CN220955837U - Stepped cooling structure of aeroengine - Google Patents
Stepped cooling structure of aeroengine Download PDFInfo
- Publication number
- CN220955837U CN220955837U CN202322896538.2U CN202322896538U CN220955837U CN 220955837 U CN220955837 U CN 220955837U CN 202322896538 U CN202322896538 U CN 202322896538U CN 220955837 U CN220955837 U CN 220955837U
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- heat
- heat dissipation
- aeroengine
- fixedly connected
- shell
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- 238000001816 cooling Methods 0.000 title claims abstract description 37
- 230000017525 heat dissipation Effects 0.000 claims abstract description 47
- 244000309464 bull Species 0.000 claims abstract description 30
- 241000883990 Flabellum Species 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims description 11
- 230000005540 biological transmission Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000001914 filtration Methods 0.000 description 3
- 239000000498 cooling water Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000009835 boiling Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Landscapes
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The utility model discloses a stepped cooling structure of an aeroengine, which comprises an aeroengine shell, a primary cooling assembly and an auxiliary heat dissipation assembly. The beneficial effects of the utility model are as follows: the heat that aeroengine operation produced is firstly absorbed through the heat conduction board, then in the heat transfer pipe reaches the seal shell with the heat transfer of heat conduction board, realize the one-level heat dissipation to aeroengine, heat rethread fin in the seal shell absorbs this moment, the heat on fin surface dispels the heat through a plurality of heat dissipation posts at last, realize the second grade heat dissipation to aeroengine, and aeroengine drives the second bull stick and rotates when rotatory, the second bull stick rotates and drives the flabellum rotation then, the wind-force that the flabellum rotation produced blows to the heat dissipation post through the rectangle play tuber pipe, can accelerate the heat dissipation on heat dissipation post surface, realize the tertiary heat dissipation to aeroengine, adopt this kind of step cooling mode, radiating efficiency is higher, the radiating effect is more obvious.
Description
Technical Field
The utility model relates to a cooling structure, in particular to a stepped cooling structure of an aeroengine, and belongs to the technical field of engine cooling.
Background
An aeroengine is a machine capable of converting other forms of energy into mechanical energy, including, for example, an internal combustion engine (gasoline engine, etc.), an external combustion engine (stirling engine, steam engine, etc.), an electric motor, etc. Such as internal combustion engines, typically convert chemical energy into mechanical energy. The engine is applicable to both power generation devices and to the entire machine (e.g., gasoline engine, aeroengine) including the power plant. The existing small aeroengine is poor in heat dissipation, a large amount of heat can be generated in the long-time working process, the inside of the engine body is sealed, and heat dissipation is very important for the engine.
The existing engine cooling mechanism, such as an engine water cooling system and an aeroengine disclosed in patent number CN111927626A, adopts the water cooling system, can effectively keep the pressure of the discharged cooling water and prevent the cooling water from boiling and evaporating, but adopts the cooling mode to be single, cannot realize stepped cooling, and has unsatisfactory cooling effect.
Disclosure of utility model
The utility model aims to solve at least one technical problem, and provides a stepped cooling structure of an aeroengine.
The utility model realizes the above purpose through the following technical scheme: a stepped cooling structure of an aeroengine comprises
The aero-engine shell is arranged in the middle of the cooling structure, and the output end of the aero-engine shell is fixedly connected with a rotating shaft;
The primary cooling assembly is used for primarily radiating heat generated by the internal operation of the engine, is arranged on two sides of the aero-engine shell, and comprises a sealing sleeve symmetrically and fixedly connected to the surface of the aero-engine shell, a heat-conducting plate fixedly inserted into the aero-engine shell, and a heat-exchanging pipe, a sealing shell, a heat-radiating fin and a heat-radiating column for cooling the heat-conducting plate;
The auxiliary heat dissipation assembly is used for dissipating heat of the heat dissipation column, is arranged on one side of the sealing shell, and comprises a support rod fixedly connected to the surface of the air engine shell, a fixing plate fixedly connected to the end part of the support rod, a hollow box for dissipating heat of the heat dissipation column, a second rotating rod, fan blades and a rectangular air outlet pipe.
