CN108482666A - A kind of gradient pitch multisection type cracks propeller - Google Patents
A kind of gradient pitch multisection type cracks propeller Download PDFInfo
- Publication number
- CN108482666A CN108482666A CN201810361876.7A CN201810361876A CN108482666A CN 108482666 A CN108482666 A CN 108482666A CN 201810361876 A CN201810361876 A CN 201810361876A CN 108482666 A CN108482666 A CN 108482666A
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- blade
- propeller
- gap
- segmentation
- pitch
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
Abstract
It cracks propeller, including propeller hub and at least two blades the present invention relates to a kind of gradient pitch multisection type, the longitudinal axis of propeller hub is pivot center；One end of blade is connecting pin, the lateral surface of connecting pin and propeller hub connects, at least two blades are axisymmetricly arranged about pivot center, each blade along the diametric(al) of propeller offer it is one or more for gas by strip gap, gap penetrates through setting from the leeward towards blade windward of blade.The propeller that cracks of the present invention, by opening up gap on the blade of rotation, air first passes through after there is the blade of thread pitch in gap front end, it is gathered into the air-flow of certain angle of downwash degree in gap, then air-flow passes through the blade positioned at gap rear end thread pitch bigger again, form the downwash flow of angle bigger, downwash flow angle is bigger, the lift of propeller is bigger, therefore aircraft is when using this propeller, the power consumption of aircraft can be reduced, cruise duration is improved, increases lifting capacity.
Description
Technical field
It cracks propeller the present invention relates to flight equipment technical field more particularly to a kind of gradient pitch multisection type.
Background technology
On helicopter and multi-rotor aerocraft, the blade of rotation directly provides lift, is called rotor；In fixed wing aircraft
On, the propeller of rotation provides the pulling force (or thrust) of aircraft flight forward, and the lift of aircraft then comes from wing, but rotor and
Principle of propeller is identical, is all to have the blade of certain thread pitch to rotate the power for generating a direction around engine shaft.
Propeller refers to having the blade at certain angle of inclination to be rotated in air or water, converts engine rotation power to
The device of propulsive force or lift, there are two or more blade be connected with hub, leaf for helicoid or is similar to spiral shell on one side backward
A kind of propeller of radial facing, and one side is arranged windward, the angle of inclination of blade are the thread pitch of blade, thread pitch it is big
The small lift for directly affecting blade, in the case where blade rotating speed is constant, thread pitch is bigger, passes through the downwash flow of blade
Angle is bigger, and the lift of blade will be higher, but excessive thread pitch can lead to blade stall, the lift resistance ratio of propeller
It reduces, the principle of blade stall is identical with the stall principle of fixed wing aircraft.
Invention content
The technical problem to be solved by the present invention is in view of the deficiencies of the prior art, provide a kind of gradient pitch multisection type to open
Stitch propeller, at least one to solve the above technical problems.
The technical solution that the present invention solves above-mentioned technical problem is as follows：A kind of gradient pitch multisection type cracks propeller, packet
It includes：
The longitudinal axis of propeller hub, the propeller hub is pivot center；
One end of at least two blades, the blade is connecting pin, and the connecting pin is connect with the lateral surface of the propeller hub,
At least two blade axisymmetricly arranges that each blade is opened along the diametric(al) of propeller about the pivot center
Equipped with it is one or more for gas by strip gap, the gap is from the blade windward towards the blade
Leeward perforation setting.
The beneficial effects of the invention are as follows：The propeller of rotation interacts with air, to generate upward lift, this hair
Bright gradient pitch multisection type cracks propeller, by opened up on the blade of rotation it is multiple for air by strip stitch
Gap, gap is penetrated through from the windward side of blade to leeward to be arranged, and air first passes through the blade for having thread pitch positioned at gap front end
Afterwards, the air-flow of certain angle of downwash degree is gathered into gap, then air-flow is again by positioned at gap rear end thread pitch bigger
Blade, formed angle bigger downwash flow, often increase a gap, so that it may with increase positioned at gap rear end blade spiral shell
Elongation degree repeatedly increases the quantity in gap, and final downwash flow angle is close to an angle of 90 degrees when propeller can be made to rotate；Under wash
The angle of air-flow is bigger, and the lift of propeller is bigger, solves the problems, such as that excessive thread pitch can lead to blade stall, therefore
Aircraft can reduce the power consumption of aircraft, improve the cruise duration of aircraft, increase simultaneously when using this propeller
Add the lifting capacity of aircraft.
