Cooling structure and air compressor

Abstract

The application discloses a cooling structure and an air compressor, and relates to the technical field of air compressors, in particular to a cooling structure for cooling a thrust disc of an air compressor, which comprises a bleed air channel, a first cooler and a cooling gas supply channel, the bleed air channel is configured to be connected with a first stage outlet of the compressor, the first cooler is connected downstream of the bleed air channel, and the cooling gas supply channel is connected between an outlet of the first cooler and a cooling area of the thrust disc. According to the application, high-pressure gas is led out from the first stage outlet through the bleed air channel, the high-pressure gas is used to overcome high flow resistance, and it is ensured that the gas can smoothly enter the thrust disc area, then the first cooler is used to cool the gas, low-temperature cooling medium is provided, the cooling gas supply channel is used to directly deliver the cold gas to the cooling area of the thrust disc, and the thrust disc is forcibly cooled, so that the temperature rise of the thrust disc is effectively reduced, and the operation stability is improved.

Description

Technical Field

[0001] This invention relates to the field of compressor technology, and in particular to a cooling structure and an air compressor. Background Technology

[0002] Air-suspension centrifugal air compressors are widely used in industrial fields, offering advantages such as oil-free operation and high efficiency. However, during actual operation, the extremely small working clearance between the thrust disc and the air suspension bearing generates a large amount of frictional heat during high-speed rotation, causing a significant increase in the thrust disc temperature and directly affecting the compressor's operational stability. Existing cooling solutions mostly employ external cooling systems, but due to the high flow resistance in the thrust disc area, cooling gas cannot effectively pass through the tiny gap, resulting in low cooling efficiency. Meanwhile, some solutions that use internal compressor gas cooling have limited cooling effects due to the high gas temperature, failing to effectively control the thrust disc temperature rise. Summary of the Invention

[0003] The embodiments of the present invention provide a cooling structure and an air compressor, which solves the technical problem that the thrust disc cannot effectively pass through the tiny gap due to insufficient cooling gas pressure.

[0004] To address the aforementioned problems, according to one aspect of this application, an embodiment of the present invention provides a cooling structure for cooling the thrust disc of an air compressor. The cooling structure includes an air intake passage, a first cooler, and a cooling gas supply passage. The air intake passage is configured to connect to a first-stage outlet of the compressor. The first cooler is connected downstream of the air intake passage. The cooling gas supply passage is connected between the outlet of the first cooler and the cooling area of ​​the thrust disc.

[0005] In some embodiments, the cooling structure further includes a second cooler and a return gas passage, the second cooler being configured to receive gas from the thrust disk cooling region, and the return gas passage being configured to connect the outlet of the second cooler to the first stage inlet of the compressor.

[0006] In some embodiments, the induced draft channel, the first cooler, the cooling gas supply channel, the second cooler, and the return gas channel constitute a closed-loop cooling system.

[0007] In some embodiments, the first stage outlet is the first stage volute outlet, and the air intake channel is connected to the first stage volute outlet.

[0008] In some embodiments, the cooling gas supply channel includes a heat dissipation end cover, which has an air inlet and an air outlet. The air inlet is connected to the outlet of the first cooler, and the air outlet is connected to the cooling area of ​​the thrust plate.

[0009] In some embodiments, the diameter of the air inlet and air outlet is 4-8 mm, the number is 1-3, and they are symmetrically arranged on the heat dissipation end cover.

[0010] In some embodiments, the cooling gas supply channel further includes a bearing housing, and an annular airflow channel for reducing gas flow resistance is formed between the heat dissipation end cap and the bearing housing.

[0011] In some embodiments, the thrust disk is mounted on a short shaft, and the cooling area of ​​the thrust disk includes the thrust disk and an axial bearing that mates with the bearing housing.

[0012] In some embodiments, the thrust disc and the short shaft are assembled by an interference fit and are axially fixed by a lock nut.

