Compressor heat dissipation structure

Abstract

The application discloses a compressor heat dissipation structure, comprising: a front shell, a middle shell and a 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 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, a channel is formed from the air inlet to the air outlet through the cavity, the 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, a core power device mounting area is arranged on the side of the rear shell opposite to the middle shell, and the areas through which the plurality of flow channels flow cover at least part of the corresponding areas of the core power device mounting area on the other side of the rear shell.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of heat dissipation structure, and in particular to a compressor heat dissipation structure. BACKGROUND

[0002] The compressor controller integrates multiple heat generating elements, and the overall temperature is relatively high. The heat dissipation performance is low by relying on the conventional shell heat conduction mode for heat dissipation, which easily affects the service life of the compressor and may cause damage to the controller.

[0003] The existing technologies for compressor heat dissipation currently include:

[0004] CN213419299U: The application discloses a heat dissipation structure of an IGBT assembly, which comprises an aluminum shell, an IGBT assembly, a heat pipe and a plurality of heat dissipation fins.

[0005] CN214617019U: The application discloses a heat dissipation structure of a scroll compressor, which comprises a bottom cover, a baffle, a bearing seat, a heat-conducting silicone grease and a PCB controller.

[0006] However, the structure of scheme CN213419299U utilizes a heat pipe to directly transfer the heat of the IGBT to the shell, and then achieves heat dissipation through external fins. In the application, the main medium for cooling is still the ambient temperature around the compressor, and the heat dissipation effect is limited. In addition, the structure of the application is relatively complex, the installation requirements of the heat pipe are relatively high, and in addition, the cooperation requirements of the heat pipe and the shell are also relatively high, and sufficient contact is required to achieve efficient heat transfer.

[0007] The structure of scheme CN214617019U utilizes a spiral fin-shaped baffle to guide the condensate into the bearing of the bearing seat, thereby improving the heat dissipation. The application mainly collects the condensate in the bearing seat for heat dissipation, and if the core heat generating element is not arranged in the center part, the heat dissipation effect of the application on the controller will be limited. In addition, the baffle of the application is an independent structure, and the installation and cooperation requirements with the bottom cover will be relatively high. SUMMARY

[0008] Therefore, the present application aims to provide a compressor heat dissipation structure.

[0009] To achieve the above-mentioned purpose, the present application adopts the following technical solution:

[0010] A compressor heat dissipation structure, comprising:

[0011] A front shell, a middle shell and a 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 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, a channel is formed from the air inlet to the air outlet through the air inlet cavity, the one or more fins divide the channel into several 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, a core power device mounting area is arranged on a side of the rear shell opposite to the middle shell, and the flow channels pass through at least a part of the core power device mounting area on the other side of the rear shell.

[0012] The compressor heat dissipation structure described above, wherein one end of the fin is arranged close to the air inlet, and one end of the fin is bent towards the direction of the air inlet.

[0013] The compressor heat dissipation structure described above, wherein the fin is streamline-shaped, and the bending radius of at least a part of the fin is consistent with the bending radius of the inner wall of the air inlet cavity adjacent to the fin.

[0014] The compressor heat dissipation structure described above, wherein an air outlet channel is arranged on the front shell, and the air outlet channel is connected with the air outlet cavity and an external space.

[0015] The compressor heat dissipation structure described above, wherein a bearing seat is further arranged in the middle shell, and one or more fins are arranged around the bearing seat in a semi-enclosed manner, and a flow channel is formed between the bearing seat and the fin closest to the bearing seat.

[0016] The compressor heat dissipation structure described above, wherein a flow channel is formed between the inner wall of the air inlet cavity and the fin closest to the air inlet cavity.

[0017] The compressor heat dissipation structure described above, wherein the following relationships are satisfied:

[0018] h / w≤3.5

[0019] w(max) / w(min)≤2

[0020] n≥2

[0021] Wherein: h is the height of the fin.

[0022] w is the width of any of the flow channels;

[0023] w(max) is the width of the widest of the flow channels;

[0024] w(min) is the width of the narrowest of the flow channels;

[0025] n is the number of fins, and n is an integer.

[0026] The compressor heat dissipation structure described above, wherein the following relationships are satisfied:

[0027] 10mm≤h≤20mm;

[0028] 1mm≤ t≤3mm

[0029] wherein: h is the height of the fin;

[0030] t is the thickness of the fin.

[0031] The compressor heat dissipation structure described above, wherein the following relationships are satisfied:

[0032] The present application focuses on the core power device of the controller for heat dissipation; according to the layout structure and range of the core power device, a certain height and layout rule of the curved fin structure is added to the bottom of the rear shell, multiple flow channels are formed, the refrigerant enters the flow channel, exchanges heat with the rear shell, and carries away the heat generated by the core power device behind the shell, thereby reducing the temperature of the entire controller, improving the service life of the compressor, and avoiding damage to the controller.

