CN108995818A - Ducted fan - Google Patents
Ducted fan Download PDFInfo
- Publication number
- CN108995818A CN108995818A CN201710422428.9A CN201710422428A CN108995818A CN 108995818 A CN108995818 A CN 108995818A CN 201710422428 A CN201710422428 A CN 201710422428A CN 108995818 A CN108995818 A CN 108995818A
- Authority
- CN
- China
- Prior art keywords
- ducted fan
- propeller hub
- hub axis
- duct
- stator blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001816 cooling Methods 0.000 claims description 62
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 23
- 239000002826 coolant Substances 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 13
- 239000012530 fluid Substances 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 7
- 230000005855 radiation Effects 0.000 claims description 7
- 238000003466 welding Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 11
- 230000017525 heat dissipation Effects 0.000 abstract description 8
- 238000006243 chemical reaction Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 241001672694 Citrus reticulata Species 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Abstract
The present invention provides a kind of ducted fan, comprising: duct has central axis, and an air inlet and an air outlet are located at the top and bottom of duct；Propeller hub axis, is arranged on the central axis of duct；Multiple movable vane pieces are arranged on propeller hub axis simultaneously close air inlet and can rotate with propeller hub axis；Fixes sleeve, propeller hub axis are installed in fixes sleeve；Multiple stator blades, opposite end are connect with the inner wall of fixes sleeve and duct respectively, are provided with radiator structure on each stator blade；And power drive unit, it is arranged in fixes sleeve and is located at below multiple movable vane pieces, power drive unit drives the rotation of propeller hub axis with propeller hub axis connection and power drive unit is connect to be radiated by radiator structure with radiator structure.Radiator structure is arranged on the stator blade of ducted fan or is integrally formed radiator structure and stator blade, stator blade is made to have the function of heat sinking function while also there is balance reaction torque, significantly improves heat dissipation effect, while also saving space.
Description
Technical field
The present invention relates to aircraft fields, and more particularly, to a kind of ducted fan.
Background technique
Cooling problem is always a crux of aircraft engine.The quality of engine-cooling system directly affects
The performance and used life of engine.The cooling system of general engine is all active cooling, that is, makes air using cooling fan
High speed blows over fin surface, takes away the heat that engine sheds, makes engine cool.But in Flight Vehicle Design, in order to
Mitigate aircraft weight and usually saves cooling fan.Without the high-speed flow that fan provides, cooling efficiency will be greatly reduced, give
The design of aircraft brings serious problem.
In the prior art, the radiator of engine has been placed on to the entrance of duct, it is desirable to by the air-flow band for entering duct
Walk heat.But the air speed of incoming flow of duct entrance is limited, very with the air velocity difference after the acceleration of duct movable vane piece
Far.It is little with the air-flow cooling efficiency of inlet, it is therefore desirable to reach the heat dissipation effect of requirement by increasing radiator volume,
But this will increase the overall weight of flight packet, and influence beautiful.
Summary of the invention
For problem present in the relevant technologies, the purpose of the present invention is to provide a kind of ducted fan, the ducted fans
By radiator layout in ducted fan, to radiate using the high-speed flow in ducted fan, the cold of radiator is significantly improved
But effect；In addition, radiator structure is arranged on stator blade the ducted fan, to save encapsulated space.
To achieve the above object, the present invention provides a kind of ducted fans, comprising: duct, duct have central axis, one
Air inlet and an air outlet are located at the top and bottom of duct；Propeller hub axis, is arranged on the central axis of duct；It is multiple dynamic
Blade is arranged on propeller hub axis simultaneously close to air inlet, and can rotate with the rotation of propeller hub axis；Fixes sleeve, the installing of propeller hub axis
In in fixes sleeve；Multiple stator blades, the opposite end of stator blade are connect with the inner wall of fixes sleeve and duct respectively, Mei Gejing
Radiator structure is provided on blade；And power drive unit, it is arranged in fixes sleeve and is located at below multiple movable vane pieces,
Wherein, power drive unit and propeller hub axis connection are to drive propeller hub axis to rotate, and power drive unit is connect with radiator structure
To be radiated by radiator structure.