[0013] In some embodiments, the cooling gas supply channel further includes a bearing cover and a retaining ring, the axial bearing is disposed between the bearing housing and the bearing cover, and the retaining ring is disposed between the bearing housing and the bearing cover to create an installation space and introduce cooling gas.

[0014] In some embodiments, the retaining ring is a circular ring structure with multiple evenly distributed protrusions on both sides. The thickness of the protrusions is 0.8-1.2 mm and the central angle is 15°-25°.

[0015] In some embodiments, the first cooler and the second cooler are integrated into a dual-channel cooling module. The dual-channel cooling module has an independent first cooling channel and a second cooling channel. The first cooling channel is used to cool the gas from the bleed air channel, and the second cooling channel is used to cool the gas from the thrust disk cooling area.

[0016] According to another aspect of this application, an embodiment of the present invention provides an air compressor, the air compressor including a compression structure and the cooling structure described above, the compression structure having a first stage outlet and a first stage inlet, the bleed air passage of the cooling structure being connected to the first stage outlet, and the return air passage of the cooling structure being connected to the first stage inlet.

[0017] Compared with the prior art, the cooling structure of the present invention has at least the following beneficial effects: The present invention provides a cooling structure for cooling the thrust plate of an air compressor. The cooling structure includes an air intake channel, a first cooler, and a cooling gas supply channel. The air intake channel is configured to connect to the first stage outlet of the compressor. The first cooler is connected downstream of the air intake channel. The cooling gas supply channel is connected between the outlet of the first cooler and the cooling area of ​​the thrust plate.

[0018] This invention draws high-pressure gas from the first-stage outlet through an air intake channel. The high-pressure gas overcomes the high flow resistance, ensuring that the gas can smoothly enter the thrust disk area. Then, the first cooler cools the gas and provides a low-temperature cooling medium. The cooling gas supply channel directly delivers the cold gas to the cooling area of ​​the thrust disk, forcibly cooling the thrust disk, thereby effectively reducing its temperature rise and improving operational stability.

[0019] The air compressor provided by the present invention is designed based on the above-described cooling structure, and its beneficial effects are the same as those of the above-described cooling structure, which will not be repeated here.

[0020] The above description is merely an overview of the technical solution of the present invention. In order to better understand the technical means of the present invention and to implement it in accordance with the contents of the specification, the preferred embodiments of the present invention are described in detail below with reference to the accompanying drawings. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0022] Figure 1 A schematic diagram of a cooling structure provided in an embodiment of the present invention; Figure 2 An exploded view of a cooling structure provided in an embodiment of the present invention; Figure 3 A cross-sectional view of a cooling structure provided in an embodiment of the present invention; Figure 4 This is a cross-sectional view of a heat dissipation end cap in a cooling structure provided in an embodiment of the present invention; Figure 5 An exploded view of the layout of a cooling structure provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the thrust disk in a cooling structure provided by an embodiment of the present invention; Figure 7 A diagram showing the fit between the heat dissipation end cap and the bearing housing in a cooling structure according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the retaining ring in a cooling structure provided by an embodiment of the present invention; Figure 9 A cross-sectional view of the engagement between a thrust disk and an axial bearing in a cooling structure provided in an embodiment of the present invention; Figure 10A cooling flow diagram of a cooling structure provided in an embodiment of the present invention; Figure label explanation: 1. Cooling structure; 11. Air intake channel; 12. First cooler; 13. Cooling gas supply channel; 14. Second cooler; 15. Return gas channel; 131. Heat dissipation end cover; 132. Bearing housing; 133. Snap ring; 134. Bearing cover plate; 1311. Air inlet; 1312. Air outlet; 1331. Boss; 2. Thrust plate; 21. Short shaft; 22. Locking nut; 23. Axial bearing; 3. Compression structure; 31. First stage outlet; 32. First stage inlet. Detailed Implementation

[0023] To further illustrate the technical means and effects adopted by the present invention to achieve the intended purpose, the specific embodiments, structures, features, and effects according to the present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments. In the following description, different "an embodiment" or "an embodiment" do not necessarily refer to the same embodiment. Furthermore, specific features, structures, or characteristics in one or more embodiments can be combined in any suitable form.

