CN107893696B - Cooling system for 3W-342 aircraft engine - Google Patents
Cooling system for 3W-342 aircraft engine Download PDFInfo
- Publication number
- CN107893696B CN107893696B CN201711175100.8A CN201711175100A CN107893696B CN 107893696 B CN107893696 B CN 107893696B CN 201711175100 A CN201711175100 A CN 201711175100A CN 107893696 B CN107893696 B CN 107893696B
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- Prior art keywords
- baffle
- notch
- fan
- air
- cooling system
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- 238000001816 cooling Methods 0.000 title claims abstract description 31
- 230000007704 transition Effects 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 241001124569 Lycaenidae Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- 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
- F01P5/06—Guiding or ducting air to, or from, ducted fans
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- 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
- 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
- F01P2005/025—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers using two or more air pumps
-
- 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
- F01P2005/046—Pump-driving arrangements with electrical pump drive
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention discloses a cooling system for a 3W-342 aircraft engine, which comprises a fan and a wind collecting cover, wherein the wind collecting cover is arranged above an engine cylinder and comprises a baffle and a surrounding plate, the baffle is shaped like a Chinese character 'ji', sinking parts at two sides are eccentrically arranged, four connecting through holes are reserved on a protruding part of the baffle, air inlets are formed in the sinking parts at two sides of the baffle, and the fan is arranged above the air inlets; the upper edge of the enclosing plate extends along the edge of the baffle plate in a surrounding manner to form an air outlet, and three holes are reserved on the outer side of the enclosing plate; the part of the coaming along the protruding part of the baffle is shorter than the rest part and is provided with a notch, the notch comprises an arched notch and an arc-shaped notch, and the arched notch is positioned in front of the arc-shaped notch; the fan is powered by a separate power source and its operation is controlled by a temperature controller. The present invention directs air directly to the cylinder to create a continuous flow of cooling air around the cylinder to ensure maximum cooling of the engine.
Description
Technical Field
The invention relates to the technical field of engine cooling, in particular to a cooling system for a 3W-342 aircraft engine.
Background
The 342 aviation piston engine of German 3W company is a natural air-cooled engine, cools an engine cylinder by natural wind in the running process, and can be widely applied to equipment equipped with small gasoline engines, such as small agricultural machines, unmanned planes, motorcycles, outboard engines, lawn vehicles, beach vehicles, chain saws, brush cutters, fence shears, harvesters, water pumps and the like. However, with the difference of working environments, for example, when the unmanned aerial vehicle performs a task, the unmanned aerial vehicle even needs to hover to complete shooting and scanning, natural wind does not exist in the cooling air duct at this time, and the heat is taken away by completely sucking air from a surrounding cold source through the cooling fan, so that the temperature of the engine is too high.
In order to solve the problem of high temperature of the 3W-342 aircraft engine, many technicians design various solutions, and currently, the following are generally adopted: firstly, the cooling air volume is increased by enlarging the rotor blade of the engine, but the large increase of the rotor blade of the engine consumes a large amount of power of the engine, seriously influences the performance of the engine and causes the increase of the production cost; secondly, airflow is guided into the air guide sleeve with a half-cover type structure, but cooling air is discharged through a large-area air outlet directly only through short-time flowing in the air guide sleeve, and the cooling airflow is not fully used for cooling the engine body, so that heat of the cylinder head and the engine body of the internal combustion engine is not fully taken away, and the purpose of well cooling the internal combustion engine is not achieved.
Disclosure of Invention
The invention aims to provide a cooling system for a 3W-342 aircraft engine, which can separately provide forced air cooling.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a cooling system for a 3W-342 aircraft engine comprises a fan and a wind collecting cover, wherein the wind collecting cover is arranged above an engine cylinder and comprises a baffle and a surrounding plate, the baffle is shaped like a Chinese character 'ji', sinking parts at two sides of the baffle are eccentrically arranged, four connecting through holes are reserved on a protruding part of the baffle, air inlets are formed in the sinking parts at two sides of the baffle, the fan is arranged above the air inlets, and the maximum diameter of blades of the fan is smaller than the inner diameter of the air inlets; the upper edge of the enclosing plate extends along the edge of the baffle plate to form an air outlet in a surrounding manner, three holes are reserved on the outer side of the enclosing plate, and one hole is positioned above the other two holes; the part of the coaming along the protruding part of the baffle is shorter than the rest part and is provided with a notch, the notch comprises an arched notch and an arc-shaped notch, and the arched notch is positioned in front of the arc-shaped notch; the fan is powered by a separate power source and its operation is controlled by a temperature controller.
