CN207417127U - A kind of aircraft impeller and aircraft - Google Patents
A kind of aircraft impeller and aircraft Download PDFInfo
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- CN207417127U CN207417127U CN201721531100.2U CN201721531100U CN207417127U CN 207417127 U CN207417127 U CN 207417127U CN 201721531100 U CN201721531100 U CN 201721531100U CN 207417127 U CN207417127 U CN 207417127U
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- aircraft
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- mounting groove
- opening face
- axial line
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Abstract
The utility model provides a kind of aircraft impeller and aircraft, belongs to aircraft driving part field, wherein aircraft impeller, including framework and runner portion；Framework includes mounting groove, and runner portion is fixed in mounting groove；Mounting groove has axial line；Mounting groove also has the opening face and bottom surface being oppositely arranged；Runner portion includes the blade of at least one circular axial line distribution, and blade includes luvisde；In the junction in luvisde Yu opening face, the section of luvisde and the angle in opening face are acute angle.By this aircraft impeller, the energy has been saved in not excessive ground-to-air gas acting.
Description
Technical field
The utility model is related to aircraft driving part field, in particular to a kind of aircraft impeller and aircraft.
Background technology
At present, for its lift from air in the flowing speed difference of aerofoil surface, aircraft must in flight for the aircraft of wing class
Constantly lift must be kept by athleticism, take very much the energy.And the aircraft of types of propellers needed when keeping flight it is big to air
To generate wind-force, the reaction force of wind-force promotes aircraft to rise, and does work to generate wind-force to original static air for amount acting
Process also consumes energy very much.
Utility model content
The utility model provides a kind of aircraft impeller and aircraft, it is intended to solve in the prior art aircraft impeller and
The above problem existing for aircraft.
The utility model is realized in this way：
A kind of aircraft impeller, including framework and runner portion；
The framework includes mounting groove, and the runner portion is fixed in the mounting groove；
The mounting groove has axial line；The mounting groove also has the opening face and bottom surface being oppositely arranged；
The runner portion includes at least one blade around axial line distribution, and the blade includes luvisde；
The luvisde and the junction in the opening face, the section of the luvisde and the angle in the opening face are acute angle.
In the utility model preferred embodiment, installation through-hole, the installation through-hole are provided in the middle part of the mounting groove
Central shaft overlapped with the axial line, the side wall of the installation through-hole extends to the bottom surface from the opening face.
In the utility model preferred embodiment, the blade is curved with the direction of rotation for deviateing the axial line
Roulette curvature.
In the utility model preferred embodiment, the mounting groove is cylindrical groove, and the blade is away from the axle center
One end of line is fixedly connected with the mounting groove inner wall.
In the utility model preferred embodiment, the installation through-hole is cylindrical hole.
In the utility model preferred embodiment, the blade is 12, and 12 blades are circumferentially uniformly mounted on
Around the axial line.
In the utility model preferred embodiment, the one end of the blade away from the bottom surface is on the opening face.
In the utility model preferred embodiment, the blade is fixed close to one end of the bottom surface and the bottom surface to be connected
It connects.
In the utility model preferred embodiment, one side of the framework away from the opening face sets oriented separate institute
The protrusion of opening face extension is stated, the protrusion is cylinder convex block, and the axle center of the protrusion is overlapped with the axial line.
A kind of aircraft, including body and above-mentioned aircraft impeller；
The body includes driving device, the driving device and the installation through-hole coordinate cause the body with it is described
Aircraft impeller connects.
The beneficial effects of the utility model are：By aircraft impeller provided by the utility model can not generate it is excessive
In the case of wind-force, lift is provided for aircraft impeller, after aircraft impeller is installed on aircraft, aircraft is in the air
When static, it is only necessary to consume the energy of aircraft impeller surface and windage, too many energy consumption is not required substantially.
Description of the drawings
It, below will be to required in embodiment in order to illustrate more clearly of the technical solution of the utility model embodiment
The attached drawing used is briefly described, it should be understood that and the following drawings illustrates only some embodiments of the utility model, therefore not
The restriction to scope is should be considered as, for those of ordinary skill in the art, without creative efforts,
It can also be obtained according to these attached drawings other relevant attached drawings.
