CN218439678U - Compressor heat radiation structure - Google Patents
Compressor heat radiation structure Download PDFInfo
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- CN218439678U CN218439678U CN202221467406.7U CN202221467406U CN218439678U CN 218439678 U CN218439678 U CN 218439678U CN 202221467406 U CN202221467406 U CN 202221467406U CN 218439678 U CN218439678 U CN 218439678U
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Abstract
The utility model discloses a compressor heat radiation structure, include: the front shell, the middle shell and the rear shell, the front shell and the rear shell respectively block two ends of the middle shell to form an air inlet cavity, an air exhaust cavity is formed in the front shell, one or more fins are arranged in the air inlet cavity, one end of the air inlet cavity is connected with an air inlet, the other end of the air inlet cavity is connected with an air outlet, the channel is divided into a plurality of flow channels by the one or more fins, the air inlet is connected with the middle shell and an external space, the air outlet is connected with the middle shell and the front shell, one surface of the rear shell, which is back to the middle shell, is provided with a core power device mounting area, and at least one part of an area corresponding to the core power device mounting area is covered on the other surface of the rear shell by the areas where the plurality of flow channels flow. The utility model discloses use the refrigerant to get into the runner, take place heat exchange with the backshell, take away the heat that casing core power device produced behind one's back to reduce the temperature of whole controller, improve compressor life, avoid the controller impaired.
Description
Technical Field
The utility model relates to a heat radiation structure's technical field especially relates to a compressor heat radiation structure.
Background
The compressor controller integrates various heating elements, the overall temperature is higher, heat dissipation is carried out only by a conventional shell heat conduction mode, the heat dissipation performance is low, the service life of the compressor is easily influenced, and meanwhile the controller can be damaged.
The prior art for heat dissipation of a compressor at present comprises:
CN213419299U: the utility model is characterized in that the installation part of the aluminum shell for installing the IGBT component is provided with a mounting groove for accommodating the heat pipe, and the mounting groove extends to the edge of the aluminum shell; thus, heat generated during the operation of the IGBT module is transferred to the outer periphery of the aluminum case through the heat pipe. Simultaneously, the periphery wall that the mounting groove extends to the edge of aluminium system casing connects a plurality of heat radiation fins to improve the heat conduction and radiating efficiency of aluminium system casing, and then avoid the IGBT subassembly because of the radiating effect poor condition that the high temperature appears.
CN214617019U: the utility model discloses a through increased a baffle in bottom department, the guide condensing agent flow direction for in the condensing agent that gets into from the induction port can enter into the bearing of bearing frame through the baffle, rethread heat conduction silicone grease transmits to PCB controller department, plays quick radiating effect, has promoted scroll compressor's life. The baffle is in a spiral fin shape, and conducts guiding polymerization on the condensing agent, so that the efficiency of the condensing agent entering the bearing seat is improved.
However, the CN213419299U structure utilizes the heat pipe to directly transfer the heat of the IGBT to the housing, and then achieves the heat dissipation effect through the external fins. In the utility model, the medium mainly used for cooling is still the ambient temperature around the compressor, and the heat dissipation effect is limited; in addition, the utility model discloses a structure is more complicated, and the installation requirement of heat pipe is than higher, and in addition, the cooperation requirement of heat pipe and casing is also than higher, need have sufficient contact just can realize the efficient heat transfer.
Scheme CN214617019U structure utilizes helical structure's fin-shaped baffle, enters into the bearing of bearing frame with the condensing agent direction in to improve the thermal diffusivity, this utility model mainly dispels the heat in gathering the condensing agent to the bearing frame, if the core generates heat the unit and does not distribute in the central part, then this utility model will be more limited to the radiating effect of controller. In addition, this utility model's baffle is independent structure, and can be than higher with the installation cooperation requirement of bottom.
SUMMERY OF THE UTILITY MODEL
In view of this, an object of the present invention is to provide a heat dissipation structure for a compressor.
