CN213510761U - Aeroengine shell with good heat dissipation performance - Google Patents
Aeroengine shell with good heat dissipation performance Download PDFInfo
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- CN213510761U CN213510761U CN202022554503.7U CN202022554503U CN213510761U CN 213510761 U CN213510761 U CN 213510761U CN 202022554503 U CN202022554503 U CN 202022554503U CN 213510761 U CN213510761 U CN 213510761U
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Abstract
The utility model discloses an aircraft engine shell with good heat dissipation, which comprises a supporting seat, a communicating groove, an outer shell, a connecting seat, a radiating fin, a connecting sheet, a liquid collecting device, a liquid inlet hole, an impeller, a liquid outlet hole, a liquid separating device and the like; the rotation of the connecting shaft can drive the blades to rotate, so that the external air can be sucked into the cooling cavity and then uniformly blown to the radiating fins through the air outlets, and the radiating effect is improved; the rotation of the middle transmission shaft drives the impeller to rotate, so that the heat conduction oil can circularly flow around the engine shell anticlockwise, the heat dissipation uniformity of the engine shell is ensured, and the service life of the engine is prevented from being reduced due to local overheating; the utility model discloses well album of liquid device that sets up can cooperate with dividing the liquid device with the even suction of the conduction oil on engine housing right side simultaneously to will inhale conduction oil homodisperse to the engine housing left side, just also ensured the radiating homogeneity of conduction oil circulation flow.
Description
Technical Field
The utility model relates to an engine accessories technical field, specific good heat dissipation's aeroengine casing that says so.
Background
The shell of the engine mainly plays a role in protecting the engine and preventing mechanical damage. Because the engine works for a long time and generates a large amount of heat, the engine shell is very important to the working environment of the engine and the working performance and the service life of each part of the engine, and the heat on the surface of the general engine is usually radiated naturally, but the heat radiation requirement of the aero-engine is difficult to meet.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned weak point that exists among the prior art, the utility model aims at providing a good heat dissipation's aeroengine casing, the heat of having solved general engine surface all is usually through natural heat dissipation, but this problem of hardly satisfying the radiating needs of aeroengine.
The utility model discloses a realize that the technical scheme that above-mentioned purpose adopted is: an aircraft engine shell with good heat dissipation performance comprises an engine shell, and is characterized by further comprising a supporting seat, a communicating groove, an outer shell, a connecting seat, a radiating fin, a connecting sheet, an air outlet, a cooling cavity, blades, an air inlet, a motor, a connecting shaft, an inner cavity, a transmission shaft, a liquid collecting device, a liquid inlet, an impeller, a liquid outlet and a liquid separating device; the supporting seat is fixedly connected to the bottom of the shell of the engine, a plurality of transverse communicating grooves are formed in the upper side of the supporting seat, and the bottom of the supporting seat is fixedly connected to the bottom surface inside the shell; the connecting pieces are vertically arranged and uniformly and fixedly connected to the outer surface of the shell of the engine, and the outer side edges of the connecting pieces are fixedly connected with the inner side surface of the shell; the radiating fins are arranged vertically and are uniformly and fixedly connected to the outer surface of the shell; the cooling cavity is arranged inside the upper side of the outer shell, and a plurality of air outlets are uniformly formed in the lower sides of the peripheral edges of the cooling cavity; the air inlets are multiple and are respectively arranged in the periphery of the upper side of the cooling cavity; the motor is fixedly connected to the center of the top of the outer shell; the connecting shaft is movably connected in a center hole at the upper side of the outer shell, and the shaft end at the upper side of the connecting shaft is fixedly connected with an output shaft at the lower side of the motor; the blade is movably connected to the center of the upper side of the cooling cavity, and the center of the blade is fixedly connected with the outer part of the connecting shaft; the inner cavity is arranged in the center of the upper side of the outer shell, the center of the inner cavity is movably connected with a transmission shaft, and the shaft end of the upper side of the transmission shaft is fixedly connected with the shaft end of the lower side of the connecting shaft; the impeller is movably connected in the inner cavity, and the center of the impeller is fixedly connected with the outer part of the transmission shaft; the liquid inlet hole is formed in the right side of the inner cavity, and a right inlet of the liquid inlet hole is connected with a left outlet of the liquid collecting device; the liquid collecting device is longitudinally and fixedly connected to the right side of the center of the upper surface of the engine shell; the liquid outlet hole is formed in the left side of the inner cavity, and the left outlet of the liquid outlet hole is connected with the right inlet of the liquid separating device; the liquid separating device is longitudinally and fixedly connected to the left side of the center of the upper surface of the shell of the engine.
