CN112855327A - Air-cooled drainage device of small-sized aero-engine - Google Patents
Air-cooled drainage device of small-sized aero-engine Download PDFInfo
- Publication number
- CN112855327A CN112855327A CN202110164293.7A CN202110164293A CN112855327A CN 112855327 A CN112855327 A CN 112855327A CN 202110164293 A CN202110164293 A CN 202110164293A CN 112855327 A CN112855327 A CN 112855327A
- Authority
- CN
- China
- Prior art keywords
- air
- engine
- guide cavity
- air guide
- 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.)
- Pending
Links
- 230000001939 inductive effect Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 5
- 230000017525 heat dissipation Effects 0.000 abstract description 14
- 230000006698 induction Effects 0.000 abstract 3
- 239000012535 impurity Substances 0.000 description 9
- 230000003749 cleanliness Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P1/00—Air cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
- F01P11/12—Filtering, cooling, or silencing cooling-air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P5/00—Pumping cooling-air or liquid coolants
- F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P5/00—Pumping cooling-air or liquid coolants
- F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
- F01P5/04—Pump-driving arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F1/00—Cylinders; Cylinder heads
- F02F1/02—Cylinders; Cylinder heads having cooling means
- F02F1/04—Cylinders; Cylinder heads having cooling means for air cooling
- F02F1/06—Shape or arrangement of cooling fins; Finned cylinders
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0065—Shape of casings for other machine parts and purposes, e.g. utilisation purposes, safety
- F02F7/007—Adaptations for cooling
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention provides an air-cooled drainage device of an aviation small-sized engine, which comprises an air guide cover body, wherein the left end of the air guide cover body is provided with a first air guide cavity, the right end of the air guide cover body is provided with a second air guide cavity, the middle part of the air guide cover body is provided with a third air guide cavity, and the upper end of the air guide cover body is provided with an air inlet. The cylinder head I is fixedly arranged inside the air guide cavity I, the cylinder head II is fixedly arranged inside the air guide cavity II, the engine is fixedly arranged inside the air guide cavity III, and the engine, the cylinder head I and the cylinder head II are of an integrated structure, so that cold air can be used for radiating the engine more intensively, and the utilization rate and the radiating efficiency of the cold air are improved. The fan is rotatably arranged at the upper end of the output end of the engine, so that the fan and the engine form a whole, the engine rotates to drive the fan to rotate, cold air is sucked from the air inlet and is transmitted to each part of the engine, which needs to dissipate heat, through the first air induction channel, the second air induction channel and the third air induction channel, and the whole heat dissipation is carried out on the device.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an air-cooled drainage device for an aviation small engine.
Background
An engine is a machine capable of converting other forms of energy into mechanical energy, and includes, for example, an internal combustion engine (gasoline engine, etc.), an external combustion engine (stirling engine, steam engine, etc.), an electric motor, etc., and the internal combustion engine converts chemical energy into mechanical energy, and is suitable for both a power generation device and an entire machine including a power device, and the engine was originally produced in the uk, so the concept of the engine is also derived from english, and its meaning refers to "a mechanical device for generating power".
Because the small-size engine of aviation is in encapsulated situation, so must dispel the heat to it, traditional small-size engine air-cooled system of aviation all needs to set up the power supply in addition, and the structure is complicated and is inconvenient for install to the heat dissipation is inhomogeneous, and the fan is also inconvenient for the clearance.
Disclosure of Invention
The invention aims to provide an air-cooling drainage device for an aviation small-sized engine, which aims to solve the problems that the aviation small-sized engine needs to be radiated because the aviation small-sized engine is in a sealed state, the traditional air-cooling system of the aviation small-sized engine needs to be additionally provided with a power source, the structure is complex, the installation is inconvenient, the radiation is not uniform, and a fan is inconvenient to clean in the background art.
In order to achieve the purpose, the invention provides the following technical scheme:
an air-cooled drainage device for an aero-small engine, comprising:
an engine;
the first cylinder head is arranged on one side of the engine;
the second cylinder head is arranged on the other side of the engine;
the wind guide cover body is arranged on the periphery of the engine and comprises a first wind guide cavity, a second wind guide cavity and a third wind guide cavity,
wherein,
the engine is accommodated in the first air guide cavity, the first cylinder head is accommodated in the second air guide cavity, and the second cylinder head is accommodated in the third air guide cavity; the upper end of the air guide cavity is provided with an air inlet, and the bottom end of the air guide cavity is provided with an air outlet I; the bottom end of the second air guide cavity is provided with a second air outlet, and the bottom end of the third air guide cavity is provided with a third air outlet; the air inlet is communicated with the air outlet I, the air outlet II and the air outlet III through the air guide cavity I, the air guide cavity II and the air guide cavity III respectively.
