CN216691269U - Aviation is with no connecting rod engine with rapid cooling structure - Google Patents
Aviation is with no connecting rod engine with rapid cooling structure Download PDFInfo
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- CN216691269U CN216691269U CN202220486172.4U CN202220486172U CN216691269U CN 216691269 U CN216691269 U CN 216691269U CN 202220486172 U CN202220486172 U CN 202220486172U CN 216691269 U CN216691269 U CN 216691269U
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- dissipation chamber
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model discloses an aviation connecting rod-free engine with a rapid cooling structure, which comprises an engine body, wherein the engine body comprises a gas compression bin and a gas compressor, the outer wall of the engine body is wrapped by a heat conducting plate, the outer wall of the heat conducting plate is fixedly provided with a plurality of heat conducting connecting pipes, the interiors of the plurality of heat conducting connecting pipes comprise a heat absorption graphite filling layer and an air circulation layer, the outside of the gas compression bin is provided with a heat dissipation chamber, one ends of the plurality of heat conducting connecting pipes are fixedly connected with the inner wall of the heat dissipation chamber, the aviation connecting rod-free engine with the rapid cooling structure is tightly attached to the heat conducting plate engine, can effectively absorb heat generated by the engine and then convey the heat away through the heat conducting connecting pipes, the heat absorption graphite filling layer in the heat conducting connecting pipes can absorb part of the heat transferred to the heat conducting connecting pipes, so that the heat is effectively relieved, the cooperation of circulation groove and through-flow hole is again with a part of heat outgoing.
Description
Technical Field
The utility model relates to an engine device with connecting rods, in particular to an aviation connecting-rod-free engine with a rapid cooling structure.
Background
The principle of the aviation connecting rod-free engine is that heat energy is converted into mechanical energy, the higher the temperature which can be borne, the greater the generated thrust, and the higher the performance of the engine. According to researches, the thrust-weight ratio of the gas turbine engine can be improved by about 10% when the temperature of the turbine inlet of the gas turbine engine is improved by 100 ℃, in recent years, the high-temperature heat-resistant material is adopted for the material of the aero-engine, the service temperature of the engine material is greatly improved by developing from a forging alloy to a conventional casting alloy and then from a directional solidification alloy to a single crystal alloy, but the high-temperature material only has the characteristic of high temperature resistance and can keep the operation effect of the engine by radiating heat.
But the existing aviation connecting rod-free engine with a rapid cooling structure is not perfect in structure and has certain defects:
1. the temperature of combustion chamber is too high on the engine, if untimely rapid cooling carries out under the high temperature condition, influences the loss of high temperature material to a certain extent to lead to the performance of engine, make the very big shortening of life of engine.
2. Since the aero-engine is always in a high-temperature consumption state when in use, parts for dissipating heat also need to be in a high-operation state, and if the parts are not maintained before or during use, the heat dissipation efficiency is affected.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an aviation connecting rod-free engine with a rapid cooling structure, which aims to solve the problem that rapid cooling and maintenance of heat dissipation components cannot be realized in the background technology.
In order to achieve the purpose, the utility model provides the following technical scheme: the aviation connecting-rod-free engine with the rapid cooling structure comprises an engine body, wherein the engine body comprises a compressed air bin and a compressor, the outer wall of the engine body is wrapped with a heat-conducting plate, a plurality of heat-conducting connecting pipes are fixedly arranged on the outer wall of the heat-conducting plate, the interiors of the plurality of heat-conducting connecting pipes comprise an endothermic graphite filling layer and an air circulation layer, a heat dissipation chamber is arranged outside the compressed air bin, one ends of the plurality of heat-conducting connecting pipes are fixedly connected with the inner wall of the heat dissipation chamber, water cooling boxes are symmetrically arranged on two sides of the heat dissipation chamber, two flow guide pipes are fixedly penetrated through the tops of the two water cooling boxes, and two backflow pipes are fixedly penetrated through the bottoms of the two water cooling boxes;
the front of the two sides of the heat dissipation chamber is provided with auxiliary plates, the front of each auxiliary plate is fixedly provided with an air guide fan, the front of each auxiliary plate is provided with a circulation groove, the inner wall of each circulation groove is fixedly clamped and connected with a filter screen, one end of each circulation groove is fixedly connected with an air gathering bucket, and the positions of the two air gathering buckets are consistent with the positions of adjacent water cooling boxes.
As a preferable technical scheme of the utility model, the gas compressor is fixedly arranged in the gas pressing bin, the gas pressing bin is positioned at one side of the combustion chamber, and the gas pressing bin is fixedly penetrated through the combustion chamber.
According to a preferable technical scheme of the utility model, the air circulation layers are all positioned on the outer wall of the heat absorption graphite filling layer, and the air circulation layers are all provided with a plurality of through holes.