Preferably, the liquid collecting device comprises a first pipe body, an output pipe and an input hole; the outlet pipe of body left side central authorities fixedly connected with, a body right side evenly is equipped with the several input hole.
Preferably, the specific structure of the liquid separating device comprises a second pipe body, an input pipe and an output hole; the inlet fixedly connected with input tube in two right sides of body, two left sides of body evenly are equipped with the several delivery outlet.
Preferably, the connecting piece is made of a heat dissipating material.
Preferably, heat conduction oil is arranged between the outside of the engine shell and the inside of the outer shell.
The utility model has the advantages that:
(1) the utility model discloses the rotation of well connecting axle then can drive the blade rotation to can inhale the cooling chamber with the outside air, then through the even blowing of air outlet to the fin, thereby improved radiating effect.
(2) The utility model discloses the rotation of well transmission shaft then drives the impeller rotation to can make the conduction oil flow around the anticlockwise circulation of engine housing, just also ensure the radiating homogeneity of engine housing, and avoid local overheat to cause the engine life to descend.
(3) The utility model discloses well album of liquid device that sets up can cooperate with dividing the liquid device with the even suction of the conduction oil on engine housing right side simultaneously to will inhale conduction oil homodisperse to the engine housing left side, just also ensured the radiating homogeneity of conduction oil circulation flow.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the liquid trap structure.
Fig. 3 is a schematic structural diagram of the liquid separating device.
In the figure: 1-an engine housing; 2-a support seat; 3-a communicating groove; 4-an outer shell; 5-a connecting seat; 6-a heat sink; 7-connecting the sheet; 8-air outlet; 9-a cooling cavity; 10-a blade; 11-an air inlet; 12-a motor; 13-a connecting shaft; 14-lumen; 15-a drive shaft; 16-a liquid collection device; 17-liquid inlet hole; 18-an impeller; 19-liquid outlet holes; 20-a liquid separating device; 161-pipe body one; 162-an output pipe; 163-input aperture; 201-pipe body two; 202-an input tube; 203-output hole.
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.
As shown in fig. 1, an aircraft engine casing with good heat dissipation performance comprises an engine casing 1, and further comprises a support seat 2, a communicating groove 3, an outer casing 4, a connecting seat 5, a heat sink 6, a connecting sheet 7, an air outlet 8, a cooling cavity 9, blades 10, an air inlet 11, a motor 12, a connecting shaft 13, an inner cavity 14, a transmission shaft 15, a liquid collecting device 16, a liquid inlet hole 17, an impeller 18, a liquid outlet hole 19 and a liquid separating device 20; the supporting seat 2 is fixedly connected to the bottom of the engine shell 1, a plurality of transverse communicating grooves 3 are formed in the upper side of the supporting seat 2, and the bottom of the supporting seat 2 is fixedly connected to the bottom surface inside the outer shell 4; the connecting pieces 7 are vertically arranged and uniformly and fixedly connected to the outer surface of the engine shell 1, and the outer side edges of the connecting pieces 7 are fixedly connected with the inner side surface of the shell 4; the radiating fins 6 and the connecting sheets 7 are vertically arranged and uniformly and fixedly connected to the outer surface of the outer shell 4; the cooling cavity 9 is arranged inside the upper side of the outer shell 4, and a plurality of air outlets 8 are uniformly arranged on the lower sides of the peripheral edges of the cooling cavity 9; the air inlets 11 are multiple, and the multiple air inlets 11 are respectively arranged in the periphery of the upper side of the cooling cavity 9; the motor 12 is fixedly connected to the center of the top of the outer shell 4; the connecting shaft 13 is movably connected in a center hole at the upper side of the outer shell 4, and the shaft end at the upper side of the connecting shaft 13 is fixedly connected with an output shaft at the lower side of the motor 12; the blade 10 is