[0024] In the description of this invention, it should be clearly stated that the terms "first," "second," etc., in the specification, claims, and accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence; the terms "vertical," "lateral," "longitudinal," "front," "rear," "left," "right," "up," "down," "horizontal," etc., indicate orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, and are merely for the convenience of describing this invention, and do not mean that the device or element referred to must have a specific orientation or position, and therefore should not be construed as a limitation of this invention.

[0025] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0026] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0027] Example 1 This embodiment provides a cooling structure, such as Figures 1-9As shown, the cooling structure 1 is used to cool the thrust plate 2 of the air compressor. The cooling structure 1 includes an air intake channel 11, a first cooler 12, and a cooling gas supply channel 13. The air intake channel 11 is configured to connect to the first stage outlet of the compressor. The first cooler 12 is connected downstream of the air intake channel 11. The cooling gas supply channel 13 is connected between the outlet of the first cooler 12 and the cooling area of ​​the thrust plate 2.

[0028] The bleed air passage 11 starts at the first stage outlet of the compressor, i.e., the first stage volute outlet, and is used to draw out the compressed high-pressure gas. The downstream of the bleed air passage 11 is directly connected to the inlet of the first cooler 12, which cools the drawn-out gas. The cooling gas supply passage 13 is connected to the outlet of the first cooler 12 and delivers the cooled gas to the cooling area of ​​the thrust plate 2. More specifically, the cooling gas supply passage 13 includes components such as pipes and heat dissipation end caps to ensure that the gas can flow directly to the gap between the thrust plate 2 and the axial bearing, thereby forming a continuous airflow path from the first stage outlet to the cooling area of ​​the thrust plate.

[0029] The function of the bleed gas passage 11 is to draw high-pressure gas from the first stage outlet of the compressor. Due to the high gas pressure at the first stage outlet, it can effectively overcome the high flow resistance in the thrust disk area and ensure that the gas passes through smoothly. The function of the first cooler 12 is to cool the drawn high-pressure gas, reduce its temperature, and thus enhance the heat dissipation capacity of the cooling gas. The function of the cooling gas supply passage 13 is to guide the cooled gas to the cooling area of ​​the thrust disk 2, force-cool the thrust disk 2, absorb the heat generated by its friction, and thus reduce the operating temperature of the thrust disk 2.

[0030] After high-pressure gas is drawn out from the first-stage outlet through the bleed gas channel 11, the gas enters the first cooler 12 for cooling treatment, and then is delivered to the cooling area of ​​the thrust disk 2 through the cooling gas supply channel 13. More specifically, the cooling gas flows directly into the tiny gap between the thrust disk 2 and the axial bearing, where it absorbs the frictional heat generated by the high-speed rotation of the thrust disk 2 and reduces the temperature of the thrust disk 2 through convection heat transfer, thereby achieving efficient heat transfer and cooling effect.

[0031] In the background technology, the thrust disk 2 generates a large amount of frictional heat during high-speed rotation due to the extremely small clearance between it and the air suspension bearing, resulting in excessive temperature rise and affecting operational stability and lifespan. Existing cooling solutions have low cooling efficiency because the flow resistance in the thrust disk area is large, making it difficult for cooling gas to pass through effectively. In this embodiment, high-pressure gas is drawn from the first-stage outlet through the air intake channel 11. The high-pressure gas overcomes the high flow resistance, ensuring that the gas can smoothly enter the thrust disk area. Then, the first cooler 12 cools the gas and provides a low-temperature cooling medium. The cooling gas supply channel 13 directly delivers the cold gas to the cooling area of ​​the thrust disk 2, forcibly cooling the thrust disk 2, thereby effectively reducing its temperature rise and improving operational stability.