Furthermore, a space is reserved between the edge of the air inlet and the edge of the baffle plate for installing the fan.
Furthermore, the fan and the air collecting cover and the engine are all installed in a bolt connection mode.
Furthermore, the connection position of the baffle and the coaming is in arc transition connection.
Furthermore, the hole on the upper portion is used for installing a pressure reducing valve on the air cylinder, and the two holes on the lower portion are used for installing spark plugs on the air cylinder.
Furthermore, four supporting columns are correspondingly distributed below the baffle protruding part connecting through hole, and bolts penetrate through the supporting columns.
Further, the depth of the arch-shaped notch is larger than that of the arch-shaped notch.
The invention has the beneficial effects that:
the invention provides a full-cover type flow guide structure, wherein all parts to be cooled are arranged in a wind collecting cover, so that the cooling effect of a machine body is more uniform, and cooling air flow can be fully utilized;
the fan is driven by using the independent power supply, and a transmission mechanism comprising a chain, a chain wheel, a bearing, an annular oil seal and the like is omitted, so that the fan occupies a smaller volume and has a more compact structure; the temperature sensor can control the rotating speed and the air quantity of the fan according to the temperature of the engine, the fan can continue to operate after the engine stops working, hot air on the surface of the cylinder head of the cylinder is continuously sucked, the engine after the engine stops is cooled, and accidents such as locking of a cylinder piston and the like caused by temperature rise and return of the engine after the engine stops are prevented.
Drawings
FIG. 1 is a schematic view of the installation of a wind-collecting cover and a fan in a cooling system for a 3W-342 aircraft engine according to the present invention.
FIG. 2 is a schematic view of a cowl for use in a cooling system of a 3W-342 aircraft engine according to the present invention.
FIG. 3 is a rear view of a cowl for use in a cooling system for a 3W-342 aircraft engine of the present invention.
FIG. 4 is a front view of a cowl for use in a cooling system for a 3W-342 aircraft engine of the present invention.
The reference numbers in the figures are: 1 is the fan, 2 is the baffle, 3 is the bounding wall, 4 is the air intake, 5 is the pillar, 6 is the hole, 7 is the arch breach, 8 is the arc breach.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings.
Example one
As shown in fig. 1 to 4, a cooling system for a 3W-342 aircraft engine comprises a fan 1 and a wind-collecting cover, wherein the wind-collecting cover is installed above an engine cylinder and comprises a baffle 2 and a surrounding plate 3, the baffle 2 is shaped like a Chinese character 'ji', two sunken parts at two sides are eccentrically arranged, four connecting through holes are reserved on a protruding part of the baffle 2, air inlets 4 are respectively formed on the sunken parts at two sides of the baffle 2, the fan 1 is installed above the air inlets 4, and the maximum diameter of blades of the fan 1 is smaller than the inner diameter of the air inlets 4; the upper edge of the enclosing plate 3 extends along the edge of the baffle 2 to form an air outlet in a surrounding manner, three holes 6 are reserved on the outer side of the enclosing plate 3, and one hole 6 is positioned above the other two holes 6; the part of the coaming 3 along the protruding part of the baffle 2 is shorter than the rest part and is provided with a notch, the notch comprises an arched notch 7 and an arc-shaped notch 8, and the arched notch 7 is positioned in front of the arc-shaped notch 8; the fan 1 is powered by a separate power supply and is controlled to work by a temperature controller; a space is reserved between the edge of the air inlet 4 and the edge of the baffle 2 for installing the fan 1, and the installation modes of the fan 1 and the air collecting cover and the engine are all in a bolt connection mode; the connecting part of the baffle 2 and the coaming 3 is in arc transition connection; the upper hole 6 is used for installing a pressure reducing valve on the cylinder, and the lower two holes 6 are used for installing spark plugs on the cylinder; four supporting columns 5 are correspondingly arranged below the protruding part connecting through hole of the baffle 2, and bolts penetrate through the supporting columns 5; the depth of the arcuate notch 7 is greater than the depth of the arcuate notch 8.
The air collecting cover designed in the system is tightly assembled around the engine, so that cooling air can pass through the cylinder from top to bottom when flowing along the direction of the exhaust port, and meanwhile, the radiating fin at the top of the cylinder, the spark plug and the plug of the spark plug can also be cooled; the temperature sensor can control the rotating speed and the air quantity of the fan 1 according to the temperature of the engine, the fan 1 can continue to operate after the engine stops working, hot air on the surface of the cylinder head of the cylinder is continuously sucked, the temperature of the engine after the engine stops is reduced, and accidents such as locking of a cylinder piston and the like caused by temperature rise and return of the engine after the engine stops are prevented.
