Integrated compressor body structure

Abstract

The utility model relates to the field of compressors, and discloses an integrated compressor body structure which comprises a body, a base is connected to the outer side of the body in a sliding mode, a plurality of sliding grooves are formed in the base, a plurality of clamping grooves are formed in the base, and a fixing assembly is arranged in the base. A heat dissipation assembly is arranged at the top of the machine body, the fixing assembly comprises a rotating rod, the outer side of the rotating rod is rotatably connected to the interior of the machine body, two winding wheels are fixedly connected to the outer side of the rotating rod, two pull ropes are fixedly connected to the outer sides of the two winding wheels, and baffles are fixedly connected to the ends, away from the winding wheels, of the pull ropes. The outer side of the pull rope is sleeved with a spring. According to the compressor, through mutual cooperation of the rotating rod, the pull rope, the spring, the baffle, the inserting block and other structures, the functions of rapid, convenient and stable assembly and disassembly between the machine body and the base are achieved, and the maintenance operation convenience and efficiency of the compressor are effectively improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of compressor, especially to a kind of integrated compressor fuselage structure. BACKGROUND

[0002] Compressor is an important mechanical equipment. It improves the pressure of gas by compression, and is widely used in refrigeration, air conditioning, industrial production and many other fields. Its working principle is various, such as piston type relying on piston reciprocating motion compression, screw type relying on screw rotation extrusion. It can provide power for system, promote gas flow, refrigeration and heating, or help industrial process to proceed smoothly.

[0003] At present, most of the compressor shell and base are fixed by using bolts, which requires a large number of auxiliary tools during operation, resulting in time-consuming and laborious fixing and dismounting process, thereby increasing the difficulty of compressor maintenance and the work burden of users.

[0004] In view of the above problems, an integrated compressor fuselage structure is proposed to solve the above problems. INVENTION CONTENTS

[0005] In order to make up for the above shortcomings, the utility model provides an integrated compressor fuselage structure, which aims to improve the problem that most of the compressor shell and base are fixed by using bolts in the prior art, which requires a large number of auxiliary tools during operation, resulting in time-consuming and laborious fixing and dismounting process, thereby increasing the difficulty of compressor maintenance and the work burden of users.

[0006] In order to achieve the above purpose, the utility model adopts the following technical scheme: an integrated compressor fuselage structure, comprising a fuselage main body, a base is slidably connected to the outer side of the fuselage main body, a plurality of sliding grooves are formed in the inside of the base, a plurality of clamping grooves are formed in the inside of the base, a fixing assembly is arranged in the inside of the base, and a heat dissipation assembly is arranged on the top of the fuselage main body.

[0007] The fixing assembly comprises a rotating rod, the rotating rod is rotatably connected to the inside of the fuselage main body, two winding wheels are fixedly connected to the outer side of the rotating rod, two pull ropes are fixedly connected to the outer side of each of the two winding wheels, a baffle is fixedly connected to the end of the pull rope away from the winding wheel, a spring is sleeved on the outer side of the pull rope, and a plug-in block is fixedly connected to the outer side of the baffle.

[0008] As a further description of the above technical scheme:

[0009] The heat dissipation assembly comprises a heat absorbing plate, the heat absorbing plate is fixedly connected to the top of the fuselage main body, a plurality of heat dissipation fins are fixedly connected to the top of the heat absorbing plate, a connecting frame is fixedly connected to the outer side of the heat absorbing plate, and a plurality of heat dissipation fans are fixedly connected to the inside of the connecting frame.

[0010] As a further description of the above technical solutions:

[0011] The bottom of the connecting frame is fixedly connected to the top of the main body.

[0012] As a further description of the above technical solutions:

[0013] The plug-in block is slidably connected to the outside of the base, and the plug-in block is plugged into the inside of the main body.

[0014] As a further description of the above technical solutions:

[0015] One end of the spring is fixedly connected to the outside of the baffle, and the other end of the spring is fixedly connected to the inner wall of the sliding groove.

[0016] As a further description of the above technical solutions:

[0017] The rotating block is fixedly connected to the outside of the rotating rod.

[0018] As a further description of the above technical solutions:

[0019] The baffle is slidably connected to the inside of the sliding groove, and two winding grooves are formed in the inside of the base.

