CN117022643B - Electric ducted power fan device and aircraft - Google Patents
Electric ducted power fan device and aircraft Download PDFInfo
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- CN117022643B CN117022643B CN202310769643.1A CN202310769643A CN117022643B CN 117022643 B CN117022643 B CN 117022643B CN 202310769643 A CN202310769643 A CN 202310769643A CN 117022643 B CN117022643 B CN 117022643B
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- support shaft
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- 238000004804 winding Methods 0.000 claims description 18
- 238000001816 cooling Methods 0.000 claims description 11
- 239000012530 fluid Substances 0.000 claims description 8
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 239000003921 oil Substances 0.000 description 49
- 239000010687 lubricating oil Substances 0.000 description 11
- 238000010586 diagram Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 238000007789 sealing Methods 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 230000005426 magnetic field effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000020347 spindle assembly Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
本发明公开了一种电动涵道动力风扇装置和飞行器，属于短距离起降飞行器技术领域，该一种电动涵道动力风扇装置和飞行器，包括支撑机匣，包括壳体部，所述壳体部限定一大致成圆柱状的流通区间；电机静子组件，所述电机静子组件配置为基于外部控制系统产生不断变化的磁场；转子支撑轴组件，包括沿轴线O设置的转子支撑轴，且所述转子支撑轴安装于所述支撑匣上；风扇转子组件。通过设置由电机静子组件和风扇转子组件的部分构成的电机结构，将风扇转子组件中的冠部和电机转子结合，同时电机静子位于叶冠外、并嵌入风扇机匣为一体，提高了空间和质量利用率。
The present invention discloses an electric ducted power fan device and an aircraft, belonging to the technical field of short-distance take-off and landing aircraft. The electric ducted power fan device and the aircraft include a support casing, a shell portion, and the shell portion defines a substantially cylindrical flow zone; a motor stator assembly, and the motor stator assembly is configured to generate a continuously changing magnetic field based on an external control system; a rotor support shaft assembly, including a rotor support shaft arranged along an axis O, and the rotor support shaft is installed on the support casing; and a fan rotor assembly. By providing a motor structure composed of a motor stator assembly and a part of a fan rotor assembly, the crown portion and the motor rotor in the fan rotor assembly are combined, and at the same time, the motor stator is located outside the blade crown and embedded in the fan casing as a whole, thereby improving space and mass utilization.
Description
Technical Field
The invention belongs to the technical field of short-distance take-off and landing aircrafts, and particularly relates to an electric bypass power fan device and an aircraft.
Background
At present, the power technology for the vertical take-off and landing aircraft mainly comprises a tilting rotor technology, an engine nozzle steering technology, a mechanical fan technology, a distributed electric propeller technology and the like, and the power device for the small and medium-sized vertical take-off and landing aircraft is still the distributed electric propeller/fan technology, is generally regarded as a propeller without a duct and is regarded as a fan with a duct;
Most of motor forms in the existing aircraft power devices adopt the existing motor forms, the space and quality utilization rate is low, and the power density is low.
Disclosure of Invention
The invention aims to provide an electric ducted power fan device and an aircraft, which are used for solving the problems of the prior power device and the prior aircraft in the use process.
To achieve the above object, in one aspect, the present invention provides an electric ducted power fan apparatus, including a supporting casing, including a housing portion defining a substantially cylindrical circulation zone;
the motor stator assembly is arranged in the circulation interval and is arranged on the supporting casing, and the motor stator assembly is configured to generate a continuously-changing magnetic field based on an external control system;
a rotor support shaft assembly comprising a rotor support shaft disposed along an axis O, and the rotor support shaft is mounted on the support box;
the fan rotor assembly is mounted on the rotor supporting shaft and is configured to rotate around an axis O, the fan rotor assembly comprises a plurality of blades uniformly arranged in the circumferential direction and a crown part fixed on the radial outer side of the blades, and the fan rotor assembly further comprises a plurality of permanent magnets fixed on the outer surface of the crown part and uniformly arranged in the circumferential direction.
Preferably, the supporting casing further comprises a second surrounding portion which is approximately cylindrical and a first surrounding portion which is arranged on the radial outer side of the second surrounding portion, the first surrounding portion and the second surrounding portion are connected through a plurality of bearing support plates which are evenly arranged in the circumferential direction, and the rotor support shaft is installed through a first installation structure on the second surrounding portion.