Fig. 1 is the structure diagram at the first visual angle of the aircraft impeller that the utility model embodiment provides；
Fig. 2 is the structure diagram at the second visual angle of the aircraft impeller that the utility model embodiment provides；
Fig. 3 be in Fig. 2 III-III to sectional view；
Fig. 4 is the structure diagram at the 3rd visual angle of the aircraft impeller that the utility model embodiment provides；
Fig. 5 is the structure diagram at the 4th visual angle of the aircraft impeller that the utility model embodiment provides；
Fig. 6 is that the structure at the second visual angle when the aircraft impeller that the utility model embodiment provides is not provided with runner portion is shown
It is intended to.
Icon：001- aircraft impellers；100- frameworks；200- runners portion；The first faces of 101-；The second faces of 103-；110- is convex
Portion；130- mounting grooves；105- axial lines；131- bottom surfaces；111- installation through-holes；140- installing zones；210- blades；211- is aweather
Face；213- leewards；230- air drains.
Specific embodiment
To make the purpose, technical scheme and advantage of the utility model embodiment clearer, below in conjunction with this practicality
The technical solution in the utility model embodiment is clearly and completely described in attached drawing in new embodiment, shows
So, described embodiment is the embodiment of a part of embodiment of the utility model rather than whole.Based on this practicality
Embodiment in new, those of ordinary skill in the art are obtained every other without creative efforts
Embodiment shall fall within the protection scope of the present invention.Therefore, the implementation to the utility model provided in the accompanying drawings below
The detailed description of mode is not intended to limit claimed the scope of the utility model, but is merely representative of the utility model
Selected embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not making creative labor
The every other embodiment obtained under the premise of dynamic, shall fall within the protection scope of the present invention.
In the description of the utility model, it is to be understood that the term of indicating position or position relationship is based on attached drawing
Shown orientation or position relationship are for only for ease of description the utility model and simplify description rather than instruction or imply institute
The equipment or element of finger must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that this reality
With new limitation.
In the utility model, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " Gu
It is fixed " etc. terms should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected or integral；Can be
Mechanical connection or electrical connection；It can be directly connected, can also be indirectly connected by intermediary, can be two
The interaction relationship of connection or two elements inside element.It for the ordinary skill in the art, can basis
Concrete condition understands concrete meaning of the above-mentioned term in the utility model.
In the utility model, unless otherwise clearly defined and limited, fisrt feature is on or below second feature
It can be contacted directly including the first and second features, it is not to contact directly but pass through it that can also include the first and second features
Between other characterisation contact.Moreover, fisrt feature is on second feature, top and above include fisrt feature the
Directly over two features and oblique upper is merely representative of fisrt feature level height higher than second feature.Fisrt feature is special second
Under sign, lower section and fisrt feature included below immediately below second feature and obliquely downward or be merely representative of fisrt feature level
Highly it is less than second feature.
Embodiment one
A kind of aircraft impeller 001 is present embodiments provided, referring to Fig. 1, this aircraft impeller 001 includes framework
100 and runner portion 200.
Referring to Fig. 6, in the present embodiment, framework 100 is discoid, and polishing processing is done in the periphery of framework 100, with drop
Windage during low rotation.Framework 100 includes the first face 101 and the second face 103 that are oppositely arranged, is provided in the second face 103 convex
Portion 110, protrusion 110 are the cylindrical bump extended from the second face 103 to the direction away from the first face 101.In the present embodiment,
The distance in the one end of protrusion 110 away from the second face 103 to the second face 103 is less than the distance in the 101 to the second face of the first face 103, i.e.,
The thickness of protrusion 110 is less than the thickness of framework 100.The axis of protrusion 110 is overlapped with the axis of framework 100.
Fig. 2 and Fig. 4 are referred to, is provided with mounting groove 130 in the first face 101, mounting groove 130 is from the first face 101 to second
Face 103 extends, and mounting groove 130 is cylindrical groove, and mounting groove 130 has axial line 105, axial line 105 and the axis of framework 100
It overlaps.Mounting groove 130 has the opening face being oppositely arranged and bottom surface 131.Face where the opening of opening face, that is, mounting groove 130, is opened
Mouth face is overlapped with the first face 101 of framework 100, and bottom surface 131 is one side of the mounting groove 130 close to the second face 103.
Installation through-hole 111, the axis of installation through-hole 111 and 105 weight of axial line of framework 100 are provided in mounting groove 130
It closes, the side wall of installation through-hole 111 extends to bottom surface 131 from opening face, in the present embodiment, continues to extend to the top of protrusion 110
End.Installation through-hole 111 drives aircraft impeller 001 to rotate for installing on the drive means, by driving device.
