CN214035854U

CN214035854U - Heat radiator for aeroengine

Info

Publication number: CN214035854U
Application number: CN202120163871.0U
Authority: CN
Inventors: 李玮林; 吕永林
Original assignee: Laizhou Zhongwei Machinery Co ltd
Current assignee: Laizhou Zhongwei Machinery Co ltd
Priority date: 2021-01-21
Filing date: 2021-01-21
Publication date: 2021-08-24
Anticipated expiration: 2031-01-21

Abstract

The utility model relates to the technical field of aircraft engine heat dissipation, in particular to a heat dissipation device of an aircraft engine, which comprises a U-shaped plate body, wherein a chute is arranged on one side of each side arm of the U-shaped plate body opposite to each other, a liquid inlet pipe is embedded at the position, close to the top, of the left end surface of the U-shaped plate body, a liquid outlet pipe is embedded at the position, close to the bottom, of the left end surface of the U-shaped plate body, a first heat dissipation fin is arranged at the bottom of the inner side surface of the U-shaped plate body, a motor, a support frame and a fan are sequentially arranged inside a cylinder from right to left; this aeroengine's heat abstractor, first radiating fin and second radiating fin's cooperation is convenient for carry out preliminary heat absorption and is handled, and the coolant liquid of packing in toward the intermediate layer through the feed liquor pipe is convenient for cool down and is used, under the cooperation of motor and fan, carries out the thermal treatment once more, and the clearance in the middle of first radiating fin and the second radiating fin is convenient for ventilate and dispel the heat for thermal dissipation.

Description

Heat radiator for aeroengine

Technical Field

The utility model relates to an aeroengine heat dissipation technical field specifically is an aeroengine's heat abstractor.

Background

The aircraft engine is used for generating thrust to make an aircraft advance, an advanced aircraft needs a strong heart, the aircraft engine is a power source of the aircraft, the aircraft engine is a very complicated high-end machine, and the working conditions have the characteristics of high temperature, high pressure and high speed: the working temperature is high, and the temperature at each position inside the device is different and constantly changed; the gas pressure is large, and the working load is high; the rotor has high rotating speed, and bears various influences on the engine caused by environment and maneuvering flight;

the heat dissipation of a general aircraft engine is not obvious enough, the long-time work, the temperature can not be dissipated in time, the temperature is accumulated, the overall working efficiency is reduced, the internal temperature can not be dissipated in time, and the overall service life is prolonged.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aeroengine's heat abstractor 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:

a heat dissipation device of an aircraft engine comprises a U-shaped plate body, wherein the top of the U-shaped plate body is provided with a clamping groove, one side of each side arm of the U-shaped plate body, which is opposite to each other, is provided with a sliding groove, a hollowed area between the inner wall and the outer wall of the U-shaped plate body is an interlayer, a liquid inlet pipe communicated with the interlayer is embedded at the position, close to the top, of the left end surface of the U-shaped plate body, a liquid outlet pipe communicated with the interlayer is embedded at the position, close to the bottom, of the left end surface of the U-shaped plate body, a first heat dissipation fin is arranged at the position of the bottom of the inner side surface of the U-shaped plate body, a fixed plate is arranged at the right end surface of the U-shaped plate body, a cylinder is embedded at the middle position of the fixed plate, a protective cover is installed at the left end surface of the cylinder, a filter screen is installed at the right end surface of the cylinder, a motor, a support frame and a fan are sequentially arranged inside the cylinder from right to left, a top cover is also arranged in the clamping groove, and a second heat dissipation fin is also arranged at the lower surface of the top cover, an aircraft engine main body is arranged in the middle of the U-shaped plate body.

Preferably, the width of the first radiating fin is matched with the width of the inner wall of the U-shaped plate body, and the first radiating fin is fixedly connected with the U-shaped plate body through a bolt.

Preferably, the feed liquor pipe is fixed with the welding of U type plate body, the drain pipe is fixed with the welding of U type plate body, feed liquor pipe, drain pipe tip all are equipped with the rubber buffer.

Preferably, the positions of the two side faces of the aircraft engine main body corresponding to the sliding grooves are further provided with sliding blocks, and the sliding blocks and the aircraft engine main body are of an integrally formed structure.

Preferably, the width of the fixing plate is matched with the width between the two side arms of the U-shaped plate body, and the fixing plate is fixedly connected with the U-shaped plate body through bolts.

Preferably, the cylinder is fixed with the fixed plate in a welded mode, the protective cover is fixedly connected with the cylinder through bolts, the filter screen is fixedly connected with the cylinder through bolts, the support frame is fixedly connected with the cylinder through bolts, the motor is fixedly connected with the support frame through bolts, an output shaft of the motor penetrates through the support frame, and the output shaft is coaxially connected with the fan.