Preferably, the fan device further comprises an accessory bin fairing mounted at one axial end of the housing part, and the accessory bin fairing, the first surrounding part and the housing part jointly enclose a second accommodating section communicated with the communicating area.
Preferably, the motor stator assembly includes:
the iron core assembly sheet is provided with an outer wall part which is approximately in the shape of an annular sheet and a plurality of T-shaped parts which are fixed on the inner surface of the outer wall part;
The stator winding comprises a plurality of winding units wound on the T-shaped part, and interval sections exist between adjacent winding units;
The cooling pipeline assembly comprises pipeline units arranged in the interval section, and the pipeline units are provided with inlets and outlets;
The pipeline unit is installed on the end plate, the other side of the pipeline unit is provided with a fluid groove, and the end plate is provided with a cable hole and a plurality of installation holes.
Preferably, the fan rotor assembly further comprises a disc portion located radially inwards of the crown, and a first oil return section is formed between an inner wall of the disc portion and an outer wall of the rotor support shaft.
Preferably, an oil inlet channel arranged along the axis O is formed in the rotor support shaft, and the oil inlet channel is communicated with the first oil return section through a radial small hole formed in the rotor support shaft.
Preferably, the rotor support shaft comprises a middle section, a first section and a second section which extend outwards from two ends of the middle section in an axial direction, the rotor support assembly further comprises two bearings mounted on the middle section, a second mounting structure for mounting the bearings is formed on the disc body, and at least one of the two bearings is a ball bearing.
Preferably, the fan device further comprises a rotating shaft assembly, and the rotating shaft assembly comprises a first rotating shaft and a second rotating shaft which are installed on two radial sides of the supporting casing and have axes coincident.
Preferably, the first rotating shaft comprises a shaft column body and a hollow cable channel, the second rotating shaft comprises an outer shaft column and an inner shaft column, the inner shaft column is connected with the accessory bin fairing, an oiling channel is formed in the inner portion of the inner shaft column in a hollow mode, and a second oil return section is formed between the outer shaft column and the inner shaft column.
In another aspect, the present invention also provides an aircraft having the above fan device, and the fan device is configured to be rotatably adjustable in direction.
Compared with the prior art, the invention has the beneficial effects that:
1. According to the application, through the motor structure formed by the motor stator component and the part of the fan rotor component, the crown part in the fan rotor component is combined with the motor rotor, and meanwhile, the motor stator is positioned outside the blade crown and is embedded into the fan casing as a whole, so that the space and the quality utilization rate are improved;
2. According to the application, by arranging the accessory bin fairing and combining the lubricating oil channels designed in other parts in the fan device, the lubrication and cooling of parts such as a bearing, a motor stator and the like in the fan device can be realized, and the service life of the device is prolonged;
3. according to the application, through arranging the rotating shaft assembly, the angular adjustment of the fan device on the aircraft is realized, and vector thrust can be generated, so that the functions of vertical lifting, stable flat flight, complex maneuvering flight and the like are controlled and realized.
Drawings
FIG. 1 is a schematic view of a conventional propeller;
FIG. 2 is a general system diagram of a fan assembly according to the present invention;
FIG. 3 is a schematic view of a casing assembly according to the present invention;
FIG. 4 is a schematic diagram of a stator assembly of a motor according to the present invention;
FIG. 5 is a schematic diagram of a motor stator assembly according to the present invention;
FIG. 6 is a schematic diagram of a motor stator assembly according to the present invention;
FIG. 7 is a schematic view of a fan rotor assembly according to the present invention;
FIG. 8 is a schematic view of a rotor support assembly according to the present invention;
FIG. 9 is a schematic view of a spindle assembly according to the present invention;
FIG. 10 is a schematic view of the overall structure of the aircraft of the present invention;
FIG. 11 is a schematic view of a motion state structure of an aircraft according to the present invention;
fig. 12 is a schematic view of another motion state structure of the aircraft of the present invention.