[0032] In a specific embodiment, such as Figure 1 As shown, the cooling structure 1 also includes a second cooler 14 and a return gas passage 15. The second cooler 14 is configured to receive gas from the cooling area of ​​the thrust disk 2, and the return gas passage 15 is configured to connect the outlet of the second cooler 14 to the first stage inlet of the compressor.

[0033] The second cooler 14 directly receives the gas flowing out of the cooling area of ​​the thrust plate 2. After the gas completes the cooling of the thrust plate 2, the temperature of the gas rises and then enters the second cooler 14 for secondary cooling. The return gas passage 15 is connected to the outlet of the second cooler 14 and transports the gas that has undergone secondary cooling back to the first stage inlet of the compressor. More specifically, the return gas passage 15 is a pipe that extends from the second cooler 14 to the first stage inlet, ensuring that the gas can flow back smoothly into the compression cycle, thereby forming a continuous airflow path from the thrust plate area to the first stage inlet.

[0034] The main function of the second cooler 14 is to perform secondary cooling on the gas flowing out of the cooling area of ​​the thrust plate 2. This is because the temperature of the gas rises after absorbing heat from the thrust plate 2. The cooling process of the second cooler 14 can reduce the temperature of the gas and prepare it for subsequent circulation. The function of the return gas channel 15 is to reintroduce the cooled gas into the first stage inlet of the compressor, so that the gas can participate in the next round of compression process, thereby realizing the recycling of gas, avoiding energy waste, and improving the overall efficiency of the system.

[0035] The second cooler 14 is connected to the cooling area of ​​the thrust plate 2, receiving the heated gas flowing out from there. At the same time, the return gas channel 15 is connected to the first-stage inlet, sending the processed gas back to the compression system. This combination, together with the bleed gas channel 11, the first cooler 12, and the cooling gas supply channel 13, forms a complete gas circulation cooling chain. More specifically, the gas is drawn out from the first-stage outlet, cooled by the first cooler 12, then cooled by the cooling gas supply channel 13, and then flows into the second cooler 14 for further cooling. Finally, it returns to the first-stage inlet via the return gas channel 15. This combination can effectively achieve a closed-loop gas circulation, reduce the external cooling demand, reduce the temperature rise of the thrust plate 2, improve operational stability, and save energy through gas reuse, thereby improving the overall energy efficiency of the compressor.

[0036] In a specific embodiment, such as Figure 1 As shown, the air intake channel 11, the first cooler 12, the cooling gas supply channel 13, the second cooler 14, and the return air channel 15 constitute a closed-loop cooling system.

[0037] The closed-loop cooling system refers to the process where high-pressure gas is drawn from the first-stage outlet of the compressor via the bleed channel 11, flows sequentially through the first cooler 12 for initial cooling, and then is delivered to the cooling area of ​​the thrust plate 2 via the cooling gas supply channel 13 to absorb heat. Subsequently, the gas flows out of the thrust plate 2 and enters the second cooler 14 for secondary cooling. Finally, the gas, after secondary cooling, is drawn back to the first-stage inlet of the compressor via the return gas channel 15, thus forming a continuous and closed gas flow loop. This loop ensures that the gas is circulated within the system and not discharged into the external environment. Each component is tightly connected: the bleed channel 11 provides the high-pressure gas source; the first cooler 12 and the second cooler 14 are responsible for cooling the gas at different stages; the cooling gas supply channel 13 precisely guides the cold gas into the heating area; and the return gas channel 15 returns the processed gas to the starting point of the compression cycle.

