on main shaft, installing copper conductor on conductor plate, fixing with bolt on fixing frame, fixing with bolt on stator, installing backing plate on stator external diameter, fixing with bolt on blade seat, installing blade assembly on stator external diameter, fixing with bolt on backing ring, installing backing ring on stator external diameter, fixing blade assembly with bolt, so on 16 sets of blade assembly and 15 backing rings are installed on stator external diameter, fixing with bolt, fixing baffle on blade assembly with bolt, fixing shell with two pieces, fixing with bolt, spring pad, spacer and nut, connecting two ends with front support and rear support, fixing with spring pad, The back support shaft is arranged on the main shaft and is fixed by a fixed nut, the back support shaft is also provided with a flow guide cone and a flow guide cover which are fixed by a bolt, a bearing is arranged in a bearing seat and is also arranged on the main shaft, a bearing cover is connected with the bearing seat and is fixed by a bolt, the bearing cover and the main shaft at the two ends of the bearing seat are sealed by sealing rings to prevent lubricating oil in the bearing seat from seeping out, the end surface of the back shaft is provided with a connector which is connected with a bent connector, the bent connector is connected with an oil pipe, the other end of the oil pipe is connected with an oil tank and an oil pump to form a circulating system to ensure the circulation of the lubricating oil in the bearing, a coil on the stator is connected with a lead, the lead is connected with a copper conductor, a carbon brush is contacted with the copper conductor, the carbon brush is arranged in a carbon brush box, the lead on the carbon brush is connected with a power supply connector on the power supply box, an external power supply enters a stator coil through the carbon brush to generate an electromagnetic field on the stator silicon steel sheet, every blade subassembly increases a set of thrust that all can increase turbine electromotive force engine, every group increases a blade and all can increases the speed of making wind, the wind speed is by the area of blade, the angle, speed decision, the wind speed volume is by blade length on the blade subassembly, the area, the blade quantity decides, a blade rotation circle, make the blade area amount of wind of circle area, there are 36 blades on the blade subassembly, just make the amount of wind of the blade area of 36 circle areas, the more blades on the blade group, the more the amount of wind of making, the more the blade group, the more the revolution produces thrust more.
The invention has the advantages that the combination of the motor and the turbine engine is realized, the outer diameter of the stator is provided with the blade seat and the gasket, the blade seat is provided with the blade, and when the external power supply is connected, the stator starts to rotate to drive the blade to rotate so as to push air to move and generate power.
Drawings
The invention is further described with reference to the following figures and examples.
FIG. 1 is a front view
FIG. 2A-A sectional view
FIG. 3, B-B is a sectional view
FIG. 4 is a front view
FIG. 5.C partial view
FIG. 6.D partial view
Detailed Description
In fig. 1, a bolt, 2, an oil tank, 3, an oil pump, 4, an oil inlet pipe, 5, a power supply box, 6, a bolt, 7, an oil return pipe, 8, a base, 9, a bolt, 10, a bolt, 11, a front bracket, 12, a dome, 13, a guide cone, 14, an oil inlet pipe, 15, a bent joint, 16, a joint, 17, a bent joint, 18, a joint, 19, an oil return pipe, 20, a fixing nut, 21, a seal ring, 22, a fixing ring, 23, a rear bracket, 24, a thrust bearing, 25, a seal ring, 26, a seal ring, 27, a bolt, 28, a bearing, 29, a bearing bracket, 30, a seal ring, 31, a bolt, 32, a bolt, 33, a baffle, 34, a carbon brush box, 35, a bolt, 36, a bolt, 37, a carbon brush bracket, 38, a carbon brush, 39, a copper conductor, 40, a conductor plate, 41, a conductor bracket, 42, a bolt 43, a lead wire, 44, a bolt, 45, a power supply connector, 46. power supply box 47, gasket 48, bolt 49, housing 50, gasket 51, stator 52, stator silicon steel sheet 53, stator coil 54, rotor coil 55, rotor silicon steel sheet 56, spindle 57, nut 58, gasket 59, spring washer 60, bolt 61, rotor key 62, stator key 63, blade 64, seal ring 65, bearing 66, stator 67, bolt 68, bolt 69, the bearing comprises a backing plate 70, an oil pipe 71, a bearing seat 72, a bolt 73, a thrust bearing 74, a nut 75, a bolt 76, a sealing element 77, a fixing ring 78, a bearing cover 79, a bolt 80, a sealing ring 81, a front support 82, a bolt 83, a fixing nut 84, an oil pipe 85, a joint 86, a bent joint 87, a joint 88, a bent joint 89, an oil pipe 90, a guide cone 91 and a guide cover.