movably connected to the center of the upper side of the cooling cavity 9, and the center of the blade 10 is fixedly connected with the outer part of the connecting shaft 13; the inner cavity 14 is arranged in the center of the upper side of the outer shell 4, the center of the inner cavity 14 is movably connected with a transmission shaft 15, and the shaft end of the upper side of the transmission shaft 15 is fixedly connected with the shaft end of the lower side of the connecting shaft 13; the impeller 18 is movably connected in the inner cavity 14, and the center of the impeller 18 is fixedly connected with the outer part of the transmission shaft 15; the liquid inlet hole 17 is arranged on the right side of the inner cavity 14, and the right inlet of the liquid inlet hole 17 is connected with the left outlet of the liquid collecting device 16; the liquid collecting device 16 is longitudinally and fixedly connected to the right side of the center of the upper surface of the engine shell 1; the liquid outlet 19 is arranged on the left side of the inner cavity 14, and the left outlet of the liquid outlet 19 is connected with the right inlet of the liquid separating device 20; the liquid separating device 20 is fixedly connected to the left side of the center of the upper surface of the engine shell 1 in the longitudinal direction.
As shown in FIG. 2, the liquid collecting device 16 comprises a first pipe 161, an output pipe 162 and an input hole 163; an output pipe 162 is fixedly connected to the left side center outlet of the first pipe body 161, and a plurality of input holes 163 are uniformly formed in the right side of the first pipe body 161.
As shown in fig. 3, the specific structure of the liquid separation device 20 includes a second pipe body 201, an input pipe 202 and an output hole 203; an inlet 202 is fixedly connected to the central inlet on the right side of the second pipe body 201, and a plurality of output holes 203 are uniformly formed in the left side of the second pipe body 201.
Wherein the connecting sheet 7 is made of a heat dissipation material; and heat conduction oil is arranged between the outside of the engine shell 1 and the inside of the outer shell 4.
When the utility model is used, the motor 12 is started to drive the connecting shaft 13 and the transmission shaft 15 to rotate, the rotation of the connecting shaft 13 can drive the blades 10 to rotate, so that the external air can be sucked into the cooling cavity 9 and then uniformly blown to the radiating fins 6 through the air outlet 8, thereby improving the heat dissipation effect, and the rotation of the transmission shaft 15 drives the impeller 18 to rotate, so that the heat conduction oil can circularly flow around the engine shell 1 anticlockwise, the heat dissipation uniformity of the engine shell 1 is ensured, the service life of the engine is prevented from being reduced due to local overheating, the liquid collecting device 16 arranged additionally can evenly suck the heat conducting oil on the right side of the engine shell 1 and is matched with the liquid separating device 20, thereby evenly dispersing the sucked heat-conducting oil to the left side of the engine shell 1, and ensuring the uniformity of heat dissipation of the heat-conducting oil circulating flow.
The control mode of the present invention is controlled by manual starting or by the existing automation technology, the connection diagram of the power element and the supply of the power source belong to the common knowledge in the field, and the present invention is mainly used for protecting the mechanical device, so the present invention does not explain the control mode and the wiring arrangement in detail.
In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.
The basic principles and main features of the present invention and the advantages of the present invention have been shown and described above, and it should be understood by those skilled in the art that the present invention is not limited by the above embodiments, which are only illustrative, but also various changes and modifications may be made without departing from the spirit and scope of the present invention, which fall within the scope of the present invention as claimed, which is defined by the appended claims and their equivalents.