As still further aspects of the utility model: the surface fixedly connected with heat exchange tube of heat-conducting plate, the heat exchange tube is fixedly inserted and is established on aero-engine casing surface, and the one end of heat exchange tube extends to the outside of aero-engine casing, and aero-engine casing surface symmetry fixedly connected with cover is established the seal shell on heat exchange tube surface, and the equidistant fixedly connected with fin in surface of seal shell, the bottom surface of fin extend to inside the seal shell, and the fixedly connected with of surface of fin is a plurality of heat dissipation posts.
As still further aspects of the utility model: the cross section of the radiating fin is rectangular and annular.
As still further aspects of the utility model: the fixed plate's surface fixedly connected with hollow box, the surface rotation of fixed plate is connected with the second bull stick, and the one end of second bull stick extends to the inside of hollow box to with set up the flabellum fixed connection in the inside of hollow box, the surface fixedly connected with of hollow box four rectangle play tuber pipes, hollow box and rectangle play tuber pipe are linked together.
As still further aspects of the utility model: the surface of the hollow box is symmetrically provided with filter holes.
As still further aspects of the utility model: the fixed surface of pivot has cup jointed the primary pulley, and the both sides of primary pulley are connected with the secondary pulley through belt drive respectively, and the bottom surface fixedly connected with third bull stick of secondary pulley, the fixed plate's of fixed surface fixedly connected with U type frame, third bull stick and U type frame swivelling joint, the bottom fixedly connected with first bevel gear of third bull stick, the surface engagement of first bevel gear is connected with second bevel gear, second bevel gear and second bull stick fixed connection.
The beneficial effects of the utility model are as follows:
In the use, the heat that aeroengine operation produced is at first absorbed through the heat conduction board, then in transferring the sealed shell with the heat transfer pipe, realize the one-level heat dissipation to aeroengine, the heat rethread fin in the sealed shell absorbs this moment, the heat on fin surface dispels the heat through a plurality of heat dissipation posts at last, realize the second heat dissipation to aeroengine, and aeroengine drives the second bull stick and rotates when rotatory, the second bull stick rotates and then drives the flabellum rotation, the wind-force that the flabellum rotation produced blows the heat dissipation post through the rectangle play tuber pipe, can accelerate the heat dissipation on heat dissipation post surface, realize the tertiary heat dissipation to aeroengine, adopt this kind of stepwise cooling's mode, radiating efficiency is higher, the radiating effect is more obvious.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic diagram of the whole structure of the present utility model;
FIG. 3 is a cross-sectional view of the connection of the heat-conducting plate and the aircraft engine housing of the present utility model;
FIG. 4 is a schematic view of the connection structure of the primary cooling module of the present utility model;
fig. 5 is a schematic diagram of a connection structure of an auxiliary heat dissipation assembly according to the present utility model.
In the figure: 1. an aero-engine housing; 2. a rotating shaft; 3. a primary cooling assembly; 31. sealing sleeve; 32. a heat conductive plate; 33. a heat exchange tube; 34. a sealed housing; 35. a heat sink; 36. a heat radiation column; 4. an auxiliary heat dissipation assembly; 41. a main belt wheel; 42. a belt; 43. a secondary pulley; 44. a third rotating rod; 45. a U-shaped frame; 46. a first bevel gear; 47. a second bevel gear; 48. a fixing plate; 49. a support rod; 410. a hollow box; 411. rectangular air outlet pipes; 412. filtering holes; 413. a fan blade; 414. and a second rotating rod.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Example 1
As shown in fig. 1 to 5, a stepped cooling structure of an aeroengine comprises
The aero-engine shell 1 is arranged in the middle of the cooling structure, and the output end of the aero-engine shell is fixedly connected with a rotating shaft 2;
the primary cooling assembly 3 is used for primarily radiating heat generated by the internal operation of the engine, is arranged on two sides of the aero-engine shell 1, and comprises a sealing sleeve 31 symmetrically and fixedly connected to the surface of the aero-engine shell 1, a heat conducting plate 32 fixedly inserted into the aero-engine shell 1, a heat exchange tube 33 used for cooling the heat conducting plate 32, a sealing shell 34, a heat radiating fin 35 and a heat radiating column 36;
The auxiliary heat dissipation component 4 is used for dissipating heat of the heat dissipation column 36, is arranged on one side of the sealing shell 34, and comprises a support rod 49 fixedly connected to the surface of the aero-engine housing 1, a fixing plate 48 fixedly connected to the end part of the support rod 49, a hollow box 410 used for dissipating heat of the heat dissipation column 36, a second rotating rod 414, fan blades 413 and a rectangular air outlet pipe 411.