The oil tank (2) is fixed on the bottom plate (8) by a bolt (1), the oil pump (3) is connected with the oil inlet pipes (4) and (14), the oil inlet pipes (4) and (14) are connected with the elbow joints (17) and (86), the elbow joints are connected with the joints (16) and (87), the joint (17) is fixed on the rear end surface of the main shaft (56), the oil return pipes (7) and (19) are connected with the oil tank (2), the other ends of the oil return pipes are connected with the elbow joint (15), the elbow joint (15) is connected with the joints (16) and (18), the joints (16) and (18) are fixed on the rear end surface of the main shaft (65), a closed loop system is formed by a bearing cavity and the oil inlet pipes (4) and (14), oil flows in the system by the oil pump (3) to lubricate and cool the bearing, the shaft part of the rear bracket (23) is arranged on the main shaft (56) and is fixed by a fixing nut (20),guide tubeThe flow cover (12) and the rear support (23) are fixed on the end face of the shell (49) by bolts and nuts, the flow guide cone (13) is fixed on the rear support (23) by bolts, the power supply box (5) is fixed on the base (8) by bolts (6) and (44), the power supply boxes (5) and (46) are provided with power supply connectors (45) which are connected with wires (43) and pass through copper conductors (39) and carbon brushes (38), the carbon brush box (34) is connected with the power supply connectors (45) by the wires, the carbon brush frame (37) is fixed on the main shaft (56) by bolts (35), the copper conductors (39) are arranged on the conductor plate (40), the conductor plate (40) is fixed on the fixed frame (41) by bolts (42) and fixed on the stators (51) and (66) by bolts (36), and the thrust bearing (24) of the bearing (28) is arranged in the bearing seat (29), is mounted on a main shaft (56) and fixed on the main shaft (56) by a fixed ring (22), a bearing seat (29) is fixed on stators (51), (66) by a bolt (31), a bearing cover (25) is fixed on the bearing seat (29) by a bolt (27), sealing rings (26), (21), (29) (, 30) are sealed to prevent lubricating oil from seeping out, a vane (63) is mounted on a vane seat (46), the vane seat (46) is mounted on the stator (51), a gasket (50) is fixed on the vane seat (46) by a bolt (48) and fixed by a stator key (62),the middle of each two of 16 blade groups (46) is separated by a gasket (47) and fixed by a bolt (68), baffle plates (33) and (69) are arranged at two ends of each blade group and fixed by bolts (68) and (67), a stator silicon steel sheet (52) is arranged on the inner diameter of a stator (51) and fixed by a stator key (62), a stator coil (53) is arranged in a slot of the stator silicon steel sheet (52), a rotor coil (54) is arranged in a slot of a rotor silicon steel sheet (55), the rotor silicon steel sheet (55) is fixed by a rotor key (61), a bearing seat (71) is fixed at the front end of the stator (51) by a bolt (72), a thrust bearing (73) of a bearing (65) is arranged in the bearing seat (71) and arranged at the front end of a main shaft (56) and positioned by a fixed ring (77), a nut (57), a gasket (58), a spring pad (59) and a bolt (60) connect two shells together, a bearing cover (78) is fixed on the bearing seat (71) by a bolt (79), the sealing rings (64), (76) and (80) play a role of sealing and prevent the leakage of lubricating oil, the shaft of the front bracket (81) is arranged at the front end of the main shaft (56) and is fixed by a fixing nut (83), the joint (85) is arranged at the front end of the main shaft (56), is linked with a bent joint (86), the bent joint (86) is linked with an oil return pipe (84), the other end of the oil return pipe (84) is linked with an oil tank (2), a joint (87) is arranged at the front end of a main shaft (56), the guide cone is connected with an elbow joint (88), the other end of the elbow joint (88) is connected with an oil pipe (89), the other ends of the oil pipes (89) and (70) are connected with an oil pump (3) to form a complete loop system, the guide cone (90) is fixed on a front support (81) through bolts (10) and (82), and the guide cover (91) and the front support (81) are fixed at the front end of a shell (49) through a nut (74) and a bolt (75).
Claims (7)
1. An electric turbine aircraft engine is composed of casing, guide cones at both ends of casing, front and back supports fixed to front and back supports by bolts and nuts, front and back bearings installed in bearing seats and sealed by bearing covers, front and back mainshafts sealed by sealing rings at the contact position with mainshaft, locating ring, silicon steel sheet and coil installed to rotor, stator connected to bearing seats and fixed by bolts, silicon steel sheet installed to inner diameter of stator, copper wire coil installed to silicon steel sheet, blade seat and blade seat fixed by key, multiple blades installed to blade seat, turbine blade set consisting of multiple turbine blade sets and multiple retaining rings installed to outer diameter of stator, and carbon brush box installed to carbon brush holder, the carbon brush frame is fixed on the rotor shaft through bolts, the copper conductor and the conductor plate are connected with the conductor plate and the fixed frame, the conductor plate and the fixed frame are fixed through bolts, the other end of the fixed frame is fixed on the stator through bolts, a stator coil wire is connected with the copper conductor, the copper conductor is connected with the carbon brush, the carbon brush is installed in the carbon brush box and is connected with a power supply connector of the power supply box through a wire, and the front connector, the rear connector, the bent connector, the guide pipe, the oil tank, the oil pump, the front connector and the rear connector are installed on two end faces of the main shaft and are communicated with an inner cavity of the bearing seat to form a closed circulation system.
