CN213473538U - Aircraft engine oil tank convenient to heat dissipation - Google Patents
Aircraft engine oil tank convenient to heat dissipation Download PDFInfo
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- CN213473538U CN213473538U CN202021804953.0U CN202021804953U CN213473538U CN 213473538 U CN213473538 U CN 213473538U CN 202021804953 U CN202021804953 U CN 202021804953U CN 213473538 U CN213473538 U CN 213473538U
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- tank main
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Abstract
The utility model discloses an aircraft engine oil tank convenient for heat dissipation, which comprises an oil tank main body, wherein a cooling layer is arranged on the outer side wall of the oil tank main body, cooling water pipes are arranged in the cooling layer, a graphite heat-conducting plate is arranged on the outer side wall of the cooling layer far away from the oil tank main body, and both side walls of the oil tank main body are arranged in a corrugated shape; the outer shell that has been put of oil tank main part cover, every group all seted up the vent on the lateral wall of shell, every group all install the fan in the vent, and be located the fan keeps away from the vent internal joint of oil tank main part one side has the filter, the bottom of shell still is provided with the water tank, the end of intaking and the play water end of cooling water pipe all with the water tank switch-on, the both ends of a water tank lateral wall are provided with water inlet and outlet respectively. This aircraft engine oil tank convenient to heat dissipation, it is rational in infrastructure, have good radiating effect, be worth promoting.
Description
Technical Field
The utility model belongs to the technical field of the engine oil tank, concretely relates to aircraft engine oil tank convenient to heat dissipation.
Background
The fuel tank is a special container for storing hydraulic oil or hydraulic fluid in a hydraulic system, and the fuel tank can be divided into an open fuel tank and a closed fuel tank; the open type oil tank is characterized in that the liquid level in the tank is communicated with the atmosphere, and an air filter is arranged on the oil tank cover; the closed oil tank is generally used for a pressure oil tank and is filled with inert gas with certain pressure; in order to keep the oil clean, the oil tank is provided with a cover plate with sealed periphery, and an air filter is arranged on the cover plate; the bottom of the tank should be kept at a distance from the ground.
The oil tank of the airplane is a power source of the airplane, in order to prevent leakage in the oil tank during traveling, the oil tank is sealed tightly, so that the inside of the oil tank is not ventilated, the oil temperature can be increased when the airplane starts driving work of an engine, driving work of each internal electric appliance and shaking of oil in the oil tank, meanwhile, a certain influence can be caused on the oil tank of a diesel engine by a surrounding high-temperature heat source, the temperature of the oil tank of the engine is high, loss of parts of the oil tank of the diesel engine is caused easily, and meanwhile, certain potential safety hazards exist, therefore, the oil tank of the airplane engine convenient for heat dissipation is needed to be designed.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft engine oil tank convenient to heat dissipation to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: an aircraft engine oil tank convenient for heat dissipation comprises an oil tank main body, wherein a cooling layer is arranged on the outer side wall of the oil tank main body, cooling water pipes are arranged in the cooling layer, a graphite heat-conducting plate is arranged on the outer side wall, far away from the oil tank main body, of the cooling layer, and both side walls of the oil tank main body are arranged in a corrugated shape;
the outer shell that has been put of oil tank main part cover, every group all seted up the vent on the lateral wall of shell, every group all install the fan in the vent, and be located the fan keeps away from the vent internal joint of oil tank main part one side has the filter, the bottom of shell still is provided with the water tank, the end of intaking and the play water end of cooling water pipe all with the water tank switch-on, the both ends of a water tank lateral wall are provided with water inlet and outlet respectively.
Preferably, the cooling water pipe sets up to the platykurtic structure and is S form and arranges in the cooling in situ, is located the water pump is installed to the end of intaking of the cooling water pipe in the water tank.
Preferably, be provided with the oiling mouth on the top face of oil tank main part, on the top face of shell with the position that the oiling mouth corresponds is provided with the apron, the bottom of an oil tank main part lateral wall is provided with the oil drain port, the oil drain port runs through the shell lateral wall and is located the shell outside.