[0020] As a further description of the above technical solutions:

[0021] The pull rope is slidably connected to the inside of the base.

[0022] The utility model has the following beneficial effects:

[0023] 1、 in the utility model, the pull rope is released by rotating the rotating rod, the spring pushes the baffle, and then the plug-in block is inserted into the clamping groove and the inside of the main body to complete the fixation; when disassembly is needed, the rotating rod is reversely rotated to wind the pull rope, the baffle drives the spring to compress, so that the plug-in block exits the clamping groove and the inside of the main body, and the fixation is released, realizing the quick, convenient and stable assembly and disassembly function between the main body and the base, and effectively improving the compressor maintenance operation convenience and efficiency.

[0024] 2、 in the utility model, the heat absorption plate absorbs the heat generated when the main body operates, and then the heat is dissipated to the surrounding air through the heat dissipation fins, and the air convection is further enhanced by the heat dissipation fan, realizing efficient and stable heat dissipation effect, effectively controlling the temperature of the main body within a reasonable range, avoiding a series of problems such as performance degradation of parts, deterioration of lubricating oil, deformation of mechanical structure and the like caused by overheating. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1A first perspective view of the integrated compressor fuselage structure is provided in the utility model.

[0026] Figure 2 A second perspective view of the integrated compressor fuselage structure is provided in the utility model.

[0027] Figure 3 A structure diagram of the clamping groove of the integrated compressor fuselage structure is provided in the utility model.

[0028] Figure 4 A structure diagram of the winding wheel of the integrated compressor fuselage structure is provided in the utility model

[0029] Figure 5 A structure diagram of the heat absorption plate of the integrated compressor fuselage structure is provided in the utility model.

[0030] Legend:

[0031] 1, fuselage main body; 2, base; 3, clamping groove; 4, rotating block; 5, rotating rod; 6, winding wheel; 7, pull rope; 8, spring; 9, baffle; 10, plug-in block; 11, winding groove; 12, sliding groove; 13, connecting frame; 14, heat dissipation fan; 15, heat absorption plate; 16, heat dissipation fin. Specific implementation

[0032] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0033] Reference Figure 1 - Figure 5 An embodiment provided by the utility model: an integrated compressor fuselage structure, comprising a fuselage main body 1, the outer side of the fuselage main body 1 is slidably connected with a base 2, a plurality of sliding grooves 12 are formed in the base 2, a plurality of clamping grooves 3 are formed in the base 2, a fixing assembly is arranged in the base 2, and a heat dissipation assembly is arranged at the top of the fuselage main body 1.

[0034] The fixing assembly comprises a rotating rod 5, the rotating rod 5 is rotatably connected to the inside of the fuselage main body 1, two winding wheels 6 are fixedly connected to the outside of the rotating rod 5, two pull ropes 7 are fixedly connected to the outside of each of the two winding wheels 6, a baffle 9 is fixedly connected to the end of the pull rope 7 away from the winding wheel 6, a spring 8 is sleeved on the outside of the pull rope 7, and a plug-in block 10 is fixedly connected to the outside of the baffle 9.

[0035] Specifically, the main body 1 is the core structure part of the integrated compressor, used to accommodate and support the main working components of the compressor, such as the cylinder, the crankshaft, etc., to provide a stable space and structural foundation for the process of compressing gas. The base 2 is used to provide a mounting foundation and support platform for the main body 1, and the multiple sliding grooves 12 opened in the inside of the base 2 are to provide a guide rail for the sliding of the baffle 9, ensuring that the baffle 9 can move linearly stably under the action of the pull rope 7 and the spring 8. The multiple clamping grooves 3 are to cooperate with the plug-in block 10, so as to realize the stable connection or separation between the main body 1 and the base 2, to meet the needs of the compressor in different scenarios such as installation, maintenance, disassembly, etc. The heat dissipation assembly is to ensure that the compressor body structure operates within a suitable temperature range, avoiding overheating and causing faults, and providing protection for the normal operation and long-term stable work of the compressor. The rotating rod 5 in the fixing assembly is to serve as the hub of power transmission, and by manually rotating the rotating rod 5, the two winding wheels 6 fixedly connected to the outside of the rotating rod 5 can be driven to rotate. The winding wheels 6 are to wind or release the pull rope 7. The pull rope 7 is to connect the winding wheels 6 and the baffle 9, realizing force transmission. When the pull rope 7 is released, the spring 8 is to use its elastic potential energy to push the baffle 9 to slide along the sliding groove 12. The baffle 9 is to drive the plug-in block 10 fixedly connected to the outside to move, so that the plug-in block 10 is inserted into the clamping groove 3 and the inside of the main body 1 to complete the fixation, or when the pull rope 7 is wound, the plug-in block 10 is driven to exit the clamping groove 3 and the inside of the main body 1 to release the fixation.