Preferably, the air inlet is communicated with the first air guide cavity through the first air inducing channel, the air inlet is communicated with the second air guide cavity through the second air inducing channel, and the air inlet is communicated with the third air guide cavity through the third air inducing channel.
Preferably, a plurality of radiating fins which are arranged in parallel are fixedly arranged on the first cylinder head and the second cylinder head, and radiating grooves are formed between the radiating fins.
Preferably, a support is fixedly mounted at the upper end of the engine close to the air inlet, a fan is movably mounted on the support and is in transmission connection with the output end of the engine.
More preferably, a filter screen is fixedly installed at the air inlet.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the air-cooled drainage device for the small-sized aviation engine, the air guide cover is arranged outside the engine, so that cold air can be used for radiating the engine more intensively, and the utilization rate and the radiating efficiency of the cold air are improved;
2. the air-cooled drainage device of the small-sized aero-engine is characterized in that a fan is rotatably mounted at the upper end of the output end of the engine, so that the device is different from the traditional small-sized aero-engine in that a transmission source is additionally arranged for air-cooled heat dissipation, the fan and the engine form a whole, the engine rotates to drive the fan to rotate, cold air is sucked from an air inlet and is transmitted to each part of the engine, which needs heat dissipation, and the whole heat dissipation is carried out on the device;
3. this small-size engine forced air cooling drainage device of aviation can make the cylinder head of engine dispel the heat rapidly, improves radiating speed, and the hot-blast air that finally produces will be discharged through the air outlet after accomplishing the heat dissipation, because contain certain impurity in the air, in order to prevent that impurity from adhering on the fan, this device has the filter screen to be used for the impurity among the filtered air, the cleanliness factor of improvement device at the inner fixed mounting of air intake.
Drawings
FIG. 1 is a schematic perspective view of an air-cooled drainage device of an aero-small engine according to an embodiment of the invention;
FIG. 2 is a schematic cross-sectional structure view of an air-cooled drainage device of an aero-small engine according to an embodiment of the invention;
FIG. 3 is a schematic sectional view of a fan of an air-cooled drainage device of an aero-small engine according to an embodiment of the invention;
fig. 4 is a schematic cross-sectional structure view of a filter screen of the air-cooled drainage device of the small-sized aircraft engine in the embodiment of the invention.
In the figure: 1. a wind scooper body; 2. a first air guide cavity; 3. a second air guide cavity; 4. a third air guide cavity; 5. an air inlet; 6. a first cylinder head; 7. a second cylinder head; 8. an engine; 9. a support; 10. a fan; 11. an induced draft channel I; 12. a second air inducing channel; 13. a third air inducing channel; 14. a heat sink; 15. a heat sink; 16. an air outlet I; 17. an air outlet II; 18. an air outlet III; 19. and (4) a filter screen.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: the air-cooled drainage device for the small-sized aero-engine comprises an air guide cover body 1, wherein an air guide cavity I2 is arranged in the middle of the air guide cover body 1, an air guide cavity II 3 is arranged at the right end of the air guide cover body 1, an air guide cavity III 4 is arranged at the left end of the air guide cover body 1, and an air inlet 5 is formed in the upper end of the air guide cover body 1.
An engine 8 is fixedly arranged inside the air guide cavity I2, a cylinder head II 7 is fixedly arranged inside the air guide cavity II 3, a cylinder head I6 is fixedly arranged inside the air guide cavity III 4, the engine 8, the cylinder head I6 and the cylinder head II 7 are of an integrated structure, cold air can be enabled to radiate the engine more intensively, and the utilization rate and the radiating efficiency of the cold air are improved.
The upper end of the engine 8 is fixedly provided with a support 9, the upper end of the support 9 is rotatably provided with a fan 10, the fan 10 is in transmission connection with the output end of the engine 8, the inside of the air guide cavity I2 is fixedly provided with an induced air channel I11, the inside of the air guide cavity II 3 is fixedly provided with an induced air channel II 12, the inside of the air guide cavity III 4 is fixedly provided with an induced air channel III 13, and the fan 10 is rotatably installed at the upper end of the engine 8, so that the device is different from a traditional aviation small-sized engine in that a transmission source is additionally arranged for air cooling heat dissipation, the fan 10 and the engine form a whole body, the engine rotates to drive the fan 10 to rotate, cold air is sucked from the air inlet 5 and is transmitted to all parts of the engine which need heat dissipation through the induced air channel I11, the induced air channel II 12 and the.