100. The motor comprises a housing assembly, a supporting housing, a housing part, a supporting part, a first surrounding part, a second surrounding part, a motor fairing, a first accommodating section, an accessory bin fairing, a second accommodating section, a bearing support plate, a first mounting structure, a motor torsion preventing raised line, a motor rectifying cone and a tail rectifying cone, wherein the housing assembly comprises the housing assembly, the supporting housing, the housing part, the supporting housing, the supporting part, the housing, the motor torsion preventing raised line, the motor fairing, the motor rectifying cone and the motor rectifying cone;
200. Motor stator assembly, 201, stator winding, 202, winding unit, 203, iron core assembly piece, 203a, outer wall part, 203b, T-shaped part, 204, cooling pipeline assembly, 205, pipeline unit, 206, end plate piece, 207, first hole group, 208, second hole group, 209, hole unit group, 210, fluid tank, 211, total inlet, 212, total outlet, 213, cable hole;
300. Fan rotor assembly, 301, bladed disk member, 301a, disk body, 301b, crown, 301c, blade portion, 302, permanent magnet, 303, second mounting structure, 304, fan fairing
400. The device comprises a rotor support assembly, a rotor support shaft, 401a, a first section, 401b, a middle section, 401c, a second section, 402, a bearing, 403, a sealing structure, 404, a compression nut, 405, a sealing cover plate, 405a, an oil inlet, 405b and an oil return port;
500. The device comprises a rotating shaft assembly, a first rotating shaft, a 502, a shaft column, a 503, a cable channel, a 504, a second rotating shaft, a 505, an inner shaft column, a 506 and an outer shaft column;
600. The oil injection channel, 601, an oil inlet channel, 602, a bearing cavity, 603, a first oil return section, 604, an oil return hole, 605, an intermediate oil duct, 606 and a second oil return section.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 2, an electric ducted power fan apparatus, a main body is composed of a casing assembly 100, a motor assembly, a rotor support shaft 401 assembly, and a fan assembly, wherein the casing assembly 100 is composed of a mounting carrier for the rest of the components, i.e., the motor assembly, the rotor support shaft 401 assembly, and the fan assembly are mounted based on the casing assembly 100;
Specifically, referring to fig. 3, the casing assembly 100 main body is composed of a supporting casing 101, a motor fairing 106, an accessory nacelle fairing, and a tail cone 114, wherein the supporting casing 101 is composed of a mounting carrier for the motor fairing 106, the accessory nacelle fairing, and the tail cone 114, referring to fig. 3, the supporting casing 101 includes a housing portion 102 and a supporting portion 103, wherein the housing portion 102 is a substantially cylindrical member having a substantially cylindrical flow-through section formed therein, specifically, the housing portion 102 is formed by a substantially rectangular cross section around an axis O, the housing portion 102 has a first end and a second end in an axial direction, wherein a mounting flange of the motor fairing 106 is formed on the first end of the housing portion 102 member, the motor fairing 106 is fitted on the first end in the axial direction of the housing portion 102 via the mounting flange, and a substantially annular first accommodation section 108 is formed in the motor fairing 106, and the first accommodating section 108 is formed with an opening at one end facing the housing 102, returning to fig. 3, continuing to describe the composition of the supporting casing 101, the supporting section 103 of the supporting casing 101 is offset from the housing 102 in the axial direction, that is, at least part of the supporting section 103 is located outside the above-mentioned circulation section, specifically, the supporting section 103 includes a first surrounding section 104 and a second surrounding section 105 which are arranged at intervals in the radial direction, the first surrounding section 104 and the second surrounding section 105 are both substantially cylindrical members, the first surrounding section 104 and the second surrounding section 105 are connected by a plurality of bearing support plates 111, the plurality of bearing support plates 111 are arranged at equal intervals in the circumferential direction, for example, the bearing support plates 111 are provided with three, the interval 120 ° between adjacent bearing support plates 111, and the angle of the coaxial line O of the single bearing support plate 111 is an acute angle, that is, the single bearing support plate 111 is arranged in a direction deviating from the radial direction, referring to fig. 3, a mounting edge is formed on the second end of the housing 102, the accessory bin fairing 109 is mounted by the mounting edge and the first surrounding portion 104 of the supporting portion 103, and the accessory bin fairing 109 and the first surrounding portion 104 jointly enclose a second substantially annular accommodating section 110, the second accommodating section 110 is formed with an opening at one end facing the housing 102, and the circulating section and the second accommodating section 110 are communicated at the opening position;
further, referring to fig. 3, the bearing support plate 111 of the supporting casing 101 further includes an intermediate oil duct 605, where an extending direction of the intermediate oil duct 605 is substantially the same as an extending direction of the bearing support plate 111, that is, the intermediate oil duct 605 is disposed along the bearing support plate 111 to form a fluid (e.g., lubricating oil) circulation channel between the second accommodating section 110 and an oil inlet 405a and an oil outlet 405b described later.