Based on the above technical solution, the present invention can also be improved as follows.
Further, the blade includes multiple segmentation blades being sequentially overlapped along its rotation direction, the gap setting
Between two adjacent segmentation blades.
Further, each segmentation blade is divided into the leading edge ends and trailing edge ends of segmentation blade along airflow direction,
The both sides in the gap are respectively the trailing edge ends of the segmentation blade positioned at the gap front end and are located at the gap rear end
It is segmented the leading edge ends of blade.
Advantageous effect using above-mentioned further scheme is：When blade is rotated around propeller hub, air is by being located at gap
After the segmentation blade back of front end and lower surface, the air-flow of certain angle of downwash degree is gathered at gap, then air-flow is again
The secondary blade by positioned at gap rear end thread pitch bigger forms the downwash flow of angle bigger, and angle of downwash degree is bigger, spiral
The lift of paddle is higher.
Further, the two neighboring segmentation blade, along airflow direction, the trailing edge ends of one of segmentation blade lean on
The leading edge ends of another nearly segmentation blade.
Further, the segmentation blade thread pitch for being located at the gap rear end is more than the segmentation for being located at the gap front end
Blade thread pitch.
Further, quantity of the gap along the airscrew diameter direction being located on each blade is one
Or it is multiple.
Further, quantity of the gap along the propeller direction of rotation being located on each blade is one or more
It is a.
Further, the windward side of the segmentation blade of the gap rear end and/or leeward are provided with multiple sheets
Protrusion, the sheet protrusion are parallel with the propeller direction of rotation.
Advantageous effect using above-mentioned further scheme is：The setting sheet protrusion on segmentation blade, can be in windward side
Guiding function is played to air-flow with leeward, sheet protrusion is parallel with propeller direction of rotation, can prevent air-flow from passing through screw pitch
When the larger segmentation blade of angle, the dispersion on airscrew diameter direction is generated.
Further, the blade is fixedly connected with the propeller hub using integrated.
Further, the blade is connect with the wheel hub by blade fold mechanism or blade pitch changing actuator.
Description of the drawings
Fig. 1 is the overall structure figure of split propeller of the present invention；
Fig. 2 is the vertical view of the split rotor in the embodiment of the present invention one；
Fig. 3 is the vertical view of the split rotor in the embodiment of the present invention two；
Fig. 4 is the vertical view of the split rotor in the embodiment of the present invention three；
Fig. 5 is the vertical view of the split rotor in the embodiment of the present invention four；
Fig. 6 is a kind of end view drawing of the blade of the propeller of the present invention at gap；
Fig. 7 is end view drawing of the blade of another propeller of the present invention at gap；
Fig. 8 is a kind of comparison diagram of the propeller blade section of the present invention；
Fig. 9 is the comparison diagram of another propeller blade section of the present invention.
In attached drawing, parts list represented by the reference numerals are as follows：
1, propeller hub；11, mounting hole；12, pivot center；2, blade；21, it is segmented blade；211, leading edge ends；212, rear
End；3, gap.
Specific implementation mode
The principle and features of the present invention will be described below with reference to the accompanying drawings, and the given examples are served only to explain the present invention, and
It is non-to be used to limit the scope of the present invention.
As shown in figs 1-9, a kind of gradient pitch multisection type of the invention cracks propeller, including propeller hub 1 and at least two
The longitudinal axis of blade 2, the propeller hub 1 is pivot center 12；One end of the blade 2 is connecting pin, the connecting pin and institute
The lateral surface connection of propeller hub 1 is stated, at least two blade 2 is axisymmetricly arranged about the pivot center 12, each described
Blade 2 along the diametric(al) A of propeller offer it is one or more for gas by strip gap 3, the gap 3 from
The leeward perforation setting towards the blade 2 windward of the blade 2.
Propeller is divided into many kinds, and application is also very extensive, such as aircraft, steamer propeller.Rotor be helicopter and
The important component of multi-rotor aerocraft.In flight course, rotor plays dual parts of to generate lift and pulling force.Moreover,
The rotor of helicopter also acts as the effect similar to aircraft aileron, elevator.Difference lies in helicopter for rotor and propeller
On multi-rotor aerocraft, the rotor of rotation directly provides lift, therefore is called rotor；On fixed wing aircraft, the spiral shell of rotation
Pulling force or thrust that paddle provides aircraft flight forward are revolved, the lift of aircraft then comes from wing, but rotor and principle of propeller phase
Together, all it is to have the blade of certain thread pitch to be pivoted the propulsive force for generating a direction.