Claims (5)
1. An aircraft engine shell with good heat dissipation performance comprises an engine shell (1), and is characterized by further comprising a supporting seat (2), a communicating groove (3), an outer shell (4), a connecting seat (5), a radiating fin (6), a connecting sheet (7), an air outlet (8), a cooling cavity (9), blades (10), an air inlet (11), a motor (12), a connecting shaft (13), an inner cavity (14), a transmission shaft (15), a liquid collecting device (16), a liquid inlet hole (17), an impeller (18), a liquid outlet hole (19) and a liquid separating device (20);
the supporting seat (2) is fixedly connected to the bottom of the engine shell (1), a plurality of transverse communication grooves (3) are formed in the upper side of the supporting seat (2), and the bottom of the supporting seat (2) is fixedly connected to the bottom surface of the interior of the shell (4);
the connecting pieces (7) are vertically arranged and uniformly and fixedly connected to the outer surface of the engine shell (1), and the outer side edges of the connecting pieces (7) are fixedly connected with the inner side surface of the shell (4);
the radiating fins (6) are arranged vertically, and the connecting sheets (7) are uniformly and fixedly connected to the outer surface of the outer shell (4);
the cooling cavity (9) is arranged inside the upper side of the outer shell (4), and a plurality of air outlets (8) are uniformly arranged on the lower side of the peripheral edge of the cooling cavity (9);
the air inlets (11) are multiple, and the multiple air inlets (11) are respectively arranged in the periphery of the upper side of the cooling cavity (9);
the motor (12) is fixedly connected to the center of the top of the outer shell (4);
the connecting shaft (13) is movably connected in a center hole at the upper side of the outer shell (4), and the shaft end at the upper side of the connecting shaft (13) is fixedly connected with an output shaft at the lower side of the motor (12);
the blades (10) are movably connected to the center of the upper side of the cooling cavity (9), and the centers of the blades (10) are fixedly connected with the outer part of the connecting shaft (13);
the inner cavity (14) is arranged in the center of the upper side of the outer shell (4), the center of the inner cavity (14) is movably connected with a transmission shaft (15), and the shaft end of the upper side of the transmission shaft (15) is fixedly connected with the shaft end of the lower side of the connecting shaft (13);
the impeller (18) is movably connected in the inner cavity (14), and the center of the impeller (18) is fixedly connected with the outer part of the transmission shaft (15);
the liquid inlet hole (17) is arranged on the right side of the inner cavity (14), and a right inlet of the liquid inlet hole (17) is connected with a left outlet of the liquid collecting device (16);
the liquid collecting device (16) is longitudinally and fixedly connected to the right side of the center of the upper surface of the engine shell (1);
the liquid outlet hole (19) is arranged on the left side of the inner cavity (14), and the left outlet of the liquid outlet hole (19) is connected with the right inlet of the liquid separating device (20);
the liquid separating device (20) is longitudinally and fixedly connected to the left side of the center of the upper surface of the engine shell (1).
2. The aircraft engine casing with good heat dissipation performance according to claim 1, wherein the specific structure of the liquid collecting device (16) comprises a first pipe body (161), an output pipe (162) and an input hole (163);
the outlet pipe (162) is fixedly connected with the left side central outlet of the first pipe body (161), and a plurality of input holes (163) are uniformly formed in the right side of the first pipe body (161).
3. The aircraft engine shell with good heat dissipation performance as recited in claim 1, wherein the specific structure of the liquid separation device (20) comprises a second pipe body (201), an input pipe (202) and an output hole (203);
the inlet fixedly connected with input tube (202) in body two (201) right side central authorities, body two (201) left side evenly is equipped with several delivery outlet (203).
4. The aircraft engine shell with good heat dissipation performance according to claim 1, wherein the connecting piece (7) is made of a heat dissipation material.
5. The aircraft engine shell with good heat dissipation performance according to claim 1 is characterized in that heat conduction oil is arranged between the outside of the engine shell (1) and the inside of the outer shell (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022554503.7U CN213510761U (en) | 2020-11-08 | 2020-11-08 | Aeroengine shell with good heat dissipation performance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022554503.7U CN213510761U (en) | 2020-11-08 | 2020-11-08 | Aeroengine shell with good heat dissipation performance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213510761U true CN213510761U (en) | 2021-06-22 |
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ID=76421536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022554503.7U Active CN213510761U (en) | 2020-11-08 | 2020-11-08 | Aeroengine shell with good heat dissipation performance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213510761U (en) |
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2020
- 2020-11-08 CN CN202022554503.7U patent/CN213510761U/en active Active
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