2. The turbine electromotive force aircraft engine of claim 1, wherein: the diversion cone is fixed on the front bracket by bolts, the diversion cone is fixed on the rear bracket by bolts, and the front bracket and the rear bracket are fixed at two ends of the shell by bolts.
3. The turbine electromotive force aircraft engine of claim 1, wherein: the bearing is installed in the bearing seat, the bearing cover is connected with the bearing seat through bolts, the bearing is installed on the rotor shaft, and the other part of the bearing seat is fixed at the ends of the front stator and the rear stator through bolts to form a motor.
4. The turbine electromotive force aircraft engine of claim 1, wherein: the stator is provided with a silicon steel sheet on the inner diameter, a copper wire coil is arranged on the silicon steel sheet, a blade seat and a check ring are arranged on the outer diameter of the stator, the check ring and the blade seat are fixed together by bolts, and a plurality of blades are arranged on the blade seat.
5. The turbine electromotive force aircraft engine of claim 1, wherein: the lower part of the blade is a trapezoid tooth rectangle, the blade seat is provided with a trapezoid tooth rectangle opposite to the blade, and the trapezoid tooth rectangle of the blade is just embedded on the blade seat.
6. The turbine electromotive force aircraft engine of claim 1, wherein: the front and rear joints, the elbow joint, the conduit, the oil tank, the oil pump, the front and rear joints are arranged on two end faces of the main shaft and communicated with the inner cavity of the bearing seat to form a closed circulation system.
7. The turbine electromotive force aircraft engine of claim 1, wherein: the rotor is provided with a silicon steel sheet, a copper wire coil is installed in a silicon steel sheet groove, the inner diameter of the stator is provided with the silicon steel sheet, the silicon steel sheet is provided with the copper wire coil in a groove, the outer diameter of the stator is provided with a plurality of check rings and a plurality of blade assemblies, when the stator is electrified, a magnetic field is generated and generates an induced current with the copper wire coil on the rotor to generate a magnetic field, and the two magnetic fields are tangent to each other to ensure that the stator rotates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010168392.8A CN113357046A (en) | 2020-03-06 | 2020-03-06 | Turbo-electric aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010168392.8A CN113357046A (en) | 2020-03-06 | 2020-03-06 | Turbo-electric aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113357046A true CN113357046A (en) | 2021-09-07 |
Family
ID=77524345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010168392.8A Pending CN113357046A (en) | 2020-03-06 | 2020-03-06 | Turbo-electric aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113357046A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103618422A (en) * | 2013-12-23 | 2014-03-05 | 中国航天空气动力技术研究院 | Electromagnetic drive fan device |
| WO2015001268A2 (en) * | 2013-07-04 | 2015-01-08 | Valeo Equipements Electriques Moteur | Automotive vehicle starter |
| CN105680596A (en) * | 2014-12-03 | 2016-06-15 | 现代自动车株式会社 | Rotor structure of wrsm motor |
| CN108468602A (en) * | 2018-05-18 | 2018-08-31 | 北京航空航天大学 | A kind of variable Brayton cycle aero-engine of multiple shafting distribution |
| CN109391063A (en) * | 2017-08-07 | 2019-02-26 | 通用电气公司 | Electric propulsion system, motor and its assemble method for delivery vehicle |
| US10690000B1 (en) * | 2019-04-18 | 2020-06-23 | Pratt & Whitney Canada Corp. | Gas turbine engine and method of operating same |
-
2020
- 2020-03-06 CN CN202010168392.8A patent/CN113357046A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015001268A2 (en) * | 2013-07-04 | 2015-01-08 | Valeo Equipements Electriques Moteur | Automotive vehicle starter |
| EP3017526A2 (en) * | 2013-07-04 | 2016-05-11 | Valeo Equipements Electriques Moteur | Automotive vehicle starter |
| CN103618422A (en) * | 2013-12-23 | 2014-03-05 | 中国航天空气动力技术研究院 | Electromagnetic drive fan device |
| CN105680596A (en) * | 2014-12-03 | 2016-06-15 | 现代自动车株式会社 | Rotor structure of wrsm motor |
| CN109391063A (en) * | 2017-08-07 | 2019-02-26 | 通用电气公司 | Electric propulsion system, motor and its assemble method for delivery vehicle |
| CN108468602A (en) * | 2018-05-18 | 2018-08-31 | 北京航空航天大学 | A kind of variable Brayton cycle aero-engine of multiple shafting distribution |
| US10690000B1 (en) * | 2019-04-18 | 2020-06-23 | Pratt & Whitney Canada Corp. | Gas turbine engine and method of operating same |
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