According to one embodiment of present invention, radiator structure is the cooling fin being attached on the outer surface of each stator blade,
Radiation fin cooling tube road is equipped in cooling fin.
According to one embodiment of present invention, power drive unit includes engine, is equipped with engine cool in engine
Pipeline, the output shaft and propeller hub axis connection of engine are to drive propeller hub axis to rotate, and engine cool pipeline and cooling fin are cold
But pipeline fluid connection is to form coolant circuit.
According to one embodiment of present invention, cooling fin includes the upper water chamber and lower water chamber being connected to via multiple heat-dissipating pipes,
Wherein, the communication of upper water chamber and engine cool pipeline, and the entrance stream of lower water chamber and engine cool pipeline
Body connection.
According to one embodiment of present invention, multiple heat-dissipating pipes are set in parallel to each other, and between adjacent heat-dissipating pipe
It is additionally provided with multiple radiating fins.
According to one embodiment of present invention, the inlet of engine cool pipeline is provided with water pump, it will be through multiple
The cooling coolant liquid of cooling fin is sent back in engine cool pipeline.
According to one embodiment of present invention, the exit of engine cool pipeline is provided with thermostat.
According to one embodiment of present invention, multiple movable vane pieces are angularly distributed around central axis, and each movable vane piece
String and movable vane piece rotation horizontal plane formed angle.
According to one embodiment of present invention, multiple stator blades are angularly distributed around central axis, and each stator blade
Perpendicular to the cross section of duct.
According to one embodiment of present invention, propeller hub axis top is provided with radome fairing, radome fairing is located at multiple movable vane pieces
Top and rotated with the rotation of movable vane piece.
According to one embodiment of present invention, multiple cooling fins by welding, rivet or be bolted be fixed on it is multiple quiet
On the surface of blade.
According to one embodiment of present invention, cooling fin can be integrally formed with corresponding stator blade.
The beneficial technical effect of the present invention lies in:
Radiator structure is arranged on the stator blade of ducted fan or is integrally formed radiator structure and stator blade by the present invention,
So that stator blade is had the function of heat sinking function while also there is balance reaction torque, the high-speed flow in ducted fan passes through, significantly
The heat dissipation effect to engine is improved, so that the temperature for guaranteeing engine improves engine within the scope of normal working temperature
Fuel efficiency, ensure the safety of flight；
In addition, engine radiator is arranged on the stator blade of ducted fan ducted fan of the invention, subtract significantly
Small encapsulated space.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 instantiates the structural schematic diagram of ducted fan according to an embodiment of the invention；
Fig. 2 instantiates ducted fan shown in FIG. 1 along the sectional view of plane interception where central axis；And
Fig. 3 instantiates the connection side of engine and cooling fin in ducted fan according to an embodiment of the invention
Formula.
Specific embodiment
Below with reference to attached drawing, the embodiment of the present invention is specifically described.It should be noted that following each implementation
Example can be combined with each other in any possible manner or partial replacement.
Referring to figs. 1 to Fig. 3, the ducted fan of an exemplary embodiment according to the present invention is shown.In the embodiment
In, as seen from Figure 1, ducted fan includes duct 1, propeller hub axis, multiple movable vane pieces 2, fixes sleeve, multiple stator blades 3 and moves
Force driving device 4.Specifically, duct 1 is the cylindrical channel with central axis, and an air inlet and an air outlet are located at
The top and bottom of duct 1, propeller hub axis and duct 1 are placed coaxially in fixes sleeve, and multiple movable vane pieces 2 are set adjacent to air inlet
It sets on propeller hub axis, wherein all movable vane pieces 2 radially arrange around propeller hub axis and can rotate with the rotation of propeller hub axis, often
The opposite end of a stator blade 3 is connect with the inner wall of fixes sleeve and duct 1 respectively, and is provided on each stator blade 3
Radiator structure, power drive unit 4 are located in fixes sleeve and the lower section of multiple movable vane pieces 2 are arranged in, wherein power drive dress
4 are set with propeller hub axis connection to drive propeller hub axis to rotate, so that the multiple movable vane pieces 2 being arranged on propeller hub axis be driven to rotate；In addition,
Power drive unit 4 is also connect with radiator structure, to be radiated by radiator structure.