Preferably, the width of top cap and the width between the draw-in groove are looks adaptation, second radiating fin passes through bolt and top cap fixed connection, the top cap passes through bolt and U type plate body fixed connection.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the utility model discloses the aeroengine main part passes through the slider and closely pegs graft fixedly with U type plate body, and first radiating fin and second radiating fin's cooperation is convenient for carry out preliminary heat absorption and is handled, through the coolant liquid of feed liquor pipe toward packing in the intermediate layer, is convenient for cool down and uses, under the cooperation of motor and fan, carries out the heat dissipation again and handles, and the clearance in the middle of first radiating fin and the second radiating fin is convenient for ventilation cooling for thermal heat removes.

2. The utility model discloses the fan is protected to the protection casing, prevents to touch the damage, and the cooperation of filter screen prevents that dust granule and other impurity among the outside air from getting into inside, and the fan rotation of influence is used, and feed liquor pipe and drain pipe cooperation rubber buffer are convenient for seal, and the manual dismantlement of being convenient for simultaneously changes inside coolant liquid and uses.

Drawings

Fig. 1 is a schematic view of the overall structure of a heat dissipation device of an aircraft engine according to the present invention;

fig. 2 is a schematic side view of a heat dissipation device of an aircraft engine according to the present invention;

fig. 3 is a schematic view of the structure of the aircraft engine of the present invention with the top cover opened;

FIG. 4 is a schematic view of the combined structure of the U-shaped plate body and the main body of the aircraft engine;

FIG. 5 is a schematic view of the frame structure of the U-shaped plate of the present invention;

FIG. 6 is a schematic view of the assembly structure of the fixing plate and the cylinder of the present invention;

fig. 7 is a schematic view of the top cover frame structure of the present invention.

The various reference numbers in the figures mean:

1. a U-shaped plate body; 10. a card slot; 11. a chute; 12. an interlayer; 13. a liquid inlet pipe; 14. a liquid outlet pipe;

2. an aircraft engine main body; 20. a slider;

3. a fixing plate;

4. a cylinder; 40. a protective cover; 41. a filter screen; 42. a motor; 43. a support frame; 44. a fan;

5. a first heat radiation fin;

6. a top cover; 60. and a second heat dissipation fin.

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.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", 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 to simplify the description, but 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.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

Referring to fig. 1-7, the present invention provides a technical solution:

a heat dissipation device of an aircraft engine comprises a U-shaped plate body 1, wherein the top of the U-shaped plate body 1 is provided with a clamping groove 10, two opposite sides of the U-shaped plate body 1 are respectively provided with a sliding groove 11, a hollowed area between the inner wall and the outer wall of the U-shaped plate body 1 is an interlayer 12, a liquid inlet pipe 13 communicated with the interlayer 12 is embedded at the position, close to the top, of the left end surface of the U-shaped plate body 1, a liquid outlet pipe 14 communicated with the interlayer 12 is embedded at the position, close to the bottom, of the left end surface of the U-shaped plate body 1, a first heat dissipation fin 5 is arranged at the position, at the bottom, of the inner side surface of the U-shaped plate body 1, a fixing plate 3 is arranged at the right end surface of the U-shaped plate body 1, a cylinder 4 is embedded at the middle position of the fixing plate 3, a protective cover 40 is arranged at the left end surface of the cylinder 4, a filter screen 41 is arranged at the right end surface of the cylinder 4, a motor 42, a support frame 43 and a fan 44 are sequentially arranged from right to left inside the cylinder 4, a top cover 6 is also arranged in the clamping groove 10, a second heat dissipation fin 60 is arranged at the lower surface of the top cover 6, an aircraft engine main body 2 is arranged in the middle of the U-shaped plate body 1.

In this embodiment, the width of first radiating fin 5 and the width looks adaptation of U type plate body 1 inner wall, first radiating fin 5 passes through bolt and U type plate body 1 fixed connection, and first radiating fin 5 is changed to convenient to detach.

Further, feed liquor pipe 13 is fixed with the 1 butt fusion of U type plate body, and drain pipe 14 is fixed with the 1 butt fusion of U type plate body, and feed liquor pipe 13, the 14 tip of drain pipe all are equipped with the rubber buffer, and feed liquor pipe 13 is convenient for fill the coolant liquid in toward intermediate layer 12, cooperation rubber buffer, and the person of facilitating the use is manual opens and changes inside solution and use.

Specifically, the positions of the two side faces of the aircraft engine main body 2 corresponding to the sliding grooves 11 are further provided with the sliding blocks 20, and the sliding blocks 20 and the aircraft engine main body 2 are of an integrally formed structure, so that the aircraft engine main body 2 can be conveniently and rapidly installed and used.

Secondly, the width of fixed plate 3 and the width looks adaptation between the arm of U type plate body 1 both sides, fixed plate 3 passes through bolt and U type plate body 1 fixed connection, convenient to detach installation and use.