As shown in Fig. 1,6-9, propeller and the air of rotation interact, of the invention to generate upward lift
Gradient pitch multisection type cracks propeller, by opened up on the blade 2 of rotation it is multiple for air by strip gap
3, gap 3 is penetrated through from the windward side of blade 2 to leeward to be arranged, and air first passes through the paddle for having thread pitch positioned at 3 front end of gap
After leaf 2, it is gathered into the air-flow of certain angle of downwash degree in gap 2, then air-flow is again by positioned at 3 rear end thread pitch of gap
The blade 2 of bigger forms the downwash flow of angle bigger, often increases a gap 3, so that it may to increase positioned at 3 rear end of gap
The thread pitch of blade 2 repeatedly increases the quantity in gap 3, and final downwash flow angle is close when propeller can be made to rotate
An angle of 90 degrees；The angle of downwash flow is bigger, and the lift of propeller is bigger, and blade stall can be led to by solving excessive thread pitch
The problem of, therefore aircraft can reduce the power consumption of aircraft when using this propeller, improve the continuous of aircraft
ETS estimated time of sailing, while increasing the lifting capacity of aircraft.Meaning aircraft of the invention, which is helicopter or multi-rotor aerocraft etc., to be had
The aircraft of revolving vane device.
Further, as shown in Figs. 1-5, the blade 2 includes multiple segmentation blades being sequentially overlapped along its rotation direction
21, the gap 3 is arranged between two adjacent segmentation blades 21.Each segmentation blade 21 divides along airflow direction C is
The leading edge ends 211 and trailing edge ends 212 of blade 21 are segmented, the both sides in the gap 3 are respectively positioned at 3 front end of the gap
It is segmented the leading edge ends 211 of the trailing edge ends 212 and the segmentation blade 21 positioned at 3 rear end of the gap of blade 21.It is two neighboring
The segmentation blade 21, along airflow direction C, the trailing edge ends 212 of one of segmentation blade 21 are close to another segmentation blade
21 leading edge ends 211.Segmentation 21 thread pitch of blade positioned at 3 rear end of the gap is more than positioned at 3 front end of the gap
It is segmented 21 thread pitch of blade.
As Figure 6-9, blade 2 of the invention includes multiple segmentation blades 21 being sequentially overlapped, and adjacent two points
The relative position of section blade 21 can be adjusted, to realize the optimization to entire propeller works efficiency.Vertically
Cutting is carried out in the position in gap 3 to blade 2, after can be fully aware of observe opens up gap 3, the variation of air-flow.Specifically
, since there is certain angles with horizontal plane for blade 2, passes through in air-flow (arrow C is signified in figure) and be segmented the upper of blade 21
Behind surface and lower surface, at gap 3, it is gathered into the air-flow of certain angle of downwash degree.It is located at that is, air first passes through
After there is the blade 2 of thread pitch in 3 front end of gap, it is gathered into the air-flow of certain angle of downwash degree in gap 2, then air-flow leads to again
The blade 2 positioned at 3 rear end thread pitch bigger of gap is crossed, forms the downwash flow of angle bigger, angle of downwash degree is bigger, rotor
Lift is higher, reduces the power consumption of aircraft, improves the cruise duration of aircraft.
As shown in fig. 6, in some specific embodiments of the present invention, it is located at the segmentation blade 21 of 3 rear end of the gap
Windward side and/or leeward be provided with multiple sheet protrusions 213, the sheet protrusion 213 and the propeller direction of rotation
It is parallel.Setting sheet protrusion 213, can play guiding function, piece in windward side and leeward to air-flow on segmentation blade 21
Shape protrusion 213 is parallel with propeller direction of rotation, when can prevent air-flow by the larger segmentation blade 21 of the angle of pitch, generates spiral shell
Revolve the dispersion in paddle diametric(al).
In some specific embodiments of the present invention, the blade 2 is fixedly connected with the propeller hub 1 using integrated.
Either, the blade 2 is connect with the wheel hub 1 by blade fold mechanism or blade pitch changing actuator.Above-described paddle
Leaf fold mechanism and blade pitch changing actuator are widely used on varying pitch aircraft, can be according to actual demand change of flight
The screw pitch of device.
As shown in Figure 2-5, in the present invention, the gap 3 being located on each blade 2 is straight along the propeller
The quantity of diameter direction A is one or more.The number of the gap 3 on each blade 2 along the propeller direction of rotation B
Amount is one or more.That is, one or more groups of gaps 3 are offered on the blade 2, the number in gap 3 described in every group
For one or more.Or multigroup gap 3 is offered on the blade 2, multigroup gap 3 is along the diameter side of the propeller
It is arranged to A.Strip gap 3 and the diametric(al) A of propeller are close to parallel.Several special mechanisms are chosen below as specific
Embodiment illustrate：
Embodiment one
As shown in Fig. 2, in the present embodiment, three groups of gaps 3 are offered along the diametric(al) A of propeller, every group of gap 3
Number is 1.That is, opening up three gaps 3 on each blade 2.
Embodiment two
As shown in figure 3, in the present embodiment, two groups of gaps 3 are offered along the diametric(al) A of propeller, close to connecting pin
One group of gap 3 in, the number in gap 3 is 2；In another group of gap 3, the number in gap 3 is 1.
Embodiment three
As shown in figure 4, in the present embodiment, three groups of gaps 3 are offered along the diametric(al) A of propeller, every group of gap 3
Number is 2.
Example IV
As shown in figure 5, the number of the blade 2 is three, three blades 2 are about 11 symmetrical cloth of the pivot center
It sets.
In the description of this specification, reference term " embodiment one ", " embodiment two ", " example ", " specific example " or
The description of " some examples " etc. means that specific method, device or feature described in conjunction with this embodiment or example are contained in this hair
In bright at least one embodiment or example.In the present specification, schematic expression of the above terms are necessarily directed to
Identical embodiment or example.Moreover, specific features, method, apparatus or the feature of description can be in any one or more realities
It applies and can be combined in any suitable manner in example or example.In addition, without conflicting with each other, those skilled in the art can incite somebody to action
The feature of different embodiments or examples and different embodiments or examples described in this specification is combined.
The foregoing is merely presently preferred embodiments of the present invention, is not intended to limit the invention, it is all the present invention spirit and
Within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention.
Claims (10)
- The propeller 1. a kind of gradient pitch multisection type cracks, which is characterized in that including：The longitudinal axis of propeller hub (1), the propeller hub (1) is pivot center (12)；One end of at least two blades (2), the blade (2) is connecting pin, the lateral surface of the connecting pin and the propeller hub (1) Connection, at least two blade (2) axisymmetricly arrange that each blade (2) is along spiral shell about the pivot center (12) The diametric(al) of rotation paddle offer it is one or more for gas by strip gap (3), the gap (3) is from the paddle The leeward perforation setting towards the blade (2) windward of leaf (2).
- 2. a kind of gradient pitch multisection type cracks propeller according to claim 1, which is characterized in that blade (2) edge Its rotation direction includes multiple segmentation blades (21) being sequentially overlapped, and the gap (3) is arranged in two adjacent segmentation blades (21) between.
- 3. a kind of gradient pitch multisection type cracks propeller according to claim 2, which is characterized in that each segmentation paddle Leaf (21) is divided into the leading edge ends (211) and trailing edge ends (212) of segmentation blade (21) along airflow direction, the gap (3) After both sides are respectively the trailing edge ends (212) of the segmentation blade (21) positioned at the gap (3) front end and are located at the gap (3) The leading edge ends (211) of the segmentation blade (21) at end.
- 4. a kind of gradient pitch multisection type cracks propeller according to claim 3, which is characterized in that two neighboring described point Section blade (21), along airflow direction, the trailing edge ends (212) of one of segmentation blade (21) are close to another segmentation blade (21) leading edge ends (211).
- 5. a kind of gradient pitch multisection type cracks propeller according to claim 2, which is characterized in that be located at the gap (3) segmentation blade (21) thread pitch of rear end is more than segmentation blade (21) thread pitch positioned at the gap (3) front end.
- 6. a kind of gradient pitch multisection type cracks propeller according to claim 2, which is characterized in that be located at each paddle Quantity of the gap (3) along the airscrew diameter direction on leaf (2) is one or more.