Valuably, in the above-described embodiments, ducted fan is by ducted fan, utilizing duct for radiator structure layout
High-speed flow heat dissipation in fan, significantly improves the cooling effect of radiator structure, to guarantee the temperature of power drive unit 4
Within the scope of normal working temperature, the efficiency of power drive unit 4 is improved, ensures the safety of flight；In addition, in above-mentioned implementation
In ducted fan shown in example, by being arranged radiator structure on stator blade 3, encapsulated space can be saved significantly.
Illustratively, in a possible embodiment of the invention, as shown in Figure 1 to Figure 3, radiator structure is embodied as pasting
The cooling fin being attached on the outer surface of each stator blade 3 is equipped with radiation fin cooling tube road in each cooling fin.Further example
Property, according to invention possible embodiment, power drive unit 4 includes engine, and it is cold to be equipped with engine in engine
But pipeline, the output shaft of engine and propeller hub axis connection to drive propeller hub axis to rotate, thus drive be connected to it is more on propeller hub axis
A movable vane piece 2 rotates.In addition, the engine cool pipeline of engine and the radiation fin cooling tube road of cooling fin are in fluid communication with shape
At coolant circuit, to realize engine cool by cooling fin.
In the above exemplary embodiments, it is beneficial to, ducted fan is utilized by that will radiate chip layout in duct 1
High-speed flow heat dissipation in duct 1, significantly improves the cooling effect of cooling fin, to guarantee the temperature of engine in normal work
Make in temperature range, improve the fuel efficiency of engine, ensures the safety of flight.In some embodiments, cooling fin can lead to
The common fastening means in this fields such as welding, rivet is crossed or is bolted to be fixed on the surface of stator blade 3；In addition, another
In a little embodiments, cooling fin can be also integrally formed with corresponding stator blade 3, changed an angle and said, i.e., cooling fin is fabricated to stator blade 3
Configuration, can regard cooling fin as and stator blade is integrated construction, therefore there is heat dissipation and the balance reaction torque of stator blade 3 simultaneously
Effect, this by cooling fin and the integrated construction of stator blade 3 in the present embodiment, structure is simpler, also makes overall structure more
It is compact, encapsulated space is reduced significantly.
With continued reference to Fig. 3, the specific configuration of cooling fin is described in detail.As shown, each cooling fin includes being located at
Above and below upper water chamber 6 and lower water chamber 7, wherein upper water chamber 6 and lower water chamber 7 are in fluid communication via multiple heat-dissipating pipes 5.Its
In, the communication of upper water chamber 6 and engine cool pipeline, to receive the cold of the need cooling from engine cool pipeline
But liquid and being sent in radiation fin cooling tube road is cooled down；The entrance of lower water chamber 7 and engine cool pipeline is in fluid communication,
Will be sent back in engine cool pipeline through cooling coolant liquid, the cooling for engine.
Preferably, in a possible embodiment of the invention, all heat-dissipating pipes 5 are parallel to each other orientation, and in institute
Multiple radiating fins are additionally provided between the adjacent heat radiation pipe 5 for having heat-dissipating pipe 5, to further enhance heat dissipation effect.
In addition, in other possible embodiments of the invention, as shown in figure 3, in the inlet of engine cool pipeline
It is provided with water pump 8, the effect of water pump 8, which is to send back in engine cool pipeline through the cooling coolant liquid of cooling fin, to be used to start
Machine is cooling.Additionally or alternatively, in another possible embodiment of the invention, as shown in figure 3, in engine cool pipe
The exit on road is provided with thermostat 9, and the effect of thermostat 9 is to control the flow direction of the coolant liquid in engine cool pipeline.Example
Such as, when the temperature of the coolant liquid in engine cool pipeline is lower than 80 degree, thermostat 9 is closed, and coolant liquid, which directly flows back to, starts
Machine does not flow to cooling fin, to guarantee engine operation in suitable temperature；When the temperature of the coolant liquid in engine cool pipeline
When degree is higher than 80 degree, thermostat 9 is opened, and coolant liquid flow to cooling fin by conduit, cooled down by cooling fin.