Preferably, every group equal vertical stopper that is provided with on the inside wall of shell, stopper and the mutual butt of oil tank bulk phase, just set up the cooperation in the oil tank bulk phase the notch of stopper joint.
Preferably, one side of the top end face of the oil tank main body is provided with a second groove, a binding post is arranged in the second groove, and the shell is provided with a first groove matched with the second groove for use.
The utility model discloses a technological effect and advantage: this aircraft engine oil tank convenient to heat dissipation, through the cooling layer, the setting of cooling water pipe and water tank, and set up the cooling water pipe into the platykurtic structure and be the S form and arrange, can realize the purpose to the quick heat dissipation cooling of oil tank main part, and the effect is better, through the setting of graphite heat-conducting plate, and set up the both sides wall of oil tank main part into the fold form, and then accelerated giving off of oil tank main part heat, simultaneously under the effect of fan alright arrange the heat that the oil tank main part gived off outside the shell rapidly, thereby make the radiating effect further improve. This aircraft engine oil tank convenient to heat dissipation, it is rational in infrastructure, have good radiating effect, be worth promoting.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a cross-sectional view of the present invention;
FIG. 3 is a schematic structural view of the fuel tank of the present invention;
fig. 4 is a cross-sectional view of the ventilation head of the present invention;
FIG. 5 is a cross-sectional view of a side wall of the fuel tank body according to the present invention;
fig. 6 is the structure schematic diagram of the cooling water pipe of the present invention.
In the figure: the oil tank comprises a shell 1, a water tank 2, a vent 3, a water inlet 4, a water outlet 5, an oil outlet 6, a first groove 7, a cover plate 8, an oil tank main body 9, a limiting block 10, an oil injection port 11, a second groove 12, a filter plate 13, a fan 14, a cooling layer 15, a graphite heat-conducting plate 16 and a cooling water pipe 17.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The utility model provides an aircraft engine oil tank convenient for heat dissipation as shown in figures 1-6, which comprises an oil tank main body 9, wherein a cooling layer 15 is arranged on the outer side wall of the oil tank main body 9, cooling water pipes 17 are distributed in the cooling layer 15, a graphite heat-conducting plate 16 is arranged on the outer side wall of the cooling layer 15 far away from the oil tank main body 9, and both side walls of the oil tank main body 9 are arranged in a corrugated shape;
the improved water tank is characterized in that a shell 1 is sleeved outside the oil tank main body 9, each group of shell 1 is provided with a vent 3 on the side wall, each group of vent 3 is provided with a fan 14, the fan 14 is positioned in the vent 3 far away from one side of the oil tank main body 9, a filter plate 13 is clamped in the vent 3, the bottom end of the shell 1 is also provided with a water tank 2, the water inlet end and the water outlet end of the cooling water pipe 17 are communicated with the water tank 2, and the two ends of one side wall of the water tank 2 are respectively provided with a water inlet 4.
Specifically, cooling water pipe 17 sets up to the platykurtic structure and is the S form and arranges in cooling layer 15, is located the water pump is installed to the end of intaking of cooling water pipe 17 in water tank 2 to carry the water in water tank 2 to cooling water pipe 17 in cooling layer 15.
Specifically, be provided with oiling mouth 11 on the top face of oil tank main part 9, on the top face of shell 1 with the position that oiling mouth 11 corresponds is provided with apron 8, plays dirt-proof effect, the bottom of 9 lateral walls of oil tank main part is provided with oil drain port 6, oil drain port 6 runs through 1 lateral wall of shell and is located the shell 1 outside.
It is specific, every group equal vertical stopper 10 that is provided with on the inside wall of shell 1, stopper 10 and the mutual butt of oil tank main part 9, just set up the cooperation on the oil tank main part 9 the notch of stopper 10 joint, stopper 10 play the effect that makes to leave the gap between shell 1 and the oil tank main part 9 to thermal giving off.
Specifically, one side of the top end face of the oil tank main body 9 is provided with a second groove 12, a binding post is arranged in the second groove 12, and the shell 1 is provided with a first groove 7 matched with the second groove 12 for use and used for connecting a sensor in the oil tank main body 9.