In order to realize the purpose, the utility model discloses the technical scheme who takes does:
a heat dissipation structure of a compressor, comprising:
the front shell and the rear shell are respectively blocked at two ends of the middle shell to form an air inlet cavity, an air outlet cavity is formed in the front shell, one or more fins are arranged in the air inlet cavity, one end of the air inlet cavity is connected with an air inlet, the other end of the air inlet cavity is connected with an air outlet, the air inlet passes through the cavity to the air outlet to form a channel, the channel is divided into a plurality of flow channels by the one or more fins, the air inlet is connected with the middle shell and an external space, the air outlet is connected with the middle shell and the front shell, the rear shell is back to one side of the middle shell, a core power device mounting area is arranged on one side of the middle shell, and a plurality of flow channel flowing areas are covered on the other side of the rear shell at least one part of the corresponding area of the core power device mounting area.
In the above compressor heat dissipation structure, one end of the fin is close to the air inlet, and one end of the fin is bent towards the direction of the air inlet.
In the above heat dissipation structure for the compressor, the fins are streamline, and the curvature of at least one part of the fins is consistent with the curvature of the inner wall of the air intake cavity adjacent to the fins.
In the heat dissipation structure of the compressor, the front shell is provided with an exhaust passage, and the exhaust passage is connected with the exhaust cavity and the external space.
In the above heat dissipation structure of the compressor, a bearing seat is further disposed in the middle shell, one or more fins are disposed around the bearing seat in a semi-enclosed manner, and a channel is formed between the bearing seat and the fin closest to the bearing seat.
In the above heat dissipation structure of the compressor, a channel is formed between the inner wall of the air inlet cavity and the fin closest to the air inlet cavity.
The above-mentioned compressor heat radiation structure, wherein, satisfy following relation:
h/w≤3.5
w(max)/w(min)≤2
n≥2
wherein: h is the height of the fin;
w is the width of any of the flow channels;
w (max) is the width of the widest of the plurality of flow channels;
w (min) is the width of the narrowest of the plurality of flow channels;
n is the number of the fins, and n is an integer.
The above-mentioned compressor heat radiation structure, wherein, satisfy following relation:
10mm≤h≤20mm；
1mm≤t≤3mm
wherein: h is the height of the fin;
and t is the thickness of the fin.
The utility model discloses owing to adopted above-mentioned technique, make it compare the positive effect that has with prior art and be:
(1) The utility model mainly radiates the core power device of the controller; according to the layout structure and the range of the core power device, a curved fin structure with a certain height and a certain layout rule is additionally arranged at the bottom of the rear shell to form a plurality of flow channels, and a refrigerant enters the flow channels to exchange heat with the rear shell to take away heat generated by the core power device behind the shell, so that the temperature of the whole controller is reduced, the service life of the compressor is prolonged, and the controller is prevented from being damaged.
(2) The utility model discloses a runner that the fin formed not only can increase the heat flux on back shell surface, promotes the thermal diffusivity, can also improve the torrent phenomenon of refrigerant in the cavity, reduces the energy consumption, improves the performance.
Drawings
Fig. 1 is a schematic view of a middle shell and a rear shell of a frame diagram of a heat dissipation structure of a compressor according to the present invention.
Fig. 2 is a schematic diagram of a half-sectional view of a frame diagram of a heat dissipation structure of a compressor according to the present invention.
Fig. 3 is a schematic view of a structure of fins of a frame diagram of a heat dissipation structure of a compressor according to the present invention.
Fig. 4 is a schematic view of a rear shell portion of a frame diagram of a heat dissipation structure of a compressor according to the present invention.
Fig. 5 is a schematic cross-sectional view of fins of a frame diagram of a heat dissipation structure of a compressor according to the present invention.