[0038] This closed-loop design produces significant results. It effectively utilizes the compressor's own high-pressure gas through internal gas circulation to overcome the high flow resistance in the thrust plate 2 area, ensuring that cooling gas can continuously pass through the tiny gaps, thereby achieving efficient cooling of the thrust plate 2 and reducing its operating temperature. Since the gas is recycled, energy waste is avoided, dependence on external cooling systems is reduced, and the overall system's energy efficiency and operational stability are improved. At the same time, continuous cooling controls the temperature rise of the thrust plate 2, extending the equipment's service life.

[0039] In a specific embodiment, the first-stage outlet is the first-stage volute outlet, and the air intake channel 11 is connected to the first-stage volute outlet.

[0040] The first-stage outlet is specifically the first-stage volute outlet, and the bleed air passage 11 is directly connected to this first-stage volute outlet. This means that during compressor operation, the starting point of the bleed air passage 11 is set at the volute section after the first compression is completed, so that gas can be directly drawn from the high-pressure area. More specifically, the first-stage volute outlet is a key location for the accumulation and discharge of gas after compression by the impeller inside the compressor. The gas here has a high pressure level because it has just completed the compression process. The bleed air passage 11 is connected to this outlet through a pipe to ensure that the high-pressure gas can be successfully extracted and introduced into the subsequent cooling process.

[0041] This design achieves the following effects: the high-pressure gas at the outlet of the first-stage volute provides sufficient power to overcome the high flow resistance caused by the tiny gap between the thrust plate 2 and the bearing, thus ensuring that the cooling gas can continuously and in large quantities flow through the cooling area of ​​the thrust plate 2, achieving effective forced cooling of the thrust plate 2; furthermore, using high-pressure gas as the source of cooling medium not only increases the flow rate and velocity of the cooling gas and enhances the heat exchange efficiency, but also directly reduces the operating temperature of the thrust plate 2, reducing the temperature rise caused by frictional heat, thereby improving the operating stability and reliability of the compressor. At the same time, it avoids the defects of insufficient cooling due to high flow resistance in traditional cooling methods, ensuring the efficient operation of the entire cooling system.

[0042] In a specific embodiment, such as Figures 2-4 As shown, the cooling gas supply channel 13 includes a heat dissipation end cover 131. The heat dissipation end cover 131 is provided with an air inlet 1311 and an air outlet 1312. The air inlet 1311 is connected to the outlet of the first cooler 12, and the air outlet 1312 is connected to the cooling area of ​​the thrust plate 2. The air inlet 1311 and the air outlet 1312 can be round holes, square holes, or other types of through holes.

[0043] The heat dissipation end cover 131, as a key component of the cooling gas supply channel 13, has an air inlet 1311 and an air outlet 1312 inside. These holes are arranged symmetrically on the heat dissipation end cover 131 to ensure the balance of gas flow. More specifically, the air inlet 1311 is directly connected to the outlet of the first cooler 12 and is responsible for receiving the gas that has undergone initial cooling, while the air outlet 1312 opens towards the cooling area of ​​the thrust plate 2 to guide the gas to the small gap between the thrust plate 2 and the axial bearing. In terms of position, the air inlet 1311... The air inlet 11 and the air outlet 1312 are usually located on opposite sides of the heat dissipation end cover 131, forming a straight or ring-shaped path, so that the gas can flow into the heat dissipation end cover 131 from the air inlet 1311 and then flow out evenly from the air outlet 1312. The main function of the air inlet 1311 is to serve as the inlet of cooling gas, ensuring that the high-pressure low-temperature gas can smoothly enter the heat dissipation end cover 131. The function of the air outlet 1312 is to accurately spray the gas onto the hot spot area of ​​the thrust plate 2, so as to achieve direct forced cooling of the thrust plate 2 and thus effectively absorb the heat generated by friction.