The outer end of the first cylinder head 6 is fixedly provided with the radiating fins 14, the radiating grooves 15 are fixedly arranged between the radiating fins 14, the first cylinder head 6 and the second cylinder head 7 are in the same structure, the radiating fins 14 are arranged on the first cylinder head 6 and the second cylinder head 7, and the radiating grooves 15 are formed between the radiating fins 14, so that the cylinder head can quickly radiate heat, and the radiating speed is improved.
The lower end of the first air guide cavity 2 is fixedly provided with an air outlet 16, the lower end of the second air guide cavity 3 is fixedly provided with an air outlet 17, the lower end of the third air guide cavity 4 is fixedly provided with an air outlet 18, and hot air finally generated after heat dissipation is finished is discharged through the air outlet 16, the air outlet 17 and the air outlet 18.
The top fixed mounting of fan 10 has filter screen 19, and filter screen 19 and air intake 5 looks adaptation because contain certain impurity in the air, in order to prevent the impurity adhesion on fan 10, this device has filter screen 19 to be used for the impurity in the filtered air at the inner fixed mounting of air intake 5, makes things convenient for the clearance of fan 10, improves the cleanliness factor of device.
The working principle is as follows: the device is an air-cooled drainage device of an aviation small-sized engine, a wind guide cover body 1 is arranged outside a cylinder head I6, a cylinder head II 7 and an engine 8, so that cold wind can be radiated to the engine more intensively, the utilization rate and the radiating efficiency of the cold wind are improved, a wind guide cavity I2, a wind guide cavity II 3 and a wind guide cavity III 4 respectively convey the cold wind generated by a fan 10 to the cylinder head I6, the cylinder head II 7 and the engine 8, the device is different from the traditional aviation small-sized engine that a transmission source is additionally arranged for air-cooled radiation, the fan 10 is rotatably arranged at the upper end of the output end of the engine 8, so that the fan 10 and the engine form a whole, the engine rotates to drive the fan 10 to rotate, the cold wind is sucked from an air inlet 5 and is transmitted to each part of the engine needing radiation through a wind guide channel I11, a wind guide channel II 12 and a wind guide channel III 13, the device is subjected to integral heat dissipation, the heat dissipation fins 14 are arranged at the outer end of the cylinder head I6, the heat dissipation grooves 15 are formed among the heat dissipation fins 14, the cylinder head can dissipate heat quickly, the heat dissipation speed is improved, and due to the fact that certain impurities are contained in the air, in order to prevent the impurities from being adhered to the fan 10, the filter screen 19 is fixedly arranged at the inner end of the air inlet 5 to filter the impurities in the air, and the cleanliness of the device is improved.
Finally, it should be noted that the above-mentioned contents are only used for illustrating the technical solutions of the present invention, and not for limiting the protection scope of the present invention, and that the simple modifications or equivalent substitutions of the technical solutions of the present invention by those of ordinary skill in the art can be made without departing from the spirit and scope of the technical solutions of the present invention.
Claims (5)
1. The utility model provides an aviation small-size engine forced air cooling drainage device which characterized in that includes:
an engine;
the first cylinder head is arranged on one side of the engine;
the second cylinder head is arranged on the other side of the engine;
the wind guide cover body is arranged on the periphery of the engine and comprises a first wind guide cavity, a second wind guide cavity and a third wind guide cavity,
wherein,
the engine is accommodated in the first air guide cavity, the first cylinder head is accommodated in the second air guide cavity, and the second cylinder head is accommodated in the third air guide cavity; the upper end of the air guide cavity is provided with an air inlet, and the bottom end of the air guide cavity is provided with an air outlet I; the bottom end of the second air guide cavity is provided with a second air outlet, and the bottom end of the third air guide cavity is provided with a third air outlet; the air inlet is communicated with the air outlet I, the air outlet II and the air outlet III through the air guide cavity I, the air guide cavity II and the air guide cavity III respectively.
2. The air-cooled drainage device for small-sized aeroengines according to claim 1, characterized in that: the air inlet is communicated with the first air guide cavity through the first air inducing channel, the air inlet is communicated with the second air guide cavity through the second air inducing channel, and the air inlet is communicated with the third air guide cavity through the third air inducing channel.
3. The air-cooled drainage device for small-sized aeroengines according to claim 1, characterized in that: and a plurality of radiating fins which are arranged in parallel are fixedly arranged on the first cylinder head and the second cylinder head, and radiating grooves are arranged between the radiating fins.