Referring to fig. 3, a mounting flange is formed at an end of the second surrounding portion 105 of the supporting portion 103 axially far from the housing portion 102, and correspondingly, the tail cone 114 is mounted on the second surrounding portion 105 through the mounting flange and is capable of rectifying a rotor supporting rear flow field to reduce resistance, and a first mounting structure 112 is provided on an inner surface of the second surrounding portion 105 for realizing mounting of a rotor supporting shaft 401 to be described later;
returning to fig. 3, the supporting casing 101 further includes a motor torsion stop rib 113 extending along the axis O and located radially inward of the housing 102;
Referring to fig. 4-6, a schematic structural diagram of a motor stator assembly 200 is shown, the motor stator assembly 200 is integrally disposed in the circulation zone and is mounted by a supporting casing 101, and a main body of the motor stator assembly 200 is formed by stator windings 201, The stator winding 201 is adjusted by an external control system to form a magnetic field which changes continuously, the iron core assembly 203 can strengthen the magnetic field effect and bear the reaction force of magnetic force, the cooling pipeline assembly 204 is configured to cool the stator winding 201 and the like, specifically, the iron core assembly 203 comprises an outer wall part 203a formed into a ring-shaped sheet body and a plurality of T-shaped parts 203b uniformly arranged on the inner surface of the outer wall part 203a and having a T-shaped section, wherein the outer wall part 203a and the T-shaped parts 203b are integrally formed, more specifically, the T-shaped parts 203b comprise a first part extending along the radial direction and a second part extending from the inner side end of the first part to two sides (refer to figure 5), the stator winding 201 comprises a plurality of winding units 202, the single winding unit 202 is wound on the outer side of the first part, i.e. the single winding unit 202 is formed as a rectangular annular unit, the winding unit 202 is limited in the height direction (i.e. radial direction) by the second portion, and adjacent winding units 202 are spaced in the circumferential direction, i.e. adjacent sides of adjacent winding units 202 are formed with spaced intervals, the cooling pipe assembly comprises a pipe unit 205 arranged in the spaced intervals, the single pipe unit 205 is a "U" -shaped pipe, the cooling pipe assembly further comprises an end plate 206, the end plate 206 is arranged at one axial end of the iron core assembly piece 203 and is arranged close to the accessory bin fairing 109, specifically, the end plate 206 is an annular plate body, the end plate 206 is provided with a mounting hole group, specifically, the mounting hole 209 group comprises a first hole group 207 and a second hole group 208, wherein the first hole group 207 is formed as a connection structure of the end plate 206 and the support casing, that is, the end plate member 206 is fixed to the supporting casing through the first hole group 207, the mounting holes constituting the first hole group 207 are illustratively cylindrical through holes, the second hole group 208 is constituted by a plurality of mounting holes cooperating with the pipe unit 205, specifically, the second hole group 208 includes a plurality of hole unit groups 209 arranged at intervals in the circumferential direction, the single hole unit group 209 includes two mounting holes arranged at intervals in the radial direction, the number of the hole unit groups 209 corresponds to the number of the pipe units, and two ends of the pipe units are respectively connected to two mounting holes of the single hole unit group 209, further, the end plate member 206 is provided with a fluid groove 210 on the other end surface of the pipe unit 205, two mounting holes circumferentially spaced in adjacent hole unit groups 209 are communicated through the fluid groove 210, that is, the fluid groove 210 is constituted as a connecting passage of two pipe units, further, the two mounting holes of the mounting hole group are respectively configured as a total inlet 211 and a total outlet 212 which are communicated with the second receiving space, and referring to fig. 6, the arrow in the drawing exemplarily shows the flowing direction of the lubricating oil, at this time, the outlet of the previous pipe unit 205 is connected to the inlet of the next pipe unit 205 (i.e., the pipe unit 205 adjacent in the circumferential direction) through the fluid groove 210 so as to traverse all the pipe units 205, and correspondingly, one of the mounting hole groups is configured as the total inlet 211, the other is configured as the total outlet 212, and is communicated with the second receiving space 110 through the total inlet 211 and the total outlet 212, the cold lubricating oil flows into the pipe unit 205 from the total inlet 211 and cools the motor stator, finally flows again into the second receiving space 100 from the total outlet 212 and cools again into the circulation, and further, the cable hole 213 is opened in the end plate 206,