[0033] The flow channel formed by the fin not only increases the heat flux of the surface of the rear shell and improves the heat dissipation, but also improves the turbulent flow phenomenon of the refrigerant in the cavity, reduces the energy consumption, and improves the performance. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 is a partial view of the middle shell and the rear shell of the frame diagram of the compressor heat dissipation structure of the present application.

[0035] Figure 2 is a schematic view of the half cross-sectional view of the frame diagram of the compressor heat dissipation structure of the present application.

[0036] Figure 3 is a schematic view of the fin structure of the frame diagram of the compressor heat dissipation structure of the present application.

[0037] Figure 4 is a schematic view of the rear shell part of the frame diagram of the compressor heat dissipation structure of the present application.

[0038] Figure 5is a schematic view of a cross section of the fin of the frame diagram of the compressor heat dissipation structure of the present application.

[0039] In the drawing: 1, middle shell; 2, front shell; 3, rear shell; 11, air inlet; 12, fin; 13, bearing seat; 21, exhaust passage; 31, core power device mounting area. DETAILED DESCRIPTION

[0040] The present application will be further described below in conjunction with the drawing and specific embodiments, but not as a limitation of the present application, Figure 1 is a schematic view of the middle shell part of the frame diagram of the compressor heat dissipation structure of the present application and the rear shell isometric view; Figure 2 is a schematic view of the half cross section of the frame diagram of the compressor heat dissipation structure of the present application; Figure 3 is a schematic view of the structure of the fin of the frame diagram of the compressor heat dissipation structure of the present application; Figure 4 is a schematic view of the rear shell part of the frame diagram of the compressor heat dissipation structure of the present application; Figure 5 is a schematic view of the cross section of the fin of the frame diagram of the compressor heat dissipation structure of the present application, see Figures 1 to 5 As shown in the drawing, a compressor heat dissipation structure of a preferred embodiment comprises: a front shell 2, a middle shell 1 and a rear shell 3, the front shell 2 and the rear shell 3 respectively seal the two ends of the middle shell 1 to form an air inlet cavity, an exhaust cavity is formed in the front shell 2, one or more fins 12 are arranged in the air inlet cavity, one end of the air inlet cavity is connected with an air inlet 11, the other end of the air inlet cavity is connected with an air outlet, a channel is formed from the air inlet 11 to the air outlet through the air inlet cavity, the one or more fins 12 divide the channel into several flow channels, the air inlet 11 is connected with the middle shell 1 and the outside space, the air outlet is connected with the middle shell 1 and the front shell 2, the rear shell 3 is provided with a core power device mounting area 31 on the side opposite to the middle shell 1, the area through which the several flow channels flow covers at least part of the corresponding area of the core power device mounting area 31 on the other side of the rear shell 3.

[0041] In a preferred embodiment, the rear shell 3 comprises a shell body and a rear cover plate, the rear shell forms a closable accommodation space, the core power device is arranged in the accommodation space, and the shell body is connected with the fin 12 on the end surface opposite to the rear cover plate.

[0042] As shown in the drawing, Figure 3 and Figure 4 the area through which the several flow channels flow on one side of the rear shell 3 covers part or all of the core power device mounting area 31 on the other side of the rear shell 3.

[0043] In a preferred embodiment, one end of the fin 12 is arranged close to the air inlet 11, and one end of the fin 12 is bent towards the direction in which the air inlet 11 is located.

[0044] In a preferred embodiment, the fins 12 are streamlined, and the curved arc of at least a portion of the fins 12 is consistent with the curved arc of the inner wall of the air inlet cavity adjacent thereto.

[0045] In a preferred embodiment, the fins 12 are connected to the rear shell 3.

[0046] In a preferred embodiment, the present application uses the refrigerant to flow from the air inlet 11 through the middle shell 1, the air outlet, and to the exhaust passage 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 emitted by the core power device installation area 31, thereby reducing the temperature of the entire controller, improving the service life of the compressor, and avoiding damage to the controller.

[0047] Specifically, the flow channel formed by the fins 12 not only increases the heat flux of the surface of the rear shell 3 and improves the heat dissipation, but also improves the turbulent flow phenomenon of the refrigerant in the cavity, reduces energy consumption, and improves performance.

[0048] In a preferred embodiment, the front shell 2 is provided with an exhaust passage 21, and the exhaust passage 21 connects the exhaust cavity and the external space.

[0049] The above is only a preferred embodiment of the present application, and does not limit the implementation and protection scope of the present application.

[0050] The present application has the following embodiments on the basis of the above:

[0051] In a further embodiment of the present application, the middle shell 1 is further provided with a bearing seat 13, and one or more fins 12 are arranged in a semi-enclosed manner around the bearing seat 13, and a flow channel is formed between the bearing seat 13 and the fin 12 closest thereto.