[0044] The air inlet 1311 is connected to the outlet of the first cooler 12 to receive cooled gas, while the air outlet 1312 is aligned with the cooling area of ​​the thrust plate 2, allowing the gas to directly act on the surface of the thrust plate 2. After the gas is drawn out from the air intake channel 11 and cooled by the first cooler 12, it enters the heat dissipation end cover 131 through the air inlet 1311 and then flows out at high speed from the air outlet 1312, impacting the gap between the thrust plate 2 and the bearing for efficient heat exchange. This combination, along with the air intake channel 11 and the first cooler 12, forms a continuous airflow path, ensuring that the cooling gas can continuously cover the heat-generating parts of the thrust plate 2. This reduces the operating temperature of the thrust plate 2, reduces thermal deformation and wear caused by high temperature, thereby improving the stability and service life of the compressor. At the same time, due to the optimization of the gas flow path, the cooling efficiency is improved, energy loss is avoided, and the overall system reliability is enhanced.

[0045] In a specific embodiment, the diameter of the air inlet 1311 and the air outlet 1312 is 4-8mm, the number is 1-3, and they are symmetrically arranged on the heat dissipation end cover 131.

[0046] The diameter of the air inlet 1311 and the air outlet 1312 is limited to between 4 mm and 8 mm, and the number of each is between 1 and 3. These holes are arranged symmetrically on the heat dissipation end cover 131. This design ensures the balance and stability of the gas flow.

[0047] More specifically, the selection of the aperture range is based on considerations of gas dynamics and heat exchange efficiency. The size of 4 mm to 8 mm can ensure sufficient cooling gas flow through the holes without increasing flow resistance or causing insufficient flow due to excessively large or small apertures. At the same time, the number is controlled between 1 and 3 to avoid problems such as overly complex structure or uneven gas distribution. The symmetrical arrangement allows the gas to flow in evenly from the air inlet 1311 and out from the air outlet 1312, thereby forming a stable airflow coverage in the cooling area of ​​the thrust plate 2.

[0048] This embodiment firstly optimizes the flow path of the cooling gas, reducing energy loss when the gas passes through the heat dissipation end cover 131, ensuring that high-pressure gas can efficiently enter the tiny gap between the thrust plate 2 and the bearing. Secondly, the symmetrical and appropriately sized hole design enhances the uniformity of cooling, preventing local overheating of the thrust plate 2, thereby effectively reducing its overall operating temperature and reducing temperature rise caused by frictional heat. Furthermore, this arrangement improves the reliability and efficiency of the cooling system, avoiding insufficient cooling caused by high flow resistance in traditional cooling methods, and ultimately extending the service life of the thrust plate 2 and improving the operating stability of the compressor.

[0049] In a specific embodiment, such as Figure 2 and Figure 3 As shown, the cooling gas supply channel 13 also includes a bearing seat 132, and an annular airflow channel for reducing gas flow resistance is formed between the heat dissipation end cover 131 and the bearing seat 132.

[0050] When cooling gas enters through the air inlet 1311, it doesn't rush directly to the air outlet 1312. Instead, a portion of the airflow, or the main airflow path, first enters and fills the annular space formed by the inner wall of the heat dissipation end cover 131 and the outer wall of the bearing housing 132. This annular airflow channel essentially widens the gas flow path, providing a low-resistance transition area. This allows the cooling gas from the first cooler 12 to be buffered and evenly distributed here before being more smoothly guided to the thrust plate 2 area that ultimately needs cooling. This design reduces the flow resistance of the gas before it reaches the heat-generating components. Lower flow resistance means that, under the same bleed pressure, a larger flow rate of cooling gas can be smoothly delivered through the entire system, thereby enhancing the heat exchange capacity between the cooling medium and the high-temperature thrust plate 2. Furthermore, the smooth gas flow also reduces the energy loss that might be required to drive the gas circulation, thus improving the energy efficiency of the entire cooling process.

[0051] In a specific embodiment, such as Figure 2 and Figure 3As shown, the thrust disk 2 is mounted on a short shaft 21, and the cooling area of ​​the thrust disk 2 includes the thrust disk 2 and an axial bearing 23 that mates with the bearing housing 132.

