CN206190387U - Piston aeroengine forced cooling cover - Google Patents
Piston aeroengine forced cooling cover Download PDFInfo
- Publication number
- CN206190387U CN206190387U CN201620742545.4U CN201620742545U CN206190387U CN 206190387 U CN206190387 U CN 206190387U CN 201620742545 U CN201620742545 U CN 201620742545U CN 206190387 U CN206190387 U CN 206190387U
- Authority
- CN
- China
- Prior art keywords
- cooling dome
- cooling jacket
- jar
- engine
- cooling
- 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.)
- Expired - Fee Related
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- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The utility model provides a piston aeroengine forced cooling cover, belongs to aviation technical field, its characterized in that: cooling jacket comprises left jar cooling jacket and right jar cooling jacket, wherein left jar cooling jacket and right jar cooling jacket divide equally do not be for open -ended metal casing around, and the open front is the entry, and the after -opening is the export, be equipped with the mounting hole on one of in the non -conterminous lateral wall of a left side jar cooling jacket and right jar cooling jacket, and the cross -sectional area of left side jar cooling jacket entry is greater than the cross -sectional area of right jar cooling jacket entry. Through to the engine about cylinder radiator member increase the not forced cooling cover of isostructure outward respectively, makes a large amount of air pass through between by the engine fin, the structural shapes who covers through forced cooling comes change the wind direction and wind speed, adjusts the jar temperature of engine to the temperature of effectively makeeing the engine control the jar realizes balancedly. Piston aeroengine forced cooling cover simple structure, easily the preparation is suitable for popularization and application.
Description
Technical field
The utility model belongs to technical field of aerospace, more particularly to a kind of Wind-cooling type piston aviation engine forces cooling
Cover.
Background technology
Engine-cooling system is the important component of engine, influence Wind-cooling type piston-mode motor cooling effect
Factor mainly have it is following some：1. the material thermal conductivity size of fin；2. fin size；3. engine is flowed through to dissipate
The wind speed and uninterrupted of heat sink surface；4. engine local environment air themperature size.
Existing air-cooled h type engine h, because engine radiating piece periphery does not have obstacle, substantial amounts of air is flowed through and started
Outside machine, certain cooling effect is played to cylinder, but because two cylinders of flat twin are away from propeller
Distance is different, therefore the cooling degree of two cylinders can be caused inconsistent, causes left and right cylinder temperature inconsistent, and the temperature difference compared with
Greatly, it is unfavorable for engine long time steady operation.
Utility model content
The utility model aims to solve the problem that above mentioned problem, there is provided one kind is by adjusting wind speed and wind always balanced engine or so cylinder
The piston aviation engine of temperature forces cooling dome.
Piston aviation engine described in the utility model forces cooling dome, and cooling dome is cold by left cylinder cooling dome and right cylinder
But cover is constituted；Wherein left cylinder cooling dome and right cylinder cooling dome are respectively the metal shell of a front and rear opening, and open front is entrance,
After-opening is outlet；One of left cylinder cooling dome and the non-conterminous side wall of right cylinder cooling dome are provided with mounting hole；And the left side
Cross-sectional area of the cross-sectional area of cylinder cooling dome entrance more than right cylinder cooling dome entrance.By the side for increasing cooling dome to engine
Formula so that substantial amounts of air-flow is concentrated by cooling dome and passed through from cylinder, because cooling dome inner section passage reduces,
Air-flow constantly accelerates, so as to increase the wind flow between cylinder fin, and then strengthens cooling effect.Because left cylinder is cold
But the inlet ratio right cylinder cooling dome area for covering is big, therefore the air-flow that left cylinder enters is also bigger than right cylinder, and unit interval intrinsic motivation is left
The cooling effectiveness of cylinder is higher than right cylinder, you can promote the temperature of left and right cylinder to be in balance.
Piston aviation engine described in the utility model forces cooling dome, the longitudinal section of the left cylinder cooling dome entrance
In inverted eight like；The longitudinal section of the right cylinder cooling dome entrance is square.Eight words are set to down by by left cylinder cooling dome entrance
Shape, with right cylinder cooling dome without compared with improved entrance, the aperture area of eight word entrances is big, while the more conducively receipts of air-flow
Collection enters so that the cooling effectiveness of engine left cylinder is higher than engine right cylinder, is quickly promoted at the temperature of engine left and right cylinder
In balance.
Piston aviation engine described in the utility model forces entrance and the outlet of cooling dome, the cooling dome not to exist
In same level.
Piston aviation engine described in the utility model forces cooling dome, the entrance of the cooling dome to be arranged at housing
Top, outlet is arranged at the bottom of housing.Bottom air inlet when being worked due to two stroke engine, intake air temperature is relatively low, so
Cylinder temperature of lower is low, top exhaust, and delivery temperature is very high, so cylinder upper temp is higher than bottom, cooling dome entrance
Opening is on the upper side, with the cooling of acceleration motor cylinder top half engine one side temperature cylinder can be made to tend to balance.