- 7. a kind of gradient pitch multisection type cracks propeller according to claim 6, which is characterized in that be located at each blade (2) quantity of the gap (3) along the propeller direction of rotation on is one or more.
- 8. a kind of gradient pitch multisection type cracks propeller according to claim 2, which is characterized in that be located at the gap (3) windward side of the segmentation blade (21) of rear end and/or leeward are provided with multiple sheets protrusions (213), the sheet protrusion (213) parallel with the propeller direction of rotation.
- 9. a kind of gradient pitch multisection type cracks propeller according to claim 1, which is characterized in that the blade (2) with The propeller hub (1) is fixedly connected using integration.
- 10. a kind of gradient pitch multisection type cracks propeller according to claim 1, which is characterized in that the blade (2) with The wheel hub (1) is connected by blade fold mechanism or blade pitch changing actuator.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810361876.7A CN108482666A (en) | 2018-04-20 | 2018-04-20 | A kind of gradient pitch multisection type cracks propeller |
| PCT/CN2018/119506 WO2019200941A1 (en) | 2018-04-20 | 2018-12-06 | Gradient pitch multi-section slotted propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810361876.7A CN108482666A (en) | 2018-04-20 | 2018-04-20 | A kind of gradient pitch multisection type cracks propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108482666A true CN108482666A (en) | 2018-09-04 |
Family
ID=63312913
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810361876.7A Pending CN108482666A (en) | 2018-04-20 | 2018-04-20 | A kind of gradient pitch multisection type cracks propeller |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108482666A (en) |
| WO (1) | WO2019200941A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019200941A1 (en) * | 2018-04-20 | 2019-10-24 | 李春 | Gradient pitch multi-section slotted propeller |
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
| CN111547236A (en) * | 2020-05-15 | 2020-08-18 | 中国科学院合肥物质科学研究院 | Coaxial dual-rotor aircraft with asymmetric rotors and control method thereof |
| CN112389630A (en) * | 2020-11-23 | 2021-02-23 | 中国航天空气动力技术研究院 | Weight reduction wing of ultrahigh-speed cruise aircraft in upper atmosphere |
| CN118470239A (en) * | 2024-07-15 | 2024-08-09 | 合肥倍豪海洋装备技术有限公司 | Construction method of hollowed-out propeller three-dimensional model |
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| CN208053630U (en) * | 2018-04-20 | 2018-11-06 | 李春 | A kind of gradient pitch multisection type cracks propeller |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108482666A (en) * | 2018-04-20 | 2018-09-04 | 李春 | A kind of gradient pitch multisection type cracks propeller |
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2018
- 2018-04-20 CN CN201810361876.7A patent/CN108482666A/en active Pending
- 2018-12-06 WO PCT/CN2018/119506 patent/WO2019200941A1/en active Application Filing
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| CN1133252A (en) * | 1995-04-13 | 1996-10-16 | 乐正伟 | New concept air propeller with auxiliary propeller |
| CN1291813A (en) * | 1999-07-30 | 2001-04-18 | 富士康(昆山)电脑接插件有限公司 | Method for electrically connecting coaxial cable to circuit board |
| US20120189457A1 (en) * | 2011-01-25 | 2012-07-26 | Occhipinti Anthony C | Propeller slipstream enhancer |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019200941A1 (en) * | 2018-04-20 | 2019-10-24 | 李春 | Gradient pitch multi-section slotted propeller |
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
| CN111547236A (en) * | 2020-05-15 | 2020-08-18 | 中国科学院合肥物质科学研究院 | Coaxial dual-rotor aircraft with asymmetric rotors and control method thereof |
| CN111547236B (en) * | 2020-05-15 | 2021-08-10 | 中国科学院合肥物质科学研究院 | Coaxial dual-rotor aircraft with asymmetric rotors and control method thereof |
| CN112389630A (en) * | 2020-11-23 | 2021-02-23 | 中国航天空气动力技术研究院 | Weight reduction wing of ultrahigh-speed cruise aircraft in upper atmosphere |
| CN118470239A (en) * | 2024-07-15 | 2024-08-09 | 合肥倍豪海洋装备技术有限公司 | Construction method of hollowed-out propeller three-dimensional model |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019200941A1 (en) | 2019-10-24 |
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Application publication date: 20180904 |
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