Referring to fig. 7, which is a schematic structural diagram of a fan rotor assembly 300, the fan rotor assembly 300 is integrally disposed in a circulation zone and is located at a radial inner side of the motor stator assembly 200, the main body of the fan rotor assembly 300 is composed of a disk member 301 and a plurality of permanent magnets 302, wherein the disk member 301 is composed of a disk portion 301a, a crown portion 301b and a blade portion 301c, the disk portion 301a is a substantially cylindrical member, the crown portion 301b is a substantially sheet-shaped ring body and is located at a radial outer side of the disk portion 301a, the plurality of permanent magnets 302 are embedded in an outer surface of the crown portion 301b and are uniformly distributed in a circumferential direction, the blade portion 301c is composed of a plurality of rotating blades disposed circumferentially, the blade portion 301c is disposed between the disk portion 301a and the crown portion 301b and is connected with the blade portion 301c and the crown portion 301b, and the structure of the fan rotor assembly 300 is further described in fig. 7, the disk portion 301a is provided with a mounting flange structure at one axial end thereof for mounting the fan fairing 304, and the disk portion 301a further has a second axial mounting mechanism for mounting a rotor part 303, which is subsequently described in the mounting the rotor part 400;
Referring to fig. 8, which is a schematic structural view of a rotor support assembly 400, the rotor support assembly 400 includes a rotor support shaft 401, the rotor support shaft 401 has an oil inlet channel 601 extending along an axis O therein, one end of the oil inlet channel 601 is open and the other end is closed, specifically, the rotor support shaft 401 has a middle section 401b located radially inside a disk portion 301a of the fan rotor assembly 300 and a first section 401a and a second section 401c extending axially outside the disk portion 301a, wherein a space exists between an outer circumferential surface of the middle section 401b and an inner surface of the disk portion 301a, a first oil return section 603 corresponding to an oil return channel (described later) is formed, and referring back to fig. 8, continuing to describe the composition of the rotor support assembly 400, the rotor support assembly 400 further includes two bearings 402 mounted at two end positions of the middle section 401b, the two bearings 402 are mounted by the second mounting mechanism 303 on the disk body 301a, at least one of the two bearings 402 mounted at two end positions of the middle section 401b is a ball bearing, the bearings 402 can support the rotor and allow the rotor to rotate, on the one hand, the axial force generated when the blades rotate can be transmitted to the rotor support shaft 401, the connecting positions of the first section 401a, the second section 401c and the middle section 401b are respectively provided with a sealing structure 403, a bearing cavity 602 is correspondingly formed at the position of the bearings 402 to provide a space for lubricating oil to lubricate and/or cool the bearings 402, and the rotor support shaft 401 is provided with radial small holes uniformly distributed in the circumferential direction at the front position of the bearings 402 to spray the lubricating bearings 402, and realize the connection of the oil inlet channel 601 and the bearing cavity 602, meanwhile, the first section 401a is also provided with a compression nut 404 outside the sealing structure 403, the bearing 402 is used for limiting the bearing 402 in the axial direction so as to transmit the axial force transmitted by the bearing 402 to the rotor support shaft 401 and continuously return to the rotor support shaft 401, a mounting flange is formed on the outer circumferential surface of the second section 401c and is used for realizing the mounting and positioning of the rotor support shaft 401 in cooperation with the first mounting structure 112, a plurality of oil return holes 604 which extend along the axis and are communicated with the first oil return section 603 are formed on the mounting flange, the plurality of oil return holes 604 are arranged at equal intervals in the circumferential direction, and returning to fig. 8, the rotor support assembly 400 also comprises a sealing cover plate 405 which is mounted on the outer side of the second section 401c of the rotor support shaft 401 and is used for realizing the construction of an oil inlet pipe and an oil inlet pipe, in particular, an oil inlet 405a and an oil outlet 405b are formed on the sealing cover plate 405, the oil inlet 405a is used for realizing the connection of the oil inlet passage 601 and an external oil supply port, and the connection of the first oil return section 603, the oil return holes 604, a bearing 402 cavity and a second oil return section 606 are formed on the mounting flange, and the solid line and the direction of the dotted line indicate the direction of the flow of lubricating oil in the rotor support shaft 401 with reference to fig. 8;