As a preferable technical scheme of the utility model, one end of each of the two flow guide pipes is fixedly penetrated through the top of the heat dissipation chamber, and one end of each of the two return pipes is fixedly penetrated through the bottom of the heat dissipation chamber.
As a preferable technical scheme of the utility model, mounting frames are fixedly mounted at the bottom ends of the two water cooling tanks, and one ends of the two mounting frames are fixedly connected with the outer wall of the heat dissipation chamber.
As a preferred technical scheme of the present invention, the top ends of the two auxiliary plates are both fixedly mounted with a connecting frame, one end of each of the two connecting frames is rotatably connected with one end of the air guiding fan, and the positions of the two circulation grooves both correspond to the position of the air guiding fan.
As a preferred technical scheme of the utility model, the two water cooling tanks are symmetrically arranged and are respectively and electrically connected with an external power supply.
Compared with the prior art, the utility model has the beneficial effects that:
1. the aviation connecting rod-free engine with the rapid cooling structure is provided with the heat conducting plate, the heat radiating chamber, the heat conducting connecting pipe and the heat absorption graphite filling layer, the heat conducting plate engine is tightly attached, can effectively absorb heat generated by the engine and then transmits the heat away through the heat conducting connecting pipe, the heat absorption graphite filling layer in the heat conducting connecting pipe can absorb part of the heat transferred to the heat conducting connecting pipe, thereby effectively relieving the heat, the cooperation of the circulation groove and the through hole can dissipate part of the heat, the heat generated by the engine body is half dissipated before entering the heat dissipation chamber, therefore, the receiving of the heat dissipation chamber to heat is relieved, the reduction of the heat in the heat dissipation chamber is accelerated, the effect of rapid cooling is achieved, and the pressure of the engine body is relieved to a certain extent.
2. According to the aviation connecting-rod-free engine with the rapid cooling structure, the connecting frame, the air guide fan, the filter screen and the air gathering hopper are matched, when the engine runs, natural wind acts on the air guide fan, so that the air guide fan rotates to generate air flow, the generated air flow is guided to act on the water cooling tank through the matching of the auxiliary plate and the filter screen, and the filtered wind does not contain impurities, so that the water cooling tank can be more effectively cooled, and excessive impurities are prevented from being attached to the water cooling tank to influence the running of the water cooling tank.
Drawings
FIG. 1 is a schematic cross-sectional view of the present invention;
FIG. 2 is a schematic cross-sectional view of a heat dissipation chamber according to the present invention;
FIG. 3 is a schematic view of the auxiliary plate and the air guiding fan according to the present invention.
In the figure: 1. an engine body; 2. a compressed gas bin; 3. a compressor; 4. a combustion chamber; 5. a heat conducting plate; 6. a heat dissipation chamber; 7. a heat-conducting connecting pipe; 8. a heat absorbing graphite filler layer; 9. a water cooling tank; 10. a flow guide pipe; 11. a return pipe; 12. an auxiliary plate; 13. a connecting frame; 14. a wind guide fan; 15. a filter screen; 16. gather wind fill.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution of an aviation rodless engine with a rapid cooling structure:
the first embodiment is as follows:
according to the drawings of fig. 1 and 2, the aviation connecting rod-free engine with the rapid cooling structure comprises an engine body 1, wherein the engine body 1 comprises a compressed air bin 2 and a compressor 3, the outer wall of the engine body 1 is wrapped by a heat conducting plate 5, a plurality of heat conducting connecting pipes 7 are fixedly arranged on the outer wall of the heat conducting plate 5, the interiors of the heat conducting connecting pipes 7 comprise a heat absorption graphite filling layer 8 and an air circulation layer, a heat dissipation chamber 6 is arranged outside the compressed air bin 2, one ends of the heat conducting connecting pipes 7 are fixedly connected with the inner wall of the heat dissipation chamber 6, water cooling boxes 9 are symmetrically arranged on two sides of the heat dissipation chamber 6, two flow guide pipes 10 are fixedly penetrated through the tops of the two water cooling boxes 9, and two backflow pipes 11 are fixedly penetrated through the bottoms of the two water cooling boxes 9; through having set up heat-conducting plate 5, heat dissipation chamber 6, the cooperation of heat conduction connecting pipe 7 and endothermic graphite filling layer 8, 5 engines of heat-conducting plate closely laminate can carry out effectual absorption back to the heat that the engine produced and carry away the heat through heat conduction connecting pipe 7, heat absorption graphite filling layer 8 in the heat conduction connecting pipe 7 can absorb partly with transmitting to heat conduction connecting pipe 7 on the heat, thereby carried out effectual alleviating to the heat, the circulation groove is with a partial heat effluvium again with the cooperation in cross-flow hole, make the heat that engine body 1 produced by half by effluvium before getting into heat dissipation chamber 6, thereby the heat dissipation chamber 6 has been alleviated to thermal receipt, realized with higher speed the reduction to heat in the heat dissipation chamber 6, thereby reach rapid cooling's effect, the pressure of engine body 1 has been alleviated to a certain extent.