Installing zone 140 is formed between the inner wall of mounting groove 130 and the outer wall of installation through-hole 111, runner portion 200 is mounted on peace
It fills in area 140.In the present embodiment, runner portion 200 includes 12 blades, 210,12 blades 210 around installation through-hole 111
Outer wall be circumferentially uniformly distributed, the one end of blade 210 away from axial line 105 is fixedly connected with 130 inner wall of mounting groove.One blade
210 rotate 30 ° with axial line 105 for axis to be overlapped with another adjacent blade 210.
Blade 210 has the luvisde 211 towards opening face, and when being rotated in runner portion 200, luvisde 211 is towards empty
The face that fate is moved.
Referring to Fig. 5, blade 210 has the curved roulette curvature in direction of rotation of disalignment line 105, specific explanations
I.e.：In the present embodiment, using parallel to axial line 105 and from the first face 101 be directed toward the second face 103 direction as A directions, from A
The visual angle in direction, luvisde 211 circle round counterclockwise during extending from axial line 105 to 130 inner wall of mounting groove.It is same herein
When, the junction in luvisde 211 and opening face, the section of luvisde 211 and the angle in opening face are acute angle.
Since the angular speed of each point when runner portion 200 rotates is equal, cause linear velocity at axial line 105 toward mounting groove
The direction of 130 inner walls can gradually increase, and the air motion being so easy to cause in mounting groove 130 is disorderly.It is asked to solve this
Topic, to 130 edge extending direction of mounting groove at axial line 105, luvisde 211 and the junction in opening face, luvisde 211
The angle of section and opening face is gradually reduced.
Blade 210 also has leeward 213, and leeward 213 is one side opposite with luvisde 211 on blade 210, at this
Leeward 213 is identical with the radian of 211 each corresponding points of luvisde in embodiment, forms an identical blade 210 of thickness everywhere.
This ensure that the intensity of blade 210, while also avoid air turbulence caused by 210 thickness of blade when runner portion 200 rotates.
Fig. 2 and Fig. 3 are referred to, the one end of blade 210 away from bottom surface 131 is on opening face, i.e., blade 210 is away from bottom surface
131 one end extends to 130 inner wall of mounting groove from the outer wall of installation through-hole 111 and always always in opening face.Blade 210 leans on
One end of nearly bottom surface 131 is fixedly connected on bottom surface 131 and with bottom surface 131, i.e., blade 210 close to one end of bottom surface 131 from peace
The outer wall of dress through hole 111 extends to 130 inner wall of mounting groove and always always in bottom surface 131.
The sealing of five faces is formed between the luvisde 211 of one blade 210 and the leeward 213 of an adjacent blades 210
Air drain 230, when being rotated in runner portion 200, air rotation synchronous with runner portion 200 under the drive of blade 210 in air drain 230
Turn, compared with the inside of aircraft impeller 001, air is motionless, keeps normal pressure state, and the second face 103 is compared with outside
Air be that high-speed motion forms negative pressure, the size of negative pressure value determines by the linear velocity that aircraft impeller 001 rotates.This negative pressure
Can be that aircraft impeller 001 provides lift.
It should be noted that in the present embodiment, runner portion 200 includes 12 blades 210, in other embodiments,
The lift size provided can be needed according to the size or aircraft impeller 001 in actual runner portion 200, to the number of blade 210
Amount carries out appropriate adjustment.
It can be in the case where not generating excessive wind-force, for flight by aircraft impeller 001 provided by the utility model
Device impeller 001 provides lift, after aircraft impeller 001 is installed on aircraft, when aircraft is static in the air, it is only necessary to
The energy of 001 surface of aircraft impeller and windage is consumed, too many energy consumption is not required substantially.
Embodiment two
A kind of aircraft is present embodiments provided, referring to Fig. 1, this aircraft includes body and aircraft impeller 001.
Aircraft impeller 001 includes framework 100 and runner portion 200.