In the drawings: 1. a middle shell; 2. a front housing; 3. a rear housing; 11. an air inlet; 12. a fin; 13. a bearing seat; 21. an exhaust passage; 31. a core power device mounting area.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but not to limit the present invention, and fig. 1 is a schematic view of the middle shell part and the axle side of the rear shell of the frame diagram of the heat dissipation structure of the compressor of the present invention; fig. 2 is a schematic view of a half-sectional view of a frame diagram of a heat dissipation structure of a compressor according to the present invention; fig. 3 is a schematic view of a structure of a fin of a frame diagram of a heat dissipation structure of a compressor according to the present invention; fig. 4 is a schematic view of a rear shell portion of a frame diagram of a heat dissipation structure of a compressor according to the present invention; fig. 5 is a schematic cross-sectional view of fins of a frame diagram of a heat dissipation structure of a compressor of the present invention, and as shown in fig. 1 to 5, a heat dissipation structure of a compressor according to a preferred embodiment is shown, including: preceding shell 2, mesochite 1 and backshell 3, preceding shell 2 and backshell 3 block up the both ends of mesochite 1 respectively and form the chamber of admitting air, form the exhaust chamber in the preceding shell 2, the intracavity is equipped with one or more fin 12 of admitting air, an air inlet 11 is connected to the one end of the chamber of admitting air, an air outlet is connected to the other end of the chamber of admitting air, form a passageway through cavity to air outlet from air inlet 11, one or more fin 12 divide the passageway into a plurality of runners, shell 1 and exterior space in the air inlet 11 connection, mesochite 1 and preceding shell 2 are connected to the air outlet, backshell 3 is equipped with core power device installation area 31 on the one side of mesochite 1 mutually, the area that a plurality of runners flow through covers at least a part of the corresponding region of core power device installation area 31 on the another side of backshell 3.
In a preferred embodiment, the rear casing 3 includes a covering casing and a rear cover plate, the rear casing forms a closable accommodating space, the core power device is disposed in the accommodating space, and a fin 12 is connected to an end surface of the casing opposite to the rear cover plate.
As shown in fig. 3 and 4, the area covered by the plurality of flow paths on one side of the rear case 3 corresponds to a part or all of the core power device mounting area 31 on the other side of the rear case 3.
In a preferred embodiment, one end of the fin 12 is disposed near the air inlet 11, and one end of the fin 12 is bent in a direction in which the air inlet 11 is located.
In a preferred embodiment, the fins 12 are streamlined, and the curvature of at least a part of the fins 12 is identical to the curvature of the inner wall of the air intake chamber adjacent to the fins.
In a preferred embodiment, the fins 12 are attached to the rear housing 3.
In a preferred embodiment, the refrigerant is discharged from the air inlet 11 through the middle shell 1 and the air outlet to the exhaust channel 21, during which the refrigerant exchanges heat with the rear shell 3 in the flow channel, and the rear shell 3 absorbs a large amount of heat dissipated from the core power device mounting area 31, so as to reduce the temperature of the whole controller, prolong the service life of the compressor, and avoid the controller from being damaged.
Specifically, the flow channel formed by the fins 12 can not only increase the heat flux on the surface of the rear shell 3 and improve the heat dissipation, but also improve the turbulence phenomenon of the refrigerant in the cavity, reduce the energy consumption and improve the performance.
In a preferred embodiment, the front case 2 is provided with an exhaust passage 21, and the exhaust passage 21 connects the exhaust chamber and the external space.
The above are merely preferred embodiments of the present invention, and the embodiments and the protection scope of the present invention are not limited thereby.
The utility model discloses still have following embodiment on above-mentioned basis:
in a further embodiment of the present invention, a bearing seat 13 is further disposed in the middle casing 1, one or more fins 12 are disposed around the bearing seat 13 in a semi-enclosed manner, and a channel is formed between the bearing seat 13 and a fin 12 closest to the bearing seat 13.
Specifically, the fins 12 are designed to have an unclosed arc structure or an opened arc structure in a front view in fig. 3 to avoid the air inlet and the air outlet.
Further, the fin 12 may be circular arc-shaped, or wave-shaped, and has a tendency of circular arc direction, and it extends in the circumferential direction around a certain point, and may have any shape or have any concave-convex within its range, but the fin 12 is necessarily unclosed and open, and has an opening for avoiding the air inlet and the air outlet.
By semi-enclosed in this application is meant that the fins 12 are disposed around the bearing housing 13 in an unclosed state.
In a preferred embodiment, referring to fig. 3, the fins 12 form a circular arc around the bearing seat 13; because the limiting fins 12 of the air inlet 11 and the air outlet cannot form a complete circle, the air inlet cavity is circular, the bearing seat 13 and the air inlet cavity are concentrically arranged, and each fin 12 is on a circle concentric with the bearing seat 13 and the air inlet cavity.
In a further embodiment of the present invention, a channel is formed between the inner wall of the inlet chamber and a fin 12 closest thereto.