Referring to fig. 9, the power fan apparatus further includes a rotation shaft assembly 500, the rotation shaft assembly 500 including a first rotation shaft 501 and a second rotation shaft 504 respectively installed at both sides of the supporting case 101, and the axes of the first shaft 501 and the second shaft 504 coincide, referring to fig. 9a and 9d, the first shaft 501 comprises a shaft cylinder 502 and a hollow cable channel 503, wherein the shaft housing 502 is adapted to effect mounting of the power fan assembly and is configured to be rotatable with respect to the aircraft, the cable channel 503 is adapted for power and information interaction between the power fan assembly and the aircraft (described later), and with reference to fig. 9b, 9c, 9e and 9f, the second shaft 504 body is formed by an outer shaft housing 506 and an inner shaft housing 505, wherein the outer hub 506 is rotatably mounted to the aircraft for angular adjustment of the power fan assembly in cooperation with the hub 502 of the first shaft 501, and wherein the inner hub 505 is hollow and coupled to the accessory bin fairing 109, while an oil injection passage 600 communicating with the second receiving space 110 is formed in the inner hub 505, and this oil filling channel 600 is connected to the above-mentioned oil filling channel 601, and low-temperature oil on the aircraft is led into the fan device cooling motor and lubrication/cooling rotor bearing 402, returning to figure 9, a second oil return section 606 of the oil return line is formed between the inner hub 505 and the outer hub 506, the second oil return section 606 is also attached to the accessory bin fairing 109, and communicates with the second receiving area 110, to lead the high-temperature lubricating oil after the rotor bearing 402 and the motor are lubricated/cooled by the fan device back to the aircraft for cooling, and to lead the lubricating oil into the fan device again after filtering impurities in the lubricating oil, and forms an oil circulation loop together with the oil injection channel 600 and the oil inlet channel 601;
Further, the power fan device further comprises a motor controller, a pipeline, an oil pump (not shown) and other components arranged in the second accommodating section 110, wherein the cooling lubricating oil led in by the aircraft is distributed by the controller and enters different channels through the oil pump to cool the motor, the controller and the rotor bearing 402, and the hot lubricating oil of the motor, the controller and the rotor bearing 402 is pumped back to the accessory bin by the oil pump and is collected and returned to the aircraft.
The invention also discloses an aircraft, referring to fig. 10, the aircraft is provided with the power fan device (hereinafter referred to as power fan), specifically, the aircraft comprises a main body system (such as a control system, a fuselage system and the like), a power generation combustion engine and three power fans, wherein the power generation combustion engine is configured as a gas turbine generator capable of outputting electric energy so as to provide electric power for the rest part (such as the main body system, the power fans and the like) of the aircraft, the three power fans are respectively arranged at two sides and the rear of the aircraft and are configured to be rotatably adjusted so as to drive the aircraft to advance and ascend, the angular state of the electric bypass power fan is horizontal when the aircraft takes off and lands, and the angular state of the electric bypass power fan is vertical when the aircraft flies ahead is shown in fig. 11. When the aircraft is in maneuvering flight, the aircraft can be realized by the 3 power fan devices in different angular states, so that the aircraft can replace the traditional aircraft elevator, steering rudder, aileron and other mechanisms to realize the flight control function.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. An electric ducted power fan apparatus, comprising:
a support casing including a housing portion defining a generally cylindrical flow-through region;
the motor stator subassembly set up in the circulation interval and install in on the support receiver, the motor stator subassembly is configured to produce the magnetic field that constantly changes based on external control system, the motor stator subassembly includes:
the iron core assembly sheet is provided with an outer wall part which is approximately in the shape of an annular sheet and a plurality of T-shaped parts which are fixed on the inner surface of the outer wall part;
The stator winding comprises a plurality of winding units wound on the T-shaped part, and interval sections exist between adjacent winding units;