The inside of the compressed air bin 2 is fixedly provided with a compressor 3, the compressed air bin 2 is positioned at one side of a combustion chamber 4, the compressed air bin 2 is fixedly penetrated through the combustion chamber 4, important parts in the compressed air bin 2 when the compressor 3 is used, the heat of the compressed air bin 2 is different from that of the combustion chamber 4, the section in front of the combustion chamber 4 is a low-temperature zone, the temperature is lower than that of the rear section, a plurality of air circulation layers are positioned on the outer wall of a heat absorption graphite filling layer 8, a plurality of through holes are formed in the plurality of air circulation layers, the heat transmission can be blocked to a certain extent by the cooperation of the air circulation layers and the through holes, the heat transmission flowing speed is reduced, the heat can be greatly reduced in the through holes, one ends of two guide pipes 10 are fixedly penetrated through the top of a heat dissipation chamber 6, one ends of two return pipes 11 are fixedly penetrated through the bottom of the heat dissipation chamber 6, and the cooperation of the guide pipes 10 and the return pipes 11 plays a role in water cooling, two water-cooling tanks 9 that set up can reduce the pressure of water-cooling tank 9 operation to increase water-cooled circulation rate, make the cooling more thoroughly and quick.
When the connecting rod-free aircraft engine is used, the engine body 1 generates heat to transfer the heat to the heat conduction plate 5, the heat conduction plate 5 transfers the heat through the heat conduction connection pipe 7 through heat dispersion and diversion, the heat absorption graphite filling layer 8 in the heat conduction connection pipe 7 can absorb part of the heat transferred to the heat conduction connection pipe 7, so that the heat is effectively relieved, the circulation groove is matched with the flow through hole to dissipate part of the heat, the heat generated by the engine body 1 is dissipated half before entering the heat dissipation chamber 6, so that the heat reception of the heat dissipation chamber 6 is relieved, the heat enters the heat dissipation chamber 6 through the transmission of the heat conduction connection pipe 7, the water cooling tank 9 operates to drive circulating liquid to enter the heat dissipation chamber 6 through the flow guide pipe 10 to carry out transmission circulating cooling, and then the heat is recycled through the return pipe 11, and a large amount of heat can be discharged and eliminated through the matching of the guide pipe 10 and the return pipe 11, so that the engine body 1 is rapidly cooled.
Example two:
on the basis of the first embodiment, as shown in fig. 1 and 3, the front surfaces of both sides of the heat dissipation chamber 6 are respectively provided with an auxiliary plate 12, the front surfaces of the two auxiliary plates 12 are respectively fixedly provided with an air guiding fan 14, the front surfaces of the two auxiliary plates 12 are respectively provided with a circulation groove, the inner wall of the circulation groove is respectively fixedly clamped and connected with a filter screen 15, one end of the circulation groove is fixedly connected with an air gathering hopper 16, the positions of the two air gathering hoppers 16 are respectively consistent with the positions of the adjacent water cooling boxes 9, the bottom ends of the two water cooling boxes 9 are respectively fixedly provided with a mounting frame, one end of each mounting frame is fixedly connected with the outer wall of the heat dissipation chamber 6, the mounting frames are arranged to fix the water cooling boxes 9, the vibration force generated by the engine body 1 during operation is prevented from influencing the water cooling boxes 9, and through the arrangement of the connecting frames 13, the air guiding fan 14, the filter screen 15 and the air gathering hoppers 16, when the engine operates, the natural wind acts on the air guiding fan 14, thereby make aviation baffle 14 rotate and produce the air current, the cooperation through accessory plate 12 and filter screen 15 that sets up will produce the air current drainage to acting on water-cooling tank 9, because of the wind-force after the filtration does not contain impurity, can carry out more effectual heat dissipation to water-cooling tank 9, prevent that too much impurity from laminating on water-cooling tank 9, influence the operation of water-cooling tank 9, the equal fixed mounting in top of two accessory plates 12 has link 13, the one end of two link 13 all rotates with the one end of aviation baffle 14 to be connected, the position of two circulation grooves all corresponds with the position of aviation baffle 14, link 13's setting plays connection and supporting role to aviation baffle 14, two water-cooling tanks 9 are the symmetry setting, two water-cooling tanks 9 respectively with external power supply electric connection.