Referring to Fig. 6, in the present embodiment, framework 100 is discoid, and polishing processing is done in the periphery of framework 100, with drop
Windage during low rotation.Framework 100 includes the first face 101 and the second face 103 that are oppositely arranged, is provided in the second face 103 convex
Portion 110, protrusion 110 are the cylindrical bump extended from the second face 103 to the direction away from the first face 101.In the present embodiment,
The distance in the one end of protrusion 110 away from the second face 103 to the second face 103 is less than the distance in the 101 to the second face of the first face 103, i.e.,
The thickness of protrusion 110 is less than the thickness of framework 100.The axis of protrusion 110 is overlapped with the axis of framework 100.
Fig. 2 and Fig. 4 are referred to, is provided with mounting groove 130 in the first face 101, mounting groove 130 is from the first face 101 to second
Face 103 extends, and mounting groove 130 is cylindrical groove, and mounting groove 130 has axial line 105, axial line 105 and the axis of framework 100
It overlaps.Mounting groove 130 has the opening face being oppositely arranged and bottom surface 131.Face where the opening of opening face, that is, mounting groove 130, is opened
Mouth face is overlapped with the first face 101 of framework 100, and bottom surface 131 is one side of the mounting groove 130 close to the second face 103.
Installation through-hole 111, the axis of installation through-hole 111 and 105 weight of axial line of framework 100 are provided in mounting groove 130
It closes, the side wall of installation through-hole 111 extends to bottom surface 131 from opening face, in the present embodiment, continues to extend to the top of protrusion 110
End.
Installation through-hole 111 is used to be connected with body.Body includes driving device, and driving device coordinates with installation through-hole 111
Connection drives aircraft impeller 001 to rotate by driving device.
Installing zone 140 is formed between the inner wall of mounting groove 130 and the outer wall of installation through-hole 111, runner portion 200 is mounted on peace
It fills in area 140.In the present embodiment, runner portion 200 includes 12 blades, 210,12 blades 210 around installation through-hole 111
Outer wall be circumferentially uniformly distributed, the one end of blade 210 away from axial line 105 is fixedly connected with 130 inner wall of mounting groove.One blade
210 rotate 30 ° with axial line 105 for axis to be overlapped with another adjacent blade 210.
Blade 210 has the luvisde 211 towards opening face, and when being rotated in runner portion 200, luvisde 211 is towards empty
The face that fate is moved.
Referring to Fig. 5, blade 210 has the curved roulette curvature in direction of rotation of disalignment line 105, specific explanations
I.e.：In the present embodiment, using parallel to axial line 105 and from the first face 101 be directed toward the second face 103 direction as A directions, from A
The visual angle in direction, luvisde 211 circle round counterclockwise during extending from axial line 105 to 130 inner wall of mounting groove.It is same herein
When, the junction in luvisde 211 and opening face, the section of luvisde 211 and the angle in opening face are acute angle.
Since the angular speed of each point when runner portion 200 rotates is equal, cause linear velocity at axial line 105 toward mounting groove
The direction of 130 inner walls can gradually increase, and the air motion being so easy to cause in mounting groove 130 is disorderly.It is asked to solve this
Topic, to 130 edge extending direction of mounting groove at axial line 105, luvisde 211 and the junction in opening face, luvisde 211
The angle of section and opening face is gradually reduced.
Blade 210 also has leeward 213, and leeward 213 is one side opposite with luvisde 211 on blade 210, at this
Leeward 213 is identical with the radian of 211 each corresponding points of luvisde in embodiment, forms an identical blade 210 of thickness everywhere.
This ensure that the intensity of blade 210, while also avoid air turbulence caused by 210 thickness of blade when runner portion 200 rotates.
Fig. 2 and Fig. 3 are referred to, the one end of blade 210 away from bottom surface 131 is on opening face, i.e., blade 210 is away from bottom surface
131 one end extends to 130 inner wall of mounting groove from the outer wall of installation through-hole 111 and always always in opening face.Blade 210 leans on
One end of nearly bottom surface 131 is fixedly connected on bottom surface 131 and with bottom surface 131, i.e., blade 210 close to one end of bottom surface 131 from peace
The outer wall of dress through hole 111 extends to 130 inner wall of mounting groove and always always in bottom surface 131.
The sealing of five faces is formed between the luvisde 211 of one blade 210 and the leeward 213 of an adjacent blades 210
Air drain 230, when being rotated in runner portion 200, air rotation synchronous with runner portion 200 under the drive of blade 210 in air drain 230
Turn, compared with the inside of aircraft impeller 001, air is motionless, keeps normal pressure state, and the second face 103 is compared with outside
Air be high-speed motion formed negative pressure, this negative pressure can be aircraft impeller 001 lift is provided.