Preferably, in above-mentioned each embodiment or the other embodiment of the present invention, as shown in Figure 1, ducted fan includes
Four movable vane pieces 2 being angularly distributed around the central axis of duct 1, and the string of each movable vane piece 2 and movable vane piece rotate water
Plane forms angle；Similarly, in above-mentioned each embodiment or the other embodiment of the present invention, ducted fan includes around duct
Six stator blades 3 that 1 central axis is angularly distributed, and stator blade 3 be in tabular, flat stator blade 3 perpendicular to
The cross section of duct 1 and be arranged.
It is further preferred that in some possible embodiments of the invention, as shown in Figure 1, can pacify on propeller hub axis top
Radome fairing 10 is filled, radome fairing 10 is located in the top of multiple movable vane pieces 2 and rotates with the rotation of multiple movable vane pieces 2.Have
Beneficially, radome fairing 10 can play the role of rectification to the air-flow for the air inlet for entering duct 1, and ducted fan is made to become a mandarin more
It is even.
In cooling fin and the integrally formed embodiment of stator blade 3, such as Fig. 1 so, in ducted fan work, engine
It drives movable vane piece 2 to rotate by transmission shaft, so that air is entered duct 1 from the air inlet of duct 1 and accelerate, air-flow flows through movable vane
Piece 2 can generate torque and thrust, and thrust drives aircraft takeoff, and cooling fin can generate reactive torque when air-flow passes through, from
And play the role of offset torque；Meanwhile coolant liquid flows through the water jacket of the cylinder of engine, coolant liquid under the action of water pump 8
Through water jacket by the heat absorption of engine, entire cooling fin is then flowed through；Wherein, cooling fin can be aluminum alloy material, when high speed
After air-flow blows over cooling fin, amount of heat is taken away by air, to reduce coolant temperature.Coolant liquid after cooling is by starting
Machine cooling line flows back to engine again, continues cooling engine by the promotion of water pump, the circulation for forming a fluid for radiating heat is high
Fast air-flow flows through cooling fin, has been also greatly facilitate the heat dissipation of engine.
It should be noted that ducted fan of the invention is mainly used in the culvert type flight for moving engine using gasoline
Device, but it is applied equally to other any aircraft using duct offer lift.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (12)
1. a kind of ducted fan characterized by comprising
Duct (1), the duct (1) have central axis, and an air inlet and an air outlet are located at the upper of the duct (1)
End and lower end；
Propeller hub axis is arranged on the central axis of the duct (1)；
Multiple movable vane pieces (2), are arranged on the propeller hub axis and close to the air inlet, and can with the rotation of the propeller hub axis and
Rotation；
Fixes sleeve, the propeller hub axis are installed in the fixes sleeve；
Multiple stator blades (3), the opposite end of each stator blade (3) respectively with the fixes sleeve and the duct (1)
Inner wall connection, be provided with radiator structure on each stator blade (3)；And
Power drive unit (4) is arranged in the fixes sleeve and is located at below the multiple movable vane piece (2),
Wherein, the power drive unit (4) and the propeller hub axis connection are to drive the propeller hub axis to rotate, and the power
Driving device (4) is connect to be radiated by the radiator structure with the radiator structure.
2. ducted fan according to claim 1, which is characterized in that the radiator structure is to be attached to each stator blade
Cooling fin on the outer surface of piece (3) is equipped with radiation fin cooling tube road in the cooling fin.
3. ducted fan according to claim 2, which is characterized in that the power drive unit (4) includes engine, institute
It states and is equipped with engine cool pipeline in engine, the output shaft of the engine and the propeller hub axis connection are to drive the propeller hub
Axis rotation, and the engine cool pipeline and the radiation fin cooling tube road are in fluid communication to form coolant circuit.
