CN206511132U - A kind of helicopter integration Complex-cooling system - Google Patents
A kind of helicopter integration Complex-cooling system Download PDFInfo
- Publication number
- CN206511132U CN206511132U CN201621482480.0U CN201621482480U CN206511132U CN 206511132 U CN206511132 U CN 206511132U CN 201621482480 U CN201621482480 U CN 201621482480U CN 206511132 U CN206511132 U CN 206511132U
- Authority
- CN
- China
- Prior art keywords
- radiator fan
- radiator
- cooling
- utility
- cylinder head
- 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.)
- Withdrawn - After Issue
Links
Abstract
The utility model discloses a kind of helicopter with integrated Complex-cooling system, mainly including radiator fan hood, brushless electric machine, motor mounting rack, radiator fan, integrated heat spreader.The utility model solves the problem of Conventional compact aviation is not suitable for helicopter with four-stroke piston engine cooling system.The utility model can cylinder head is air-cooled, cylinder wall water cooling and lubricating oil cooling be integrated together, with the features such as lightweight, simple in construction, energy consumption is smaller, space-consuming is smaller；Fan system of the present utility model can also carry out subsidiary wind-cooling heat dissipating, effect is more preferable while radiator effectively being cooled down to lubricating oil and cylinder head liquid cooling radiator radiates to cylinder head；The utility model rotation speed of the fan is adjustable, is applicable to different environment temperatures, and energy consumption is reduced while great heat radiation effect is reached.
Description
Technical field
The utility model is related to technical field of aerospace, more particularly to a kind of helicopter integration Complex-cooling system
System.
Background technology
Small-sized aviation with four-stroke piston engine housing cooling system (as shown in Figure 1) and oil cooling system (such as
Shown in Fig. 2) more using water cooling and the form of air-cooled combination.
Such as Fig. 1, small-sized aviation is divided into cylinder head cooling and cylinder wall with four-stroke piston engine housing cooling system
Cooling, general cylinder head uses liquid cooling, and cylinder wall is cooled down using air.The cooling system of cylinder head is a band expansion
The circulatory system of the closing of case, i.e., press to cylinder head from radiator by coolant by bent shaft-driven water pump, take away cylinder head
The expansion tank positioned at engine top is reached after heat, recycles the gravitional force of coolant to be back to radiator, so circulation
The reciprocal purpose to reach cooling cylinder head.Expansion tank carries excess pressure valve and return valve, when it act as coolant temperature rise
Excess pressure valve is opened, and coolant is flowed in overflow bottle；After temperature reduction, coolant is sucked back into the circulatory system again, passes through this side
Formula maintains pressure in the circulatory system.General cylinder wall is cooled down using air, i.e., the cold air band moved using opposite engine
Walk the heat on cylinder wall.
Such as Fig. 2, the cylinder of the small-sized aviation similar cylinder body of four-stroke piston engine oil cooling system methods for cooling
Head liquid cooling, i.e. main oil pump suction out lubricating oil from oil tank, and each oil site, unnecessary lubricating oil are reached by oil cooler
Accumulate in oil groove, then sent back to by gaseous-pressure in oil tank.
Fixed wing aircraft being applied to above-mentioned engine-cooling system, its engine is normally at body foremost, right more
For cylinder wall cooling, relative air speed is larger and more lasting, is pressurized by propeller, the kinetic energy of air-flow, flow and
Position relative to engine all comparatively facilitates the radiating of cylinder wall.If above-mentioned engine-cooling system is applied into helicopter
In, rotor down-wash flow continues, efficiently cylinder wall is radiated like that without image of Buddha fixed-wing relative wind；Cylinder head radiator
Structural system with the discrete arrangement of oil cooler also with helicopter compact efficient is runed counter to.