The working principle is as follows: when the aircraft engine oil tank convenient for heat dissipation is used, the water pump positioned at the water inlet end of the cooling water pipe 17 connected in the water tank 2 is started, water in the water tank 2 is conveyed into the cooling water pipe 17, and the cooling water pipe 17 is arranged in a flat structure and is distributed in the cooling layer 15 in an S shape, so that the purpose of heat dissipation and cooling of the oil tank main body 9 can be realized, the effect is better, meanwhile, the water in the water tank 2 can flow back into the water tank 2 again after the oil tank main body 9 is cooled through the cooling water pipe 17, and a water circulation system is formed, so that the purpose of saving resources is achieved; further, because the graphite heat-conducting plate 16 is arranged on the outer side wall of the oil tank main body 9, and the two side walls of the oil tank main body 9 are arranged in a corrugated shape, the dissipation of the heat of the oil tank main body 9 is accelerated, and meanwhile, the heat dissipated from the oil tank main body 9 is rapidly discharged out of the shell 1 under the action of the fan 14, so that the heat dissipation effect is further improved. This aircraft engine oil tank convenient to heat dissipation, it is rational in infrastructure, have good radiating effect, be worth promoting.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.
Claims (5)
1. An aircraft engine oil tank convenient to heat dissipation, includes oil tank main part (9), its characterized in that: a cooling layer (15) is arranged on the outer side wall of the oil tank main body (9), cooling water pipes (17) are arranged in the cooling layer (15), a graphite heat-conducting plate (16) is arranged on the outer side wall, far away from the oil tank main body (9), of the cooling layer (15), and two side walls of the oil tank main body (9) are arranged in a corrugated shape;
shell (1) has been put outward to oil tank main part (9), every group vent (3) have all been seted up on the lateral wall of shell (1), every group all install fan (14) in vent (3), and be located fan (14) keep away from in vent (3) of oil tank main part (9) one side filter (13) of joint, the bottom of shell (1) still is provided with water tank (2), the end of intaking and the play water end of cooling water pipe (17) all with water tank (2) switch-on, the both ends of a lateral wall of water tank (2) are provided with water inlet (4) and outlet (5) respectively.
2. An aircraft engine oil sump for facilitating heat dissipation as defined in claim 1, wherein: cooling water pipe (17) set up to the platykurtic structure and are S-shaped and arrange in cooling layer (15), are located the water pump is installed to the end of intaking of cooling water pipe (17) in water tank (2).
3. An aircraft engine oil sump for facilitating heat dissipation as defined in claim 1, wherein: be provided with oiling mouth (11) on the top face of oil tank main part (9), on the top face of shell (1) with the position that oiling mouth (11) correspond is provided with apron (8), the bottom of oil tank main part (9) a lateral wall is provided with oil drain hole (6), oil drain hole (6) run through shell (1) lateral wall and are located the shell (1) outside.
4. An aircraft engine oil sump for facilitating heat dissipation as defined in claim 1, wherein: every group equal vertical stopper (10) that is provided with on the inside wall of shell (1), stopper (10) and the mutual butt of oil tank main part (9), just set up the cooperation on oil tank main part (9) the notch of stopper (10) joint.
5. An aircraft engine oil sump for facilitating heat dissipation as defined in claim 1, wherein: one side of the top end face of the oil tank main body (9) is provided with a second groove (12), a binding post is arranged in the second groove (12), and a first groove (7) matched with the second groove (12) is formed in the shell (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021804953.0U CN213473538U (en) | 2020-08-25 | 2020-08-25 | Aircraft engine oil tank convenient to heat dissipation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021804953.0U CN213473538U (en) | 2020-08-25 | 2020-08-25 | Aircraft engine oil tank convenient to heat dissipation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213473538U true CN213473538U (en) | 2021-06-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021804953.0U Active CN213473538U (en) | 2020-08-25 | 2020-08-25 | Aircraft engine oil tank convenient to heat dissipation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213473538U (en) |
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2020
- 2020-08-25 CN CN202021804953.0U patent/CN213473538U/en active Active
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