[0036] Referring to Figure 1 and Figure 5 , the heat dissipation assembly includes a heat absorption plate 15 fixedly connected to the top of the main body 1, a plurality of heat dissipation fins 16 fixedly connected to the top of the heat absorption plate 15, a connecting frame 13 fixedly connected to the outside of the heat absorption plate 15, and a plurality of heat dissipation fans 14 fixedly connected in the connecting frame 13.

[0037] Specifically, the heat absorption plate 15 is to absorb the heat generated by the main body 1 during operation, and conduct the heat through good thermal conductivity. The multiple heat dissipation fins 16 are to increase the contact area with air, so as to dissipate the heat conducted by the heat absorption plate 15 to the surrounding air. The connecting frame 13 is to fix and support the heat dissipation fans 14. The heat dissipation fans 14 are to accelerate the flow of air, further enhancing the convection of air, thereby improving the heat dissipation efficiency of the entire heat dissipation assembly.

[0038] Referring to Figure 1 - Figure 5The bottom of the connecting frame 13 is fixedly connected to the top of the fuselage body 1, the outer side of the insertion block 10 is slidably connected to the inside of the base 2, the outer side of the insertion block 10 is inserted into the inside of the fuselage body 1, one end of the spring 8 is fixedly connected to the outer side of the baffle 9, the other end of the spring 8 is fixedly connected to the inner wall of the sliding groove 12, the outer side of the rotating rod 5 is fixedly connected with the rotating block 4, the outer side of the baffle 9 is slidably connected to the inside of the sliding groove 12, two winding grooves 11 are formed in the inside of the base 2, and the outer side of the pull rope 7 is slidably connected to the inside of the base 2.

[0039] Specifically, the bottom of the connecting frame 13 is fixedly connected to the top of the fuselage body 1, which is to provide a stable and reliable mounting position for the cooling fan 14 and ensure that the cooling fan 14 does not shake or displace during operation due to unstable structure, thereby ensuring that it can effectively cool the fuselage body 1, the outer side of the insertion block 10 is slidably connected to the inside of the base 2, which is to enable the insertion block 10 to move accurately and smoothly in the path defined by the base 2 under the action of the pull rope 7 and the spring 8, so as to accurately insert and cooperate with the clamping groove 3 and the inside of the fuselage body 1, realize the switching of the connection state between the fuselage body 1 and the base 2, the outer side of the insertion block 10 is inserted into the inside of the fuselage body 1, which is to enhance the stability and integrity of the connection between the fuselage body 1 and the base 2, prevent the fuselage body 1 from shaking, displacing or detaching relative to the base 2 during operation due to external force, and ensure the stability and reliability of the overall structure of the compressor, the spring 8 is to store elastic potential energy and release elastic force when the pull rope 7 is released, push the baffle 9 to slide along the sliding groove 12, thereby driving the insertion block 10 to complete the connection action with the clamping groove 3 and the inside of the fuselage body 1, and at the same time provide a reverse resistance when the pull rope 7 is wound, so that the operation of the entire fixing assembly has a certain buffer and controllability, the rotating block 4 is to provide an easy force application site for the operator, so that the operator can more easily and conveniently rotate the rotating rod 5, the outer side of the baffle 9 is slidably connected to the inside of the sliding groove 12, which is to limit the movement trajectory of the baffle 9 under the synergistic action of the pull rope 7 and the spring 8, so that it can only slide linearly along the sliding groove 12, thereby ensuring that the insertion block 10 connected with the baffle 9 can be accurately inserted into or withdrawn from the clamping groove 3 and the inside of the fuselage body 1, making the operation of the fixing assembly more reliable and accurate, the winding groove 11 is to provide a containing space for the pull rope 7 during winding, avoid interference or winding of the pull rope 7 with other parts inside the base 2 when winding, and ensure that the pull rope 7 can be smoothly wound on the winding wheel 6, thereby ensuring the normal operation of the fixing assembly, and the outer side of the pull rope 7 is slidably connected to the inside of the base 2, which is to enable the pull rope 7 to move smoothly in a specific channel or space inside the base 2 during winding or releasing, reduce the friction resistance between the pull rope 7 and the base 2, prevent the pull rope 7 from being damaged or jammed due to friction, and ensure the effective control of the fixing assembly on the connection state of the fuselage body 1 and the base 2.