When the aviation connectionless engine with the rapid cooling structure is used, air flow is transmitted to drive the air guiding fan 14 to rotate when the aviation connectionless engine is used, the air guiding fan 14 rotates to increase wind power generation and concentration, the wind power enters the filter screen 15 through the auxiliary plate 12, impurities in air are filtered through the filter screen 15, the filtered wind power does not contain impurities, the water cooling tank 9 can be more effectively cooled, the situation that the excessive impurities are attached to the water cooling tank 9 to damage the outside of the water cooling tank 9 and contaminate the impurities is prevented, and the cooling efficiency is increased to a certain degree.
In the description of the present invention, it is to be understood that the indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings and are only for convenience in describing the present invention and simplifying the description, but are not intended to indicate or imply that the indicated devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the present invention.
In the present invention, unless otherwise explicitly specified or limited, for example, it may be fixedly attached, detachably attached, or integrated; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate agent, and may be used for communicating the inside of two elements or interacting relation of two elements, unless otherwise specifically defined, and the specific meaning of the terms in the present invention can be understood by those skilled in the art according to specific situations.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides an aviation is with no connecting rod engine with rapid cooling structure, includes engine body (1), its characterized in that: the engine body (1) comprises a gas compression bin (2) and a gas compressor (3), the outer wall of the engine body (1) is wrapped by a heat conduction plate (5), a plurality of heat conduction connecting pipes (7) are fixedly arranged on the outer wall of the heat conduction plate (5), the interiors of the heat conduction connecting pipes (7) comprise a heat absorption graphite filling layer (8) and an air circulation layer, a heat dissipation chamber (6) is arranged outside the gas compression bin (2), one ends of the heat conduction connecting pipes (7) are fixedly connected with the inner wall of the heat dissipation chamber (6), water cooling boxes (9) are symmetrically arranged on two sides of the heat dissipation chamber (6), two flow guide pipes (10) are fixedly penetrated through the tops of the two water cooling boxes (9), and two return pipes (11) are fixedly penetrated through the bottoms of the two water cooling boxes (9);
the front of the two sides of the heat dissipation chamber (6) is provided with auxiliary plates (12), the front of each of the auxiliary plates (12) is fixedly provided with an air guide fan (14), the front of each of the auxiliary plates (12) is provided with a circulation groove, the inner wall of each of the circulation grooves is fixedly clamped and connected with a filter screen (15), one end of each of the circulation grooves is fixedly connected with an air gathering hopper (16), and the positions of the air gathering hoppers (16) are identical to the positions of the adjacent water cooling tanks (9).
2. The aviation connecting-rod-free engine with the rapid cooling structure as claimed in claim 1, wherein: the gas compressor (3) is fixedly arranged inside the gas pressing bin (2), the gas pressing bin (2) is located on one side of the combustion chamber (4), and the gas pressing bin (2) is fixedly penetrated through the combustion chamber (4).
3. The aviation connectionless engine with the rapid cooling structure as claimed in claim 1, wherein: it is a plurality of the air circulation layer all is located the outer wall of heat absorption graphite filling layer (8), and is a plurality of discharge orifices have all been seted up to a plurality of air circulation layer.
4. The aviation connecting-rod-free engine with the rapid cooling structure as claimed in claim 1, wherein: one end of each of the two flow guide pipes (10) is fixedly penetrated through the top of the heat dissipation chamber (6), and one end of each of the two return pipes (11) is fixedly penetrated through the bottom of the heat dissipation chamber (6).
5. The aviation connecting-rod-free engine with the rapid cooling structure as claimed in claim 1, wherein: and the bottom ends of the two water cooling tanks (9) are fixedly provided with mounting racks, and one ends of the mounting racks are fixedly connected with the outer wall of the heat dissipation chamber (6).
6. The aviation connecting-rod-free engine with the rapid cooling structure as claimed in claim 1, wherein: the top ends of the two auxiliary plates (12) are fixedly provided with connecting frames (13), one ends of the two connecting frames (13) are rotatably connected with one ends of the air guiding fans (14), and the positions of the two circulation grooves correspond to the positions of the air guiding fans (14).
7. The aviation connecting-rod-free engine with the rapid cooling structure as claimed in claim 1, wherein: the two water cooling tanks (9) are symmetrically arranged, and the two water cooling tanks (9) are respectively electrically connected with an external power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220486172.4U CN216691269U (en) | 2022-03-08 | 2022-03-08 | Aviation is with no connecting rod engine with rapid cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220486172.4U CN216691269U (en) | 2022-03-08 | 2022-03-08 | Aviation is with no connecting rod engine with rapid cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216691269U true CN216691269U (en) | 2022-06-07 |
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ID=81828878
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220486172.4U Active CN216691269U (en) | 2022-03-08 | 2022-03-08 | Aviation is with no connecting rod engine with rapid cooling structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216691269U (en) |
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2022
- 2022-03-08 CN CN202220486172.4U patent/CN216691269U/en active Active
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