It should be noted that, the cylinder 4 is fixed to the fixing plate 3 by welding, the protective cover 40 is fixed to the cylinder 4 by bolts, the filter screen 41 is fixed to the cylinder 4 by bolts, the support frame 43 is fixed to the cylinder 4 by bolts, the motor 42 is fixed to the support frame 43 by bolts, the output shaft of the motor 42 passes through the support frame 43, the output shaft is coaxially connected to the fan 44, the motor 42 cooperates with the fan 44 to perform ventilation and heat dissipation to remove heat accumulated inside, the filter screen 41 filters the entering air, and the protective cover 40 protects the fan 44 to prevent the fan 44 from being damaged.

In addition, width looks adaptation between the width of top cap 6 and the draw-in groove 10, second radiating fin 60 passes through bolt and top cap 6 fixed connection, and top cap 6 passes through bolt and 1 fixed connection of U type plate body, and top cap 6 is convenient for fix inside aeroengine main part 2, prevents to break away from and influences holistic use, and second radiating fin 60 cooperates jointly with first radiating fin 5, and the inside ventilation and heat dissipation of being convenient for uses.

The heat abstractor of aeroengine of this embodiment is when using, the user is manual installs first radiating fin 5 in U type plate body 1, aeroengine main part 2 is installed in U type plate body 1 through the grafting of slider 20, top cap 6 is fixed on U type plate body 1, then the user is manual with motor 42 switch on, the output shaft rotates and drives fan 44, carry out ventilation cooling to inside, the user is manual with the coolant liquid from feed liquor pipe 13 add intermediate layer 12, then through sealing plug shutoff feed liquor pipe 1, accelerate inside temperature reduction, be convenient for whole aeroengine main part 2 cooling use, prolonged service life.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides an aeroengine's heat abstractor, includes U shaped plate body (1), its characterized in that: the novel U-shaped plate is characterized in that a clamping groove (10) is formed in the top of the U-shaped plate body (1), a sliding groove (11) is formed in one face of each of two side arms of the U-shaped plate body (1) opposite to each other, an interlayer (12) is arranged in a hollow area between the inner wall and the outer wall of the U-shaped plate body (1), a liquid inlet pipe (13) communicated with the interlayer (12) is embedded in the position, close to the top, of the left end face of the U-shaped plate body (1), a liquid outlet pipe (14) communicated with the interlayer (12) is embedded in the position, close to the bottom, of the left end face of the U-shaped plate body (1), a first radiating fin (5) is arranged in the position, a fixing plate (3) is arranged on the right end face of the U-shaped plate body (1), a cylinder (4) is embedded in the middle of the fixing plate (3), a protective cover (40) is installed on the left end face of the cylinder (4), a filter screen (41) is installed on the right end face of the cylinder (4), the cylinder (4) is internally provided with a motor (42), a support frame (43) and a fan (44) from right to left in sequence, a top cover (6) is further arranged in the clamping groove (10), a second heat dissipation fin (60) is further arranged on the lower surface of the top cover (6), and an aircraft engine main body (2) is arranged in the middle of the U-shaped plate body (1).

2. The heat sink of an aircraft engine as recited in claim 1, wherein: the width of the first radiating fin (5) is matched with the width of the inner wall of the U-shaped plate body (1), and the first radiating fin (5) is fixedly connected with the U-shaped plate body (1) through a bolt.

3. The heat sink of an aircraft engine as recited in claim 1, wherein: feed liquor pipe (13) are fixed with U type plate body (1) butt fusion, drain pipe (14) are fixed with U type plate body (1) butt fusion, feed liquor pipe (13), drain pipe (14) tip all are equipped with the rubber buffer.

4. The heat sink of an aircraft engine as recited in claim 1, wherein: the aircraft engine main part (2) both sides face still is equipped with slider (20) with the position that spout (11) correspond, slider (20) and aircraft engine main part (2) are the integrated into one piece structure.

5. The heat sink of an aircraft engine as recited in claim 1, wherein: the width of fixed plate (3) and the width looks adaptation between the arm of U type plate body (1) both sides, fixed plate (3) pass through bolt and U type plate body (1) fixed connection.

6. The heat sink of an aircraft engine as recited in claim 1, wherein: drum (4) and fixed plate (3) butt fusion are fixed, protection casing (40) pass through bolt and drum (4) fixed connection, filter screen (41) pass through bolt and drum (4) fixed connection, support frame (43) pass through bolt and drum (4) fixed connection, motor (42) pass through bolt and support frame (43) fixed connection, support frame (43) are passed to the output shaft of motor (42), and output shaft and fan (44) coaxial coupling.

7. The heat sink of an aircraft engine as recited in claim 1, wherein: the width of top cap (6) and the width looks adaptation between draw-in groove (10), second radiating fin (60) pass through bolt and top cap (6) fixed connection, top cap (6) pass through bolt and U type plate body (1) fixed connection.