The above-described embodiments are merely preferred embodiments of the present invention, and not intended to limit the scope of the invention, so that equivalent changes or modifications in the structure, features and principles described in the present invention should be included in the claims of the present invention.
Claims (6)
1. A cooling system for a 3W-342 aircraft engine comprises a fan (1) and a wind collecting cover, and is characterized in that the wind collecting cover is installed above an engine cylinder and comprises a baffle (2) and a coaming (3), the baffle (2) is in a shape like a Chinese character 'ji', sinking parts at two sides are eccentrically arranged, four connecting through holes are reserved on a protruding part of the baffle (2), air inlets (4) are formed in the sinking parts at two sides of the baffle (2), the fan (1) is installed above the air inlets (4), and the maximum diameter of fan blades of the fan (1) is smaller than the inner diameter of the air inlets (4); the upper edge of the enclosing plate (3) extends along the edge of the baffle (2) to form an air outlet in a surrounding manner, three holes (6) are reserved on the outer side of the enclosing plate (3), one hole (6) is positioned above the other two holes (6), the upper hole (6) is used for installing a pressure reducing valve on the air cylinder, and the lower two holes (6) are used for installing spark plugs on the air cylinder; the part of the coaming (3) along the protruding part of the baffle (2) is shorter than the rest part and is provided with a notch, the notch comprises an arched notch (7) and an arc-shaped notch (8), and the arched notch (7) is positioned in front of the arc-shaped notch (8); the fan (1) is powered by a separate power supply and its operation is controlled by a temperature controller.
2. A cooling system for a 3W-342 aircraft engine according to claim 1, characterized in that a distance is reserved between the edge of the air inlet (4) and the edge of the baffle (2) for mounting the fan (1).
3. A cooling system for a 3W-342 aircraft engine according to claim 1, wherein the fan (1) is bolted to the air-collecting hood and to the engine.
4. A cooling system for a 3W-342 aircraft engine according to claim 1, wherein the baffle (2) and the shroud (3) are joined by a circular arc transition.
5. A cooling system for a 3W-342 aircraft engine according to claim 1, characterized in that four pillars (5) are correspondingly arranged below the protruding part connecting through hole of the baffle (2), and bolts are arranged in the pillars (5).
6. A cooling system for a 3W-342 aircraft engine according to claim 1, wherein the depth of the arcuate notch (7) is greater than the depth of the arcuate notch (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711175100.8A CN107893696B (en) | 2017-11-22 | 2017-11-22 | Cooling system for 3W-342 aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711175100.8A CN107893696B (en) | 2017-11-22 | 2017-11-22 | Cooling system for 3W-342 aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107893696A CN107893696A (en) | 2018-04-10 |
| CN107893696B true CN107893696B (en) | 2020-04-28 |
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ID=61805904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711175100.8A Active CN107893696B (en) | 2017-11-22 | 2017-11-22 | Cooling system for 3W-342 aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107893696B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112879144B (en) * | 2021-03-24 | 2024-10-11 | 北京北方车辆集团有限公司 | Vertical ladder type fan cabin arrangement structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202417680U (en) * | 2011-11-29 | 2012-09-05 | 成都精石模型开发有限公司 | Radiator for unmanned helicopter |
| CN206054070U (en) * | 2016-08-31 | 2017-03-29 | 飞瑞航空科技（江苏）有限公司 | A kind of unmanned plane transmission and engine-cooling system |
| CN106907267A (en) * | 2017-03-10 | 2017-06-30 | 西安天问智能科技有限公司 | Engine cooling system and rotor craft |
-
2017
- 2017-11-22 CN CN201711175100.8A patent/CN107893696B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202417680U (en) * | 2011-11-29 | 2012-09-05 | 成都精石模型开发有限公司 | Radiator for unmanned helicopter |
| CN206054070U (en) * | 2016-08-31 | 2017-03-29 | 飞瑞航空科技（江苏）有限公司 | A kind of unmanned plane transmission and engine-cooling system |
| CN106907267A (en) * | 2017-03-10 | 2017-06-30 | 西安天问智能科技有限公司 | Engine cooling system and rotor craft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107893696A (en) | 2018-04-10 |
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