[0040] Working principle: when the main body 1 needs to be fixed on the base 2, the pull rope 7 is released by rotating the rotating rod 5, the spring 8 pushes the baffle 9, and then the plug-in block 10 is inserted into the card slot 3 and the inside of the main body 1 to complete the fixing; when disassembling, reverse rotation of the rotating rod 5 winds the pull rope 7, drives the baffle 9 to compress the spring 8, so that the plug-in block 10 exits the card slot 3 and the inside of the main body 1, and the fixing is released;

[0041] The heat generated by the main body 1 during operation is absorbed by the heat absorption plate 15, and then the heat is dissipated to the surrounding air through the heat dissipation fin 16, and the heat dissipation fan 14 further enhances the convection of air, thereby improving the heat dissipation efficiency, ensuring that the compressor body structure operates within a suitable temperature range, reducing the risk of failure caused by overheating, prolonging the service life of the compressor and maintaining its good working performance.

[0042] Finally, it should be noted that: the above only for the preferred embodiments of the present application, and not for limiting the present application, although the present application has been described in detail with reference to the foregoing embodiments, for those skilled in the art, it still can be modified to the technical solutions recorded in the foregoing embodiments, or equivalent replacement of some technical features, any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application, should be included in the protection scope of the present application.

Claims

1. An integrated compressor housing structure comprising a housing main body (1), characterized by: The fuselage body (1) outside slide connection has base (2), the base (2) inside is equipped with multiple sliding slots (12), the base (2) inside is equipped with multiple clamping grooves (3), the base (2) inside is provided with fixed assembly, the fuselage body (1) top is provided with heat dissipation assembly; The fixed assembly includes a rotating rod (5), the rotating rod (5) is rotatably connected to the inside of the fuselage body (1), the rotating rod (5) is fixedly connected with two winding wheels (6) outside, two winding wheels (6) are fixedly connected with two pull ropes (7) outside, the pull rope (7) is fixedly connected with a baffle (9) away from one end of the winding wheel (6), the pull rope (7) is provided with a spring (8) outside, the baffle (9) is fixedly connected with a plug-in block (10) outside.

2. An integrated compressor housing structure according to claim 1, characterized in that: The heat dissipation assembly includes a heat absorbing plate (15), the heat absorbing plate (15) is fixedly connected to the top of the fuselage body (1) outside, the heat absorbing plate (15) is fixedly connected with multiple cooling fins (16) on the top, the heat absorbing plate (15) is fixedly connected with a connecting frame (13) outside, the connecting frame (13) is fixedly connected with multiple cooling fans (14) inside.

3. An integrated compressor housing structure as set forth in claim 2 wherein: The connecting frame (13) is fixedly connected to the top of the fuselage body (1) on the bottom.

4. The integrated compressor airframe structure of claim 1, wherein: The plug-in block (10) is slidably connected to the inside of the base (2) outside, and the plug-in block (10) is inserted into the inside of the fuselage body (1) outside.

5. The integrated compressor airframe structure of claim 1, wherein: One end of the spring (8) is fixedly connected to the outside of the baffle (9), and the other end of the spring (8) is fixedly connected to the inner wall of the sliding slot (12).

6. An integrated compressor airframe structure as set forth in claim 1, characterized by: The rotating rod (5) is fixedly connected with a rotating block (4) outside.

7. The integrated compressor airframe structure of claim 1, wherein: The baffle (9) is slidably connected to the inside of the sliding slot (12) outside, and the base (2) is provided with two winding grooves (11) inside.

8. The integrated compressor airframe structure of claim 1, wherein: The pull rope (7) is slidably connected to the inside of the base (2) outside.

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