4. The air-cooled drainage device for small-sized aeroengines according to claim 1, characterized in that: the upper end of the engine is fixedly provided with a support close to the air inlet, the support is movably provided with a fan, and the fan is in transmission connection with the output end of the engine.
5. The air-cooled drainage device for small-sized aeroengines according to claim 1, characterized in that: a filter screen is fixedly installed at the air inlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110164293.7A CN112855327A (en) | 2021-02-05 | 2021-02-05 | Air-cooled drainage device of small-sized aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110164293.7A CN112855327A (en) | 2021-02-05 | 2021-02-05 | Air-cooled drainage device of small-sized aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112855327A true CN112855327A (en) | 2021-05-28 |
Family
ID=75989670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110164293.7A Pending CN112855327A (en) | 2021-02-05 | 2021-02-05 | Air-cooled drainage device of small-sized aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112855327A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104343518A (en) * | 2014-11-07 | 2015-02-11 | 重庆鼎工机电有限公司 | General machine engine cooling structure |
| CN204627734U (en) * | 2015-05-07 | 2015-09-09 | 苏州市双马机电有限公司 | Petrol engine forces cooling structure and petrol engine thereof |
| CN209838518U (en) * | 2019-05-17 | 2019-12-24 | 北京华翼星空科技有限公司 | Small-size aeroengine forced air cooling system |
| CN112709626A (en) * | 2021-01-08 | 2021-04-27 | 南京金城机械有限公司 | Forced air cooling engine cooling system |
| CN214118306U (en) * | 2020-12-24 | 2021-09-03 | 重庆睿泽塑料制品有限公司 | Cylinder head air ducting of engine |
-
2021
- 2021-02-05 CN CN202110164293.7A patent/CN112855327A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104343518A (en) * | 2014-11-07 | 2015-02-11 | 重庆鼎工机电有限公司 | General machine engine cooling structure |
| CN204627734U (en) * | 2015-05-07 | 2015-09-09 | 苏州市双马机电有限公司 | Petrol engine forces cooling structure and petrol engine thereof |
| CN209838518U (en) * | 2019-05-17 | 2019-12-24 | 北京华翼星空科技有限公司 | Small-size aeroengine forced air cooling system |
| CN214118306U (en) * | 2020-12-24 | 2021-09-03 | 重庆睿泽塑料制品有限公司 | Cylinder head air ducting of engine |
| CN112709626A (en) * | 2021-01-08 | 2021-04-27 | 南京金城机械有限公司 | Forced air cooling engine cooling system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210374720U (en) | High-efficiency radiator | |
| CN2899258Y (en) | Mixed-cooling generator | |
| CN102223010A (en) | Conducting and radiating energy-saving motor | |
| WO2020134065A1 (en) | Air-cooled diesel engine structure-based water-cooled generator set | |
| CN212231979U (en) | Electric generator | |
| CN112855327A (en) | Air-cooled drainage device of small-sized aero-engine | |
| CN201934189U (en) | Digital generator unit | |
| CN207583498U (en) | A kind of small-sized high temperature resistant mute type diesel generating set | |
| CN104074605B (en) | The air cooling diesel engine generator group of a kind of round-the-clock use | |
| WO2012041210A1 (en) | Paper shredder | |
| CN207728439U (en) | A kind of box generating set of totally-enclosed Two-way Cycle cooling | |
| CN213754240U (en) | Integrated heat dissipation type range extender | |
| CN110284955B (en) | Operation method of rapid heat dissipation device for motorcycle engine | |
| CN102042070B (en) | Digital generator device | |
| CN208057233U (en) | A kind of air-cooled power supply of small-power low noise soundproofed cabin formula | |
| CN206016963U (en) | A kind of diesel-driven generator | |
| CN217002033U (en) | Generating set heat radiation structure | |
| CN201038927Y (en) | A digital permanent magnetic generator unit | |
| CN214380425U (en) | Electric motorcycle motor that radiating efficiency is high | |
| CN212625061U (en) | Transformer heat dissipation dust keeper | |
| CN220358970U (en) | Generator set with high heat dissipation performance | |
| CN213637391U (en) | Well cementation pump motor | |
| CN212435532U (en) | Three-phase asynchronous motor special for oil pump | |
| CN216751388U (en) | Heat dissipation dust keeper for generator | |
| CN212231283U (en) | Motor with good heat dissipation effect |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210528 |
|
| RJ01 | Rejection of invention patent application after publication |