The cooling pipeline assembly comprises pipeline units arranged in the interval section, and the pipeline units are provided with inlets and outlets;
the pipeline unit is arranged on the end plate, a fluid groove is formed in the other side of the pipeline unit by the end plate, and a cable hole and a plurality of mounting holes are formed in the end plate;
The fan device also comprises a rotor support shaft assembly, a first surrounding part and a second surrounding part, wherein the rotor support shaft assembly comprises a rotor support shaft arranged along an axis O, the rotor support shaft is mounted on the support casing, the support casing also comprises a second surrounding part which is approximately cylindrical and a first surrounding part which is arranged on the radial outer side of the second surrounding part, the first surrounding part and the second surrounding part are connected through a plurality of bearing support plates which are uniformly arranged in the circumferential direction, and the rotor support shaft is mounted through a first mounting structure on the second surrounding part;
the fan rotor assembly is installed on the rotor supporting shaft and is configured to rotate around the axis O, the fan rotor assembly comprises a plurality of blades uniformly arranged in the circumferential direction and a crown part fixed on the radial outer side of the blades, the fan rotor assembly further comprises a plurality of permanent magnets fixed on the outer surface of the crown part and uniformly arranged in the circumferential direction, the fan rotor assembly further comprises a disc body part positioned on the radial inner side of the crown part, and a first oil return section is formed between the inner wall of the disc body part and the outer wall of the rotor supporting shaft.
2. The electrically powered ducted powered fan assembly of claim 1, further comprising an accessory bin fairing mounted to an axial end of said housing portion, wherein said accessory bin fairing, said first surrounding portion, and said housing portion together define a second receiving space in communication with said circulation space.
3. The electric ducted power fan apparatus as set forth in claim 2, wherein an oil inlet passage is formed in the rotor support shaft and disposed along the axis O, the oil inlet passage communicating with the first oil return section through a radial hole formed in the rotor support shaft.
4. The electrically powered ducted power fan apparatus as set forth in claim 3 wherein said rotor support shaft includes a middle section and first and second sections extending axially outwardly from opposite ends of said middle section, said rotor support shaft assembly further including two bearings mounted to said middle section, and said disk portion having a second mounting structure formed thereon for mounting bearings, at least one of said two bearings being a ball bearing.
5. The electrically powered ducted power fan apparatus as set forth in claim 4 further comprising a shaft assembly including first and second shafts mounted on opposite radial sides of said support housing with axes coincident.
6. The electrically powered ducted powered fan apparatus of claim 5, wherein said first shaft includes a shaft post and a hollow cable channel, said second shaft includes an outer shaft post and an inner shaft post, said inner shaft post is connected to said accessory bin fairing, an oil injection channel is hollow within said inner shaft post, and a second oil return section is formed between said outer shaft post and said inner shaft post.
7. An aircraft characterized in that it has a fan device according to any of claims 1-6, and in that the fan device is configured to be rotatably adjustable in direction.
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| CN202310769643.1A CN117022643B (en) | 2023-06-27 | 2023-06-27 | Electric ducted power fan device and aircraft |
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| CN202310769643.1A CN117022643B (en) | 2023-06-27 | 2023-06-27 | Electric ducted power fan device and aircraft |
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| CN117022643B true CN117022643B (en) | 2025-01-24 |
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| CN114144355A (en) * | 2019-05-16 | 2022-03-04 | 杜希欧汽车公司 | Electric aircraft propulsion system |
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| US20100148515A1 (en) * | 2007-11-02 | 2010-06-17 | Mary Geddry | Direct Current Brushless Machine and Wind Turbine System |
| NZ569455A (en) * | 2008-06-27 | 2009-10-30 | Martin Aircraft Company Ltd | Propulsion device incorporating radiator cooling passage |
| US20200239152A1 (en) * | 2019-01-30 | 2020-07-30 | Bell Helicopter Textron Inc. | Thermal management system |
| CN112722242A (en) * | 2020-12-28 | 2021-04-30 | 中国航空发动机研究院 | Magnetic suspension ducted fan for electric aircraft |
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| CN114144355A (en) * | 2019-05-16 | 2022-03-04 | 杜希欧汽车公司 | Electric aircraft propulsion system |
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