Piston aviation engine described in the utility model forces cooling dome, is radiated by the left and right cylinder to engine
Increase the pressure cooling dome of different structure outside piece respectively, substantial amounts of air is passed through by between engine radiating piece, by forcing
The planform of cooling dome changes wind direction and wind speed, and the cylinder temperature to engine is adjusted, so as to effectively promote engine left
The temperature of right cylinder realizes balance.Piston aviation engine described in the utility model forces cooling dome simple structure, it is easy to make
It is standby, it is suitable to popularization and application.
Brief description of the drawings
Fig. 1 is left cylinder cooling dome structural front view；
Fig. 2 is left cylinder cooling cover structure left view；
Fig. 3 is left cylinder cooling dome structure top view；
Fig. 4 is right cylinder cooling dome structural front view；
Fig. 5 is right cylinder cooling cover structure left view；
Fig. 6 is right cylinder cooling dome structure top view；
Fig. 7 is engine or so cylinder temperature contrast and experiment figure in the case of bare machine；
Fig. 8 is to increase to force cooling dome rear engine or so cylinder temperature contrast and experiment figure；
Wherein 1- entrances, 2- outlets.
Specific embodiment
Below in conjunction with the accompanying drawings and embodiment to piston aviation engine described in the utility model force cooling dome say
It is bright：
Pressure cooling dome described in the utility model includes left cylinder cooling dome and right cylinder cooling dome, and cooling dome is opening before and after
Metal shell, the side wall of the cooling dome is provided with mounting hole；Cooling dome is realized by the mounting hole on the wall of cooling dome side
With the connection of engine.Left side opening is entrance 1 to left cylinder cooling dome as shown in Figure 1, and right openings are outlet 2；Right cooling dome is such as
Right openings shown in Fig. 2 are entrance 1, and left side opening is outlet 2；The longitudinal section of the left cylinder cooling dome entrance 1 is in inverted eight like；
The cross-sectional area of the left cylinder cooling dome entrance 1 is more than the cross-sectional area of right cylinder cooling dome entrance 1, for adjusting engine or so
The difference of cylinder temperature, makes it tend to be steady.The entrance 1 of the cooling dome may be contained within the top of housing, and outlet 2 may be contained within shell
The bottom of body, the difference for adjusting unilateral engine cylinder temperature, makes it tend to be steady.
After increasing pressure cooling dome, the air entered by pressure cooling dome entrance 1 is limited in pressure cooling dome
Portion, forces it through the gap between fin, which increases air mass flow, strengthens the cooling effect of cross-ventilation heat exchange
Really.Again by the special setting to forcing cooling hood shape, adjustment air is entering the flow direction after forcing cooling dome, is making its more
Flow through engine cylinder temperature part higher, can so reach makes the purpose of whole engine temperature balance.
The present embodiment selects the stroke twin-tub opposed piston engines of 630H two, and first bare machine is tested, and acquirement is started
Machine cylinder temperature data, equilibrium temperature during record 5 minutes in 5500 turns of engine speed, the left and right cylinder temperature difference is in the case of bare machine
10.6℃；After its engine or so cylinder installs pressure cooling dome described in the utility model, the cylinder of experimental test acquirement is carried out
The temperature data left and right cylinder temperature difference is 0.9 DEG C.As shown in Figure 7, Figure 8, it can be seen that in Fig. 7 during 5500 turns of rotating speed, engine is left
The right cylinder temperature difference is larger, and in Fig. 8 during 5500 turns of rotating speed, engine left and right cylinder temperature is basically identical.
Claims (4)
1. a kind of piston aviation engine forces cooling dome, it is characterised in that：Cooling dome is cooled down by left cylinder cooling dome and right cylinder
Cover composition；Wherein left cylinder cooling dome and right cylinder cooling dome are respectively the metal shell of a front and rear opening, and open front is entrance
（1）, after-opening is outlet（2）；One of left cylinder cooling dome and the non-conterminous side wall of right cylinder cooling dome are provided with mounting hole；And
The left cylinder cooling dome entrance（1）Cross-sectional area be more than right cylinder cooling dome entrance（1）Cross-sectional area.
2. piston aviation engine according to claim 1 forces cooling dome, it is characterised in that：The left cylinder cooling dome
Entrance（1）Longitudinal section be in inverted eight like；The right cylinder cooling dome entrance（1）Longitudinal section be square.
3. piston aviation engine according to claim 1 and 2 forces cooling dome, it is characterised in that：The cooling dome
Entrance（1）With outlet（2）Not in same level.
4. piston aviation engine according to claim 3 forces cooling dome, it is characterised in that：The cooling dome enters
Mouthful（1）The top of housing is arranged at, is exported（2）It is arranged at the bottom of housing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620742545.4U CN206190387U (en) | 2016-07-14 | 2016-07-14 | Piston aeroengine forced cooling cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620742545.4U CN206190387U (en) | 2016-07-14 | 2016-07-14 | Piston aeroengine forced cooling cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206190387U true CN206190387U (en) | 2017-05-24 |
Family
ID=58736322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620742545.4U Expired - Fee Related CN206190387U (en) | 2016-07-14 | 2016-07-14 | Piston aeroengine forced cooling cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206190387U (en) |
-
2016
- 2016-07-14 CN CN201620742545.4U patent/CN206190387U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170524 Termination date: 20190714 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |