Compressor body rear cover sealing structure
By adding a barrier ring to the crankshaft of the compressor and adding an oil groove to the rear cover of the fuselage to form a multi-stage sealing system, the problem of poor sealing effect of traditional compressors is solved, and efficient lubricating oil management and long-term stable operation are achieved.
Patent Information
- Application Number
- CN202421685486.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-16
- Publication Date
- 2025-04-29
- Estimated Expiration
- 2034-07-16
AI Technical Summary
The sealing effect between the rear cover of the traditional reciprocating compressor and the crankshaft is discounted at high speeds, resulting in splashing and leaking of lubricant oil, causing unplanned downtime and economic losses to the equipment.
A sealing structure for the rear cover of the compressor fuselage is designed. By adding two barrier rings to the crankshaft and adding oil grooves to the rear cover of the fuselage, a multi-stage sealing system is formed to effectively prevent lubricating oil from splashing and leaking.
It realizes efficient lubricant sealing, reduces wear and replacement of shaft seals, ensures long-term stable operation of the compressor, reduces economic losses, and simplifies assembly accuracy requirements.
Smart Images
Figure CN222810920U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of compressors, in particular to a compressor body rear cover sealing structure. Background Art
[0002] With the increase in global energy consumption and the development of energy science and technology, higher and higher requirements are placed on reciprocating compressors. The rear cover of traditional reciprocating compressors is sealed with a crankshaft flange shield combined with a shaft seal, especially for high-speed compressors. High-speed, large-diameter crankshafts can increase the linear velocity of the outer edge of the crankshaft. The lubricating oil flowing out between the body bearing and the crankshaft, as the linear velocity of the outer edge of the crankshaft increases, the lubricating oil splashes violently, and the lubricating oil enters the gap between the crankshaft and the rear cover of the body. The shaft seal is required for sealing. Due to the high linear velocity of the outer edge of the crankshaft, the sealing effect of the shaft seal is discounted, and the wear is accelerated accordingly, which may cause oil leakage, resulting in unplanned equipment shutdown and economic losses. Utility Model Content
[0003] In view of the deficiencies in the prior art, the utility model provides a compressor body rear cover sealing structure, which solves the sealing problem between the compressor body rear cover and the crankshaft.
[0004] To achieve the above objectives, the utility model is implemented through the following technical solutions: a compressor body rear cover sealing structure, including a crankshaft and a body rear cover sleeved on the outside of the crankshaft, a shaft seal is provided between the body rear cover and the crankshaft, a flange is provided on the side wall of the crankshaft, a first oil groove is provided on the side close to the shaft seal in the body rear cover, a second oil groove is provided on the side away from the shaft seal, a second retaining ring is provided on the side close to the shaft seal on the side wall of the crankshaft, a first retaining ring is provided below the second oil groove and between the second retaining ring and the flange, and a groove is formed between the first retaining ring and the second retaining ring.
[0005] Preferably, a cover plate is detachably mounted on one side of the rear cover of the fuselage.
[0006] Preferably, the cover plate is connected to the rear cover of the body by screws.
[0007] Beneficial Effects
[0008] The utility model provides a compressor body rear cover sealing structure, which has the following beneficial effects:
[0009] By adding two retaining rings on the crankshaft and an oil groove on the rear cover of the machine body, a multi-stage sealing system is formed, which effectively prevents the splashing and leakage of lubricating oil under high-speed rotation and improves the sealing performance;
[0010] Through effective seal and lubricating oil management, the number of shaft seal replacements is reduced, ensuring long-term stable operation of the compressor and reducing economic losses caused by compressor downtime;
[0011] The assembly accuracy requirement of the rear cover of the fuselage is reduced, and it is easy to use. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 It is a structural schematic diagram of the utility model.
[0013] Figure 2 It is a schematic diagram of the prior art structure.
[0014] In the figure: 1. crankshaft; 2. rear cover of the body; 3. shaft seal; 4. cover plate; 5. screws; 6. flange; 7. first oil groove; 8. second oil groove; 9. second retaining ring; 10. first retaining ring. DETAILED DESCRIPTION
[0015] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0016] See also Figure 1 The utility model provides a technical solution: a sealing structure of a compressor body rear cover 2, comprising a crankshaft 1 and a body rear cover 2 sleeved on the outside of the crankshaft 1, a shaft seal 3 is arranged between the body rear cover 2 and the crankshaft 1, a flange 6 is arranged on the side wall of the crankshaft 1, a first oil groove 7 is arranged on the side close to the shaft seal 3 in the body rear cover 2, a second oil groove 8 is arranged on the side away from the shaft seal 3, a second retaining ring 9 is arranged on the side of the side wall of the crankshaft 1 close to the shaft seal 3, a first retaining ring 10 is arranged below the second oil groove 8 and between the second retaining ring 9 and the flange 6, and a groove is formed between the first retaining ring 10 and the second retaining ring 9.
[0017] This embodiment is further configured such that a cover plate 4 is detachably mounted on one side of the rear cover 2 of the body.
[0018] The present embodiment is further configured such that the cover plate 4 is connected to the body rear cover 2 via screws 5 .
[0019] By those skilled in the art, the components in this case are connected in sequence. The specific connection and operation sequence should refer to the following working principle. The detailed connection means are well-known technologies in the field. The following mainly introduces the working principle and process.
[0020] Example: Figure 1 As shown, the present invention adds two retaining rings on the crankshaft 1 and an oil groove on the rear cover 2 of the body. When the compressor is running normally, although the crankshaft 1 has a high speed and a large diameter, and the outer edge linear speed of the crankshaft 1 is large, the lubricating oil splashes violently. This lubricating oil sealing solution can be used to solve the problem:
[0021] The first seal allows a portion of the splashed lubricating oil to flow to the oil pool at the bottom of the fuselage through the second oil groove 8, and a portion of the lubricating oil moves toward the flange end of the crankshaft 1 through the gap between the second oil groove 8 and the crankshaft 1.
[0022] The second seal is that a first retaining ring 10 is arranged below the second oil groove 8 on the rear cover 2 of the fuselage, and is placed between the flange 6 of the crankshaft 1 and the second retaining ring 9. The lubricating oil passes through here and is blocked, and a small amount of the lubricating oil moves to the flange end.
[0023] The third seal forms a groove between the first retaining ring 10 and the second retaining ring 9, so that part of the lubricating oil can flow back and at the same time the lubricating oil can move toward the flange end to form an obstacle.
[0024] In the fourth seal, part of the lubricating oil flows to the oil pool at the bottom of the fuselage through the first oil groove 7, and part of the lubricating oil needs to move to the flange end through the gap between the second retaining ring 9 and the first oil groove 7.
[0025] The fifth seal is sealed by the shaft seal 3 on the crankshaft 1, so that the lubricating oil cannot leak and a higher sealing effect is achieved.
[0026] The use of this sealing structure is a method for solving the oil leakage between the rear cover 2 and the crankshaft 1, and has strong practicality.
[0027] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions. The sentence "includes an element defined by ... does not exclude the existence of other identical elements in the process, method, article or device including the element".
[0028] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A compressor body rear cover sealing structure, comprising a crankshaft (1) and a body rear cover (2) sleeved on the outside of the crankshaft (1), a shaft seal (3) being arranged between the body rear cover (2) and the crankshaft (1), and a flange (6) being arranged on the side wall of the crankshaft (1), characterized in that: A first oil groove (7) is provided on a side of the rear cover (2) close to the shaft seal (3), and a second oil groove (8) is provided on a side away from the shaft seal (3). A second retaining ring (9) is provided on a side of the crankshaft (1) close to the shaft seal (3). A first retaining ring (10) is provided below the second oil groove (8) and between the second retaining ring (9) and the flange (6), and a groove is formed between the first retaining ring (10) and the second retaining ring (9).
2. A compressor body rear cover sealing structure according to claim 1, characterized in that: A cover plate (4) is detachably mounted on one side of the rear cover (2) of the body.
3. A compressor body rear cover sealing structure according to claim 2, characterized in that: The cover plate (4) is connected to the rear cover (2) of the body via screws (5).