In a further embodiment of the present invention, the following relationship is satisfied:
h/w≤3.5
w(max)/w(min)≤2
n≥2
wherein: h is the height of the fins 12;
w is the width of any flow channel;
w (max) is the width of the widest runner in the plurality of runners;
w (min) is the width of the narrowest runner of the plurality of runners;
n is the number of fins 12 and n is an integer.
Specifically, the plurality of w may be the same or different, and the density may be adjusted according to the arrangement of the core power devices;
a further h/w of less than or equal to 3.5 means that the ratio of the height of each fin 12 to the width of the flow channel on the two adjacent sides must be less than or equal to 3.5 to ensure the feasibility of the processing.
In a further embodiment of the present invention, the following relationship is satisfied:
10mm≤h≤20mm；
1mm≤t≤3mm
wherein: h is the height of the fins 12;
t is the thickness of the fin 12.
Specifically, the height h of each fin 12 may be the same or different, but the fin tops are at the same plane height. If the fins are too high, the structural strength is influenced; if the fins are too low, heat dissipation is not satisfactory.
Furthermore, the thickness t of each fin 2 is the same, and if the fin is too thin, the structural strength is affected, and the heat dissipation capability is limited; the fins are too thick, which affects the size of the width w of the flow channel, affects the heat flux, and cannot satisfy the lightweight.
The above is only a preferred embodiment of the present invention, and not intended to limit the scope of the invention, and it should be appreciated by those skilled in the art that various equivalent substitutions and obvious changes made in the specification and drawings should be included within the scope of the present invention.
Claims (8)
1. A heat dissipation structure for a compressor, comprising:
the front shell, the middle shell and the rear shell are respectively blocked, the two ends of the middle shell form an air inlet cavity, an air outlet cavity is formed in the front shell, one or more fins are arranged in the air inlet cavity, one end of the air inlet cavity is connected with an air inlet, the other end of the air inlet cavity is connected with an air outlet, the air inlet passes through a cavity and reaches the air outlet to form a channel, one or more fins divide the channel into a plurality of flow channels, the air inlet is connected with the middle shell and an external space, the air outlet is connected with the middle shell and the front shell, the rear shell is back of the middle shell, one side of the middle shell is provided with a core power device installation area, and the flow channel flowing area is covered with at least one part of the corresponding area of the core power device installation area on the other side of the rear shell.
2. The heat dissipating structure of a compressor as claimed in claim 1, wherein one end of the fin is disposed near the air inlet, and one end of the fin is bent in a direction of the air inlet.
3. A heat dissipating structure for a compressor as claimed in claim 2, wherein the fins are streamlined, and at least a part of the fins have a curvature corresponding to a curvature of an inner wall of the intake chamber adjacent thereto.
4. The heat dissipating structure of a compressor as claimed in claim 1, wherein the front casing has a discharge passage connecting the discharge chamber and an external space.
5. A heat dissipating structure for a compressor as claimed in claim 3, wherein a bearing seat is further provided in the middle casing, one or more of the fins are disposed around the bearing seat in a semi-enclosed manner, and a passage is formed between the bearing seat and a fin closest thereto.
6. A heat dissipating structure for a compressor as claimed in claim 5, wherein a passage is formed between an inner wall of said intake chamber and a fin located closest thereto.
7. A heat dissipating structure of a compressor in accordance with claim 6,
the following relationships are satisfied:
h/w≤3.5
w(max)/w(min)≤2
n≥2
wherein: h is the height of the fin;
w is the width of any of the flow channels;
w (max) is the width of the widest of the plurality of flow channels;
w (min) is the width of the narrowest of the plurality of flow channels;
n is the number of the fins, and n is an integer.
8. The heat dissipating structure of a compressor as set forth in claim 7,
the following relationships are satisfied:
10mm≤h≤20mm；
1mm≤t≤3mm
wherein: h is the height of the fin;
and t is the thickness of the fin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221467406.7U CN218439678U (en) | 2022-06-13 | 2022-06-13 | Compressor heat radiation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221467406.7U CN218439678U (en) | 2022-06-13 | 2022-06-13 | Compressor heat radiation structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218439678U true CN218439678U (en) | 2023-02-03 |
Family
ID=85077757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221467406.7U Active CN218439678U (en) | 2022-06-13 | 2022-06-13 | Compressor heat radiation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218439678U (en) |
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2022
- 2022-06-13 CN CN202221467406.7U patent/CN218439678U/en active Active
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