[0052] Specifically, the fins 12 are designed to be in an open arc structure in the front view, so as to avoid the air inlet and the air outlet. Figure 3 The fins 12 are in an open arc structure in the front view, so as to avoid the air inlet and the air outlet.

[0053] Further, the fins 12 can be circular arc-shaped, or wavy and have a trend of circular arc direction, which extends in the circumferential direction around a certain point, and can be any shape or have any concave-convex in its range, but the fins 12 must be open and not closed, and have an opening to avoid the air inlet and the air outlet.

[0054] The semi-enclosure of the present application means that the fins 12 are arranged around the bearing seat 13 and are in an open state.

[0055] In a preferred embodiment, referring to Figure 3As shown, the fin 12 forms an arc with the bearing seat 13 as the center; due to the limitation of the air inlet 11 and the air outlet, the fin 12 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.

[0056] In a further embodiment of the present application, a flow channel is formed between the inner wall of the air inlet cavity and the fin 12 closest to it.

[0057] In a further embodiment of the present application, the following relationship is satisfied:

[0058] h / w≤3.5

[0059] w(max) / w(min)≤2

[0060] n≥2

[0061] Wherein: h is the height of the fin 12;

[0062] w is the width of any flow channel;

[0063] w(max) is the width of the widest flow channel among the flow channels;

[0064] w(min) is the width of the narrowest flow channel among the flow channels;

[0065] n is the number of fins 12, and n is an integer.

[0066] Specifically, the plurality of w can be the same or different, and can be adjusted in density according to the arrangement of the core power device;

[0067] Further, h / w≤3.5 can mean that the ratio of the height of each fin 12 to the width of the flow channel on both sides must be less than or equal to 3.5, in order to ensure the feasibility of the process.

[0068] In a further embodiment of the present application, the following relationship is satisfied:

[0069] 10mm≤h≤20mm;

[0070] 1mm≤ t≤3mm

[0071] Wherein: h is the height of the fin 12;

[0072] t is the thickness of the fin 12.

[0073] Specifically, the height h of each fin 12 can be the same or different, but the top of the fin is at the same height. If the fin is too high, the structural strength will be affected; if the fin is too low, the heat dissipation will not be ideal.

[0074] Further, the thickness t of each fin 2 is the same, if the fin is too thin, the structural strength is affected, and the heat dissipation capacity is limited; if the fin is too thick, the size of the width w of the flow channel is affected, the heat flow flux is affected, and the lightweight cannot be met.

[0075] The above merely describes the preferred embodiments of the present application, and is not intended to limit the embodiments and protection scope of the present application. It should be noted by those skilled in the art that any equivalent replacement and obvious changes made according to the content of the present application should be included in the protection scope of the present application.

Claims

1. A compressor heat dissipation structure, characterized in that, include: The enclosure comprises a front shell, a middle shell, and a rear shell. The front shell and the rear shell respectively seal both ends of the middle shell to form an air intake chamber. An exhaust chamber is formed inside the front shell. One or more fins are provided in the air intake chamber. One end of the air intake chamber is connected to an air inlet, and the other end of the air intake chamber is connected to an air outlet. A channel is formed from the air inlet, through the air intake chamber, to the air outlet. One or more fins divide the channel into several flow channels. The air inlet connects the middle shell and the external space. The air outlet connects the middle shell and the front shell. A core power device mounting area is provided on the side of the rear shell opposite to the middle shell. The areas through which the several flow channels flow cover at least a portion of the corresponding area of ​​the core power device mounting area on the other side of the rear shell. The tops of the fins are at the same height in the same plane; The rear shell includes a covered shell and a rear cover plate. The rear shell forms a sealable accommodating space, in which the core power device is disposed. Fins are connected to the end face of the shell opposite to the rear cover plate. The inner shell is also provided with a bearing seat, and one or more of the fins are arranged around the bearing seat in a semi-enclosed form, and a flow channel is formed between the bearing seat and the fin closest to it. A flow channel is formed between the inner wall of the air intake chamber and the fin closest to it; The following relationship must be satisfied: h / w≤3.5 w(max) / w(min)≤2 n≥2 Where: h is the height of the fin; w is the width of any of the aforementioned channels; w(max) is the width of the widest of the several flow channels; w(min) is the width of the narrowest of the several flow channels; n is the number of fins, and n is an integer; The following relationship must be satisfied: 10mm≤h≤20mm; 1mm≤t≤3mm Where: h is the height of the fin; t is the thickness of the fin.

2. The compressor heat dissipation structure according to claim 1, characterized in that, One end of the fin is positioned close to the air inlet, and the other end of the fin is bent in the direction of the air inlet.

3. A compressor heat dissipation structure according to claim 2, characterized in that, The fins are streamlined, and the curvature of at least a portion of the fins is consistent with the curvature of the inner wall of the adjacent air intake cavity.

4. A compressor heat dissipation structure according to claim 1, characterized in that, The front shell is provided with an exhaust channel, which connects the exhaust chamber and the external space.

Images