Example two
As shown in fig. 1 to 5, this embodiment includes, in addition to all the technical features of the first embodiment, the following steps:
The surface fixedly connected with heat exchange tube 33 of heat-conducting plate 32, heat exchange tube 33 fixed insertion is at aeroengine casing 1 surface, the one end of heat exchange tube 33 extends to the outside of aeroengine casing 1, aeroengine casing 1 surface symmetry fixedly connected with cover is established at the sealed shell 34 on heat exchange tube 33 surface, the equidistant fixedly connected with fin 35 in the surface of sealed shell 34, the bottom surface of fin 35 extends to the sealed shell 34 inside, the surface fixedly connected with a plurality of heat dissipation posts 36 of fin 35, in the use, the heat that the aeroengine operation produced is firstly absorbed through heat-conducting plate 32, then pass through heat exchange tube 33 with the heat transfer of heat-conducting plate 32 in the sealed shell 34, realize the one-level heat dissipation to the aeroengine, heat rethread fin 35 in the sealed shell 34 absorbs this moment, the heat on fin 35 surface carries out the heat dissipation through a plurality of heat dissipation posts 36 at last, realize the second grade heat dissipation to the aeroengine.
The cross section of the radiating fin 35 is rectangular and annular, and is conveniently sleeved on the sealing shell 34.
Example III
As shown in fig. 1 to 5, this embodiment includes, in addition to all the technical features of the first embodiment, the following steps:
The fixed plate 48's surface fixedly connected with hollow box 410, the surface rotation of fixed plate 48 is connected with second bull stick 414, the one end of second bull stick 414 extends to the inside of hollow box 410 to with set up the flabellum 413 fixed connection in the inside of hollow box 410, the fixed surface of hollow box 410 is connected with four rectangle tuber pipes 411, hollow box 410 and rectangle tuber pipe 411 are linked together, the aeroengine drives the rotation of second bull stick 414 when rotatory, the rotation of second bull stick 414 then drives flabellum 413 and rotate, the wind-force that the flabellum 413 rotatory produced blows heat dissipation post 36 through rectangle tuber pipe 411, can accelerate the heat dissipation of heat dissipation post 36 surface, realize the tertiary heat dissipation to the aeroengine.
The surface of the hollow box 410 is symmetrically provided with filtering holes 412, which is convenient for filtering air and prevents dust from adhering to the surface of the fan blades 413.
The surface fixing of pivot 2 has cup jointed main pulley 41, the both sides of main pulley 41 are connected with secondary pulley 43 through the belt 42 transmission respectively, secondary pulley 43's bottom surface fixedly connected with third bull stick 44, fixed plate 48's surface fixedly connected with U type frame 45, third bull stick 44 and U type frame 45 rotate and connect, third bull stick 44's bottom fixedly connected with first bevel gear 46, first bevel gear 46's surface meshing is connected with second bevel gear 47, second bevel gear 47 and second bull stick 414 fixed connection, in the use, the aeroengine operation can drive pivot 2 rotation, pivot 2 rotates and then drives primary pulley 41 rotation, primary pulley 41 rotates and drives secondary pulley 43 rotation through belt 42, secondary pulley 43 rotates and then drives third bull stick 44 rotation, third bull stick 44 rotates and drives first bevel gear 46 rotation, first bevel gear 46 rotates and then drives second bevel gear 47 rotation, second bevel gear 47 rotates and then drives second bull stick 414 rotation, thereby can drive 413 rotation.
Working principle: during the use, the heat that aeroengine operation produced is firstly absorbed through heat-conducting plate 32, then heat transfer to sealed shell 34 with heat-conducting plate 32 through heat exchange tube 33 is in, realize the one-level heat dissipation to the aeroengine, heat rethread fin 35 in the sealed shell 34 absorbs this moment, the heat on fin 35 surface dispels the heat through a plurality of heat dissipation posts 36 at last, realize the second grade heat dissipation to the aeroengine, and the aeroengine operation can drive pivot 2 rotation, pivot 2 rotates and then drives primary pulley 41 and rotates, primary pulley 41 rotates and drives secondary pulley 43 through belt 42 rotation, secondary pulley 43 rotates and then drives the rotation of third bull stick 44, the rotation of third bull stick 44 drives first bevel gear 46 and rotates, first bevel gear 46 rotates and then drives second bevel gear 47 and rotate, second bevel gear 47 rotates and then drives second bull stick 414 and rotate, thereby can drive the flabellum 413 rotation, the wind-force that the rotation produced through rectangle play tuber pipe 36, can accelerate the heat dissipation on the surface of heat dissipation post 36, realize the tertiary heat dissipation to the aeroengine, adopt this kind of step heat dissipation mode that can effectively reduce the heat dissipation effect inside aeroengine 1, aeroengine can be better.