It should be noted that in the present embodiment, runner portion 200 includes 12 blades 210, in other embodiments,
The lift size provided can be needed according to the size or aircraft impeller 001 in actual runner portion 200, to the number of blade 210
Amount carries out appropriate adjustment.
And in practical applications, the optimal shape of this aircraft is streamline dish.Can also be other random appearances
Aircraft or aerial castle, hovering building etc., simply need sufficient amount or sufficiently large aircraft impeller 001 provide it is enough
Lifting force can.
It can be in the case where not generating excessive wind-force, for flight by aircraft impeller 001 provided by the utility model
Device provides lift, therefore when aircraft is static in the air, need not consume substantially too many energy for for it is new enter air provide
Kinetic energy, it is only necessary to keep the kinetic energy of air in air drain 230.
Above description is merely a prefered embodiment of the utility model, is not intended to limit the utility model, for
For those skilled in the art, various modifications and changes may be made to the present invention.It is all in the spiritual and former of the utility model
Within then, any modifications, equivalent replacements and improvements are made should be included within the scope of protection of this utility model.
Claims (10)
1. a kind of aircraft impeller, which is characterized in that including framework and runner portion；
The framework includes mounting groove, and the runner portion is fixed in the mounting groove；
The mounting groove has axial line；The mounting groove also has the opening face and bottom surface being oppositely arranged；
The runner portion includes at least one blade around axial line distribution, and the blade includes luvisde；Described
Luvisde and the junction in the opening face, the section of the luvisde and the angle in the opening face are acute angle.
2. aircraft impeller according to claim 1, which is characterized in that installation through-hole is provided in the middle part of the mounting groove,
The central shaft of the installation through-hole is overlapped with the axial line, and the side wall of the installation through-hole extends to described from the opening face
Bottom surface.
3. aircraft impeller according to claim 2, which is characterized in that the blade has the rotation for deviateing the axial line
Turn the curved roulette curvature in direction.
4. aircraft impeller according to claim 2, which is characterized in that the mounting groove be cylindrical groove, the blade
One end away from the axial line is fixedly connected with the inner wall of the mounting groove.
5. aircraft impeller according to claim 2, which is characterized in that the installation through-hole is cylindrical hole.
6. aircraft impeller according to claim 2, which is characterized in that the blade is 12,12 blade weeks
To uniformly be mounted on the axial line around.
7. aircraft impeller according to claim 2, which is characterized in that the one end of the blade away from the bottom surface is in institute
It states on opening face.
8. aircraft impeller according to claim 2, which is characterized in that the blade is close to one end of the bottom surface and institute
Bottom surface is stated to be fixedly connected.
9. aircraft impeller according to claim 2, which is characterized in that the framework is set on one side away from the opening face
It is equipped with to the protrusion away from opening face extension, the protrusion is cylinder convex block, the axle center of the protrusion and the axle center
Line overlaps.
10. a kind of aircraft, which is characterized in that including body and such as claim 2-9 any one of them aircraft impellers；
The body includes driving device, and the driving device coordinates with the installation through-hole so that the body and the flight
Device impeller connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721531100.2U CN207417127U (en) | 2017-11-16 | 2017-11-16 | A kind of aircraft impeller and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721531100.2U CN207417127U (en) | 2017-11-16 | 2017-11-16 | A kind of aircraft impeller and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207417127U true CN207417127U (en) | 2018-05-29 |
Family
ID=62306267
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721531100.2U Active CN207417127U (en) | 2017-11-16 | 2017-11-16 | A kind of aircraft impeller and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107856843A (en) * | 2017-11-16 | 2018-03-30 | 唐良伦 | A kind of aircraft impeller and aircraft |
-
2017
- 2017-11-16 CN CN201721531100.2U patent/CN207417127U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107856843A (en) * | 2017-11-16 | 2018-03-30 | 唐良伦 | A kind of aircraft impeller and aircraft |
| WO2019095841A1 (en) * | 2017-11-16 | 2019-05-23 | 唐良伦 | Aircraft impeller and aircraft |
| CN107856843B (en) * | 2017-11-16 | 2020-02-07 | 唐良伦 | Aircraft impeller and aircraft |
| US11401029B2 (en) | 2017-11-16 | 2022-08-02 | Lianglun TANG | Aircraft impeller and aircraft |
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