Utility model content
In order to overcome the above-mentioned deficiencies of the prior art, the utility model provides a kind of helicopter with integrated composite type cold
But system, to solve the problem of Conventional compact aviation is not suitable for helicopter with four-stroke piston engine cooling system.This
Utility model can cylinder head is air-cooled, cylinder wall water cooling and lubricating oil cooling be integrated together, with lightweight, simple in construction, energy
The features such as consumption is smaller, space-consuming is smaller, while the utility model can also effectively solve lifting airscrew purling to gas
The problem of casing wall air-cooled scarce capacity.
The technical scheme that the utility model is used is：A kind of helicopter integrated Complex-cooling system, main bag
Include radiator fan hood, brushless electric machine, motor mounting rack, radiator fan, integrated heat spreader.Radiator fan is installed on brushless electric machine and turned
On axle, brushless electric machine casing is arranged on radiator fan hood top by motor mounting rack, and now radiator fan interior can be lining in radiating
In fan guard；Radiator fan hood is installed in engine head with integrated heat spreader, and the two position relationship is put for radiator fan hood
In the surface of integrated heat spreader.Brushless electric machine drives radiator fan to be rotated with certain rotating speed after being powered, by engine upper end
Air pressurized is radiated after accelerating by integrated heat spreader for it, and air-flow continues down through cylinder wall and cylinder wall and dissipated
Heat.Integrated heat spreader structure is divided into two parts, and a part cools down radiator for lubricating oil, and another part dissipates for cylinder head liquid cooling
Hot device.
Compared with prior art, the utility model solves Conventional compact aviation four-stroke piston engine cooling system
Not the problem of system is not suitable for helicopter.The utility model can cylinder head is air-cooled, cylinder wall water cooling and lubricating oil cooling be integrated into one
Rise, with the features such as lightweight, simple in construction, energy consumption is smaller, space-consuming is smaller；Fan system of the present utility model is effective
While cooling down radiator and cylinder head liquid cooling radiator to lubricating oil and radiate, cylinder head can also be attached
Wind-cooling heat dissipating, effect is more preferable；The utility model rotation speed of the fan is adjustable, is applicable to different environment temperatures, good reaching
Energy consumption is reduced while radiating effect.
Brief description of the drawings
Fig. 1 small-sized aviations four-stroke piston engine cylinder block cooling system schematic diagram；
Fig. 2 small-sized aviations four-stroke piston engine oil cooling system schematic diagram；
Fig. 3 helicopters integration Complex-cooling system composition schematic diagram；
Fig. 4 integrated heat spreader composition schematic diagrams；
Fig. 5 helicopters integration Complex-cooling system operating diagram；
Symbol description is as follows in figure：
1st, radiator fan hood；2nd, brushless electric machine；3rd, motor mounting rack；4th, radiator fan；5th, integrated heat spreader；6th, lubricating oil is cold
But radiator；7th, cylinder head liquid cooling radiator；8th, engine；9th, high temperature coolant；10th, cryogenic liquid；11st, high temperature is slided
Oil；12nd, low temperature lubricating oil；13rd, cooling air-flow；14th, lubricating oil bottle.
Embodiment
See Fig. 3-Fig. 5, the utility model is further illustrated below in conjunction with the accompanying drawings.In order to overcome above-mentioned prior art
Deficiency, the utility model provides a kind of helicopter with integrated Complex-cooling system, and four are used to solve Conventional compact aviation
Not the problem of single stroke piston type engine cooling system is not suitable for helicopter.
Referring to Fig. 3-Fig. 5, constituted such as with the related system of integrated Complex-cooling system to the helicopter of the present embodiment
Under：
Radiator fan 4 is installed in the rotating shaft of brushless electric machine 2, and the casing of brushless electric machine 2 is arranged on radiating by motor mounting rack 3
The top of fan guard 1, now radiator fan 4 can in be lining in radiator fan hood 1；Radiator fan hood 1 is respectively mounted with integrated heat spreader 5
In engine head, the two position relationship is the surface that radiator fan hood 1 is placed in integrated heat spreader 5.After brushless electric machine 2 is powered
Drive radiator fan 3 to be rotated with certain rotating speed, by integrated heat spreader 5 be it after the air pressurized of the upper end of engine 8 is accelerated
Radiating, air-flow continues down through cylinder wall and radiated.The structure of integrated heat spreader 5 is divided into two parts, and a part is lubricating oil
Radiator 6 is cooled down, another part is cylinder head liquid cooling radiator 7.