It will be evident to those skilled in the art that the utility model is not limited to the details of the foregoing illustrative embodiments, and that the present utility model may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (6)
1. A stepped cooling structure of an aeroengine is characterized by comprising
The aero-engine shell (1) is arranged in the middle of the cooling structure, and the output end of the aero-engine shell is fixedly connected with the rotating shaft (2);
The primary cooling assembly (3) is used for primarily radiating heat generated by the internal operation of the engine, is arranged on two sides of the aero-engine shell (1), and comprises sealing sleeves (31) symmetrically and fixedly connected to the surface of the aero-engine shell (1), a heat conducting plate (32) fixedly inserted into the aero-engine shell (1), a heat exchange tube (33), a sealing shell (34), cooling fins (35) and a cooling column (36) for cooling the heat conducting plate (32);
The auxiliary heat dissipation assembly (4) is used for dissipating heat of the heat dissipation column (36), is arranged on one side of the sealing shell (34), and comprises a support rod (49) fixedly connected to the surface of the aero-engine shell (1), a fixing plate (48) fixedly connected to the end part of the support rod (49), a hollow box (410) for dissipating heat of the heat dissipation column (36), a second rotating rod (414), fan blades (413) and a rectangular air outlet pipe (411).
2. The stepped cooling structure of an aircraft engine according to claim 1, wherein: the surface fixedly connected with of heat conduction board (32) heat exchange tube (33), heat exchange tube (33) are fixed to be inserted and establish aircraft engine casing (1) surface, the one end of heat exchange tube (33) extends to the outside of aircraft engine casing (1), aircraft engine casing (1) surface symmetry fixedly connected with cover is established sealed shell (34) on heat exchange tube (33) surface, the equidistant fixedly connected with fin (35) of surface of sealed shell (34), the bottom surface of fin (35) extends to inside sealed shell (34), the fixedly connected with of surface of fin (35) a plurality of heat dissipation post (36).
3. The stepped cooling structure of an aircraft engine according to claim 2, wherein: the cross section of the radiating fin (35) is rectangular and annular.
4. A stepped cooling structure of an aircraft engine according to claim 3, wherein: the surface fixing of fixed plate (48) is connected with hollow box (410), the surface rotation of fixed plate (48) is connected with second bull stick (414), the one end of second bull stick (414) extends to the inside of hollow box (410) to with set up the inside flabellum (413) fixed connection of hollow box (410), the surface fixing of hollow box (410) is connected with four rectangle tuber pipes (411), hollow box (410) with rectangle tuber pipe (411) are linked together.
5. The stepped cooling structure of an aircraft engine according to claim 1, wherein: the surface of the hollow box (410) is symmetrically provided with filter holes (412).
6. The stepped cooling structure of an aircraft engine according to claim 1, wherein: the surface fixing of pivot (2) has cup jointed main belt wheel (41), the both sides of main belt wheel (41) are connected with secondary pulley (43) through belt (42) transmission respectively, the bottom surface fixedly connected with third bull stick (44) of secondary pulley (43), the surface fixing of fixed plate (48) is connected with U type frame (45), third bull stick (44) with U type frame (45) rotate and connect, the bottom fixedly connected with first bevel gear (46) of third bull stick (44), the surface engagement of first bevel gear (46) is connected with second bevel gear (47), second bevel gear (47) and second bull stick (414) fixed connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322896538.2U CN220955837U (en) | 2023-10-27 | 2023-10-27 | Stepped cooling structure of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322896538.2U CN220955837U (en) | 2023-10-27 | 2023-10-27 | Stepped cooling structure of aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220955837U true CN220955837U (en) | 2024-05-14 |
Family
ID=90979986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322896538.2U Active CN220955837U (en) | 2023-10-27 | 2023-10-27 | Stepped cooling structure of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220955837U (en) |
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2023
- 2023-10-27 CN CN202322896538.2U patent/CN220955837U/en active Active
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