4. ducted fan according to claim 3, which is characterized in that the cooling fin includes via multiple heat-dissipating pipes (5)
The upper water chamber (6) and lower water chamber (7) of connection, wherein the outlet fluid of the upper water chamber (6) and the engine cool pipeline connects
It is logical, and the entrance of the lower water chamber (7) and the engine cool pipeline is in fluid communication.
5. ducted fan according to claim 4, which is characterized in that the multiple heat-dissipating pipe (5) is set in parallel to each other,
And multiple radiating fins are additionally provided between the adjacent heat-dissipating pipe (5).
6. ducted fan according to claim 4, which is characterized in that in the inlet of the engine cool pipeline
Water pump (8) are provided with, will be sent back in the engine cool pipeline through the cooling coolant liquid of the cooling fin.
7. ducted fan according to claim 4, which is characterized in that be arranged in the exit of the engine cool pipeline
There are thermostat (9).
8. ducted fan according to claim 1, which is characterized in that the multiple movable vane piece (2) is around the central axis
It is angularly distributed, and the string of each movable vane piece (2) and movable vane piece rotation horizontal plane form angle.
9. ducted fan according to claim 1, which is characterized in that the multiple stator blade (3) is around the central axis
It is angularly distributed, and each stator blade (3) is perpendicular to the cross section of the duct (1).
10. ducted fan according to claim 3, which is characterized in that propeller hub axis top is provided with radome fairing
(10), the radome fairing (10) is located at the top of the multiple movable vane piece (2) and turns with the rotation of the multiple movable vane piece (2)
It is dynamic.
11. ducted fan according to claim 1, which is characterized in that the cooling fin is connected by welding, riveting or bolt
It connects and is fixed on the surface of each stator blade (3).
12. ducted fan according to claim 1, which is characterized in that the cooling fin can be with the corresponding stator blade
(3) it is integrally formed.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710422428.9A CN108995818A (en) | 2017-06-07 | 2017-06-07 | Ducted fan |
| PCT/CN2018/079749 WO2018223748A1 (en) | 2017-06-07 | 2018-03-21 | Duct fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710422428.9A CN108995818A (en) | 2017-06-07 | 2017-06-07 | Ducted fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108995818A true CN108995818A (en) | 2018-12-14 |
Family
ID=64565723
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710422428.9A Pending CN108995818A (en) | 2017-06-07 | 2017-06-07 | Ducted fan |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108995818A (en) |
| WO (1) | WO2018223748A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111137082A (en) * | 2019-12-30 | 2020-05-12 | 长春理工大学 | Single-duct land air cross-domain robot and control method thereof |
| CN115750439A (en) * | 2022-11-16 | 2023-03-07 | 南昌航空大学 | Air-cooled integrated ducted fan based on boundary layer intake |
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| FR3006996B1 (en) * | 2013-06-14 | 2016-12-09 | European Aeronautic Defence & Space Co Eads France | ELECTRICAL PROPULSION ASSEMBLY FOR AIRCRAFT |
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| CN101178027A (en) * | 2006-10-19 | 2008-05-14 | 通用电气公司 | Heat exchanger assembly for a gas turbine engine |
| CN101050727A (en) * | 2007-05-09 | 2007-10-10 | 韩培洲 | Medium cooling isobaric backheating gas turbine |
| CN102971493A (en) * | 2010-07-09 | 2013-03-13 | 株式会社Ihi | Turbine blade and engine component |
| US20150285186A1 (en) * | 2013-02-20 | 2015-10-08 | United Technologies Corporation | Integrated Heat Exchangers for Low Fan Pressure Ratio Feared Turbofan |
| US20160318619A1 (en) * | 2013-05-31 | 2016-11-03 | General Electric Company | Cooled cooling air system for a gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111137082A (en) * | 2019-12-30 | 2020-05-12 | 长春理工大学 | Single-duct land air cross-domain robot and control method thereof |
| CN115750439A (en) * | 2022-11-16 | 2023-03-07 | 南昌航空大学 | Air-cooled integrated ducted fan based on boundary layer intake |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2018223748A1 (en) | 2018-12-13 |
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