Referring to Fig. 3-Fig. 5, the present embodiment cooling procedure is as follows：
When engine 8 starts, start brushless electric machine 2 and drive radiator fan 4 will be colder in environment from the top of radiator fan hood 1
Air suction, cold air is blowed to by integrated heat spreader 5 using the form of aerofoil fan, by air after integrated heat spreader 5 after
Continuous flow downward blows to cylinder wall and cylinder head, and air flow direction is as shown in cooling air-flow 13 in Fig. 5.At the same time, in engine 8
Oil pump and water pump also work simultaneously.Cryogenic liquid 10 is changed into high temperature coolant after cylinder head in cylinder head cooling system
9, in the cylinder head liquid cooling radiator 7 that high temperature coolant 9 flows to integrated heat spreader 5 from cylinder head, by cooling air-flow 13
Cooling effect, high temperature coolant 9 is converted into cryogenic liquid 10, flows back to cylinder head in the presence of water pump in engine 8, such as
This moves in circles is radiated with lasting for cylinder head；Low temperature lubricating oil 12 passes through each machine of engine 8 in oil cooling system
It is changed into high temperature lubricating oil 11 after structure, high temperature lubricating oil 11 is flowed back in lubricating oil bottle 14 from the bottom oil box of engine 8 under lubricating oil pumping action,
The lower high temperature lubricating oil 11 of pressure effect flows out from lubricating oil bottle and flows to lubricating oil cooling radiator 6, by the cooling of cooling air-flow 13
Effect, high temperature lubricating oil 11 is converted into low temperature lubricating oil 12, and low temperature lubricating oil 12 flows to engine 8 from lubricating oil cooling radiator 6 afterwards, such as
This moves in circles, to keep normal lubrication of the lubricating oil at a lower temperature to each mechanism part of engine 8.
The rotating speed of brushless electric machine 2 can adjust in the present embodiment, at different ambient temperatures, the regulation rotating speed of brushless electric machine 2 and work(
Rate, can make the utility model to meet the radiating requirements of engine, and the effect of reduction energy consumption can be reached again.
The helicopter that the utility model is provided solves four punchings of Conventional compact aviation with integrated Complex-cooling system
Not the problem of journey piston-mode motor cooling system is not suitable for helicopter.The utility model can cylinder head is air-cooled, cylinder wall water
The cooling of cold and lubricating oil is integrated together, with the features such as lightweight, simple in construction, energy consumption is smaller, space-consuming is smaller；This practicality
New fan system to lubricating oil while radiator is effectively cooled down and cylinder head liquid cooling radiator radiates, also
Subsidiary wind-cooling heat dissipating can be carried out to cylinder head, effect is more preferable；The utility model rotation speed of the fan is adjustable, is applicable to different
Environment temperature, energy consumption is reduced while great heat radiation effect is reached.
Claims (1)
1. a kind of helicopter integration Complex-cooling system, it is characterised in that：It include radiator fan hood, brushless electric machine,
Motor mounting rack, radiator fan, integrated heat spreader, radiator fan are installed in brushless electric machine rotating shaft, and brushless electric machine casing passes through
Motor mounting rack is arranged on radiator fan hood top, and now radiator fan interior can be lining in radiator fan hood；Radiator fan hood with
Integrated heat spreader is installed in engine head, and the two position relationship is the surface that radiator fan hood is placed in integrated heat spreader,
Brushless electric machine drives radiator fan to be rotated with certain rotating speed after being powered, by integrated after the air pressurized of engine upper end is accelerated
Radiator radiates for it, and air-flow continues down through cylinder wall and cylinder head and radiated, and integrated heat spreader structure is divided into two
Part a, part cools down radiator for lubricating oil, and another part is cylinder head liquid cooling radiator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621482480.0U CN206511132U (en) | 2016-12-30 | 2016-12-30 | A kind of helicopter integration Complex-cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621482480.0U CN206511132U (en) | 2016-12-30 | 2016-12-30 | A kind of helicopter integration Complex-cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206511132U true CN206511132U (en) | 2017-09-22 |
Family
ID=59864116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621482480.0U Withdrawn - After Issue CN206511132U (en) | 2016-12-30 | 2016-12-30 | A kind of helicopter integration Complex-cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206511132U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741978A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of helicopter integration Complex-cooling system |
-
2016
- 2016-12-30 CN CN201621482480.0U patent/CN206511132U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741978A (en) * | 2016-12-30 | 2017-05-31 | 中航维拓（天津）科技有限公司 | A kind of helicopter integration Complex-cooling system |
| CN106741978B (en) * | 2016-12-30 | 2023-09-29 | 重庆驼航科技有限公司 | Integrated composite cooling system for helicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106741978A (en) | A kind of helicopter integration Complex-cooling system | |
| CN104136322B (en) | The turbogenerator cabin of heat exchanger is housed | |
| US20190128570A1 (en) | Thermal management system | |
| WO2020033010A3 (en) | Aircraft drag reduction system and internally cooled electric motor system and aircraft using same | |
| CN206511132U (en) | A kind of helicopter integration Complex-cooling system | |
| CN106194385A (en) | Cooling fan of internal combustion locomotive control method | |
| CN206753860U (en) | Compressor cooling fan | |
| CN108869322A (en) | A kind of water pump having high-cooling property | |
| CN108216642A (en) | A kind of Reheat-type cooling turbine unit system applied to aircraft pod | |
| CN206397759U (en) | A kind of chamber flow heat dissipation device | |
| CN205248989U (en) | Circulative cooling motor in oil | |
| CN207568983U (en) | A kind of engineering machinery integrated hydraulic fuel tank | |
| CN219018623U (en) | Motor rotating shaft with forced cooling device | |
| CN108835843A (en) | A kind of summer open air cooling-down air conditioner knapsack | |
| CN104747260A (en) | Novel helicopter water-cooled engine cooling system | |
| CN108952936A (en) | A kind of automobile radiators produced wind using traveling process | |
| CN205714834U (en) | A kind of centrifugal high pressure fan with cooling device | |
| CN209730991U (en) | A kind of empty oily combination cooling electric moto used in compressor | |
| CN108995818A (en) | Ducted fan | |
| CN207939352U (en) | A kind of New energy automobile motor that heat dissipation effect is excellent | |
| CN206983719U (en) | A kind of Major off road hybrid power vehicle double electric machine system radiator | |
| CN217462620U (en) | Fan with simple structure | |
| CN202215717U (en) | Integrated cooling device | |
| JP2016052821A (en) | Electrically-driven unit cooling system for aircraft | |
| CN215490472U (en) | Energy-saving control equipment for refrigeration host |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180117 Address after: 516000 Hongxing Village, Huizhou City, Guangdong Province Patentee after: HUIZHOU JIEXIN INDUSTRY Co.,Ltd. Address before: 300300 Tianjin City Industrial Park Dongli District takeoff rations Road No. 3 block B Patentee before: AVIC WEITUO (TIANJIN) TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190906 Address after: 404100 North Section 390 Shuangfu Street, Jiangjin District, Chongqing Patentee after: Chongqing Camel Aviation Technology Co.,Ltd. Address before: 516000 Hongxing Village, Huihuan Office, Huizhou City, Guangdong Province Patentee before: HUIZHOU JIEXIN INDUSTRY Co.,Ltd. |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170922 Effective date of abandoning: 20230929 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20170922 Effective date of abandoning: 20230929 |