[0052] The thrust plate 2 is fixedly mounted on the short shaft 21. This mounting method typically involves an interference fit to ensure stability under high-speed rotation. The cooling zone is defined to include not only the thrust plate 2 itself but also the axial bearing 23, which is tightly fitted to the bearing housing 132. This means that the critical area requiring heat dissipation is the minute gap between the thrust plate 2 and its corresponding axial bearing 23, as well as their contact surfaces. More specifically, the thrust plate 2 uses the short shaft 21 as its rotational carrier, while the axial bearing 23 is fixed to the bearing housing 132. The two move relative to each other at extremely close distances, thus becoming the main source of frictional heat. Covering the thrust plate 2 and the axial bearing 23 with the cooling zone ensures that the cooling gas can act simultaneously on these two core heat-generating components, directly removing the heat generated by their high-speed relative motion. This design, through targeted cooling, guides the gas to the areas most in need of heat dissipation, effectively reducing the operating temperature of the thrust plate 2 and the axial bearing 23, minimizing the risk of material expansion or deformation due to overheating, thereby maintaining the precise gap between them and ensuring the smooth operation of the compressor.

[0053] In a specific embodiment, the thrust disk 2 and the short shaft 21 are assembled by an interference fit and are axially fixed by a locking nut 22.

[0054] The thrust plate 2 is assembled on the short shaft 21 by an interference fit. This means that the inner diameter of the thrust plate 2 is designed to be slightly smaller than the mating shaft diameter of the short shaft 21, thereby generating a certain clamping force during assembly to ensure that the two are tightly joined in the radial direction and cannot rotate relative to each other. On this basis, a lock nut 22 is used to thread with the short shaft 21 to press and position the thrust plate 2 in the axial direction to prevent any displacement of it in the axial direction. This double-fixed mechanical structure produces very important effects. First, the interference fit ensures that the thrust plate 2 and the short shaft 21 have extremely high coaxiality and connection rigidity when rotating at high speed, effectively avoiding vibration caused by imbalance or looseness, and laying the foundation for the smooth operation of the compressor. Second, the axial constraint provided by the locking nut 22 ensures that the position of the thrust plate 2 remains fixed when bearing working load, maintaining the stability of the crucial small gap between it and the adjacent axial bearing 23. Furthermore, this stable connection not only improves the reliability of mechanical operation, but also indirectly benefits thermal management, because good contact helps heat to be conducted from the thrust plate 2 to the short shaft 21. Combined with active cooling gas circulation, this keeps the operating temperature of the thrust plate 2 within a safe range, thereby significantly reducing the risk of failure due to thermal deformation or mechanical failure.

[0055] In a specific embodiment, such as Figure 2 and Figure 3 As shown, the cooling gas supply channel 13 also includes a bearing cover plate 134 and a retaining ring 133. The axial bearing 23 is disposed between the bearing housing 132 and the bearing cover plate 134. The retaining ring 133 is disposed between the bearing housing 132 and the bearing cover plate 134 to create an installation space and introduce cooling gas.

[0056] The bearing cover plate 134 and the bearing housing 132 are mechanically connected to form a closed or semi-closed space for accommodating and fixing the axial bearing 23. The retaining ring 133 is installed at a specific position between the bearing housing 132 and the bearing cover plate 134. Its function is to build and maintain a precise installation environment for the axial bearing 23 and the thrust plate 2. At the same time, the structural features of the retaining ring 133 itself are designed to guide the flow path of the cooling gas. More specifically, the main function of the bearing cover plate 134 is to cooperate with the bearing housing 132 to ensure that the axial bearing 23 maintains a stable and precise position during operation, thereby maintaining the small gap between it and the rotating thrust disk 2. The core function of the retaining ring 133 is dual: first, it acts as a mechanical shim or spacer to help determine the relative axial distance between the bearing housing 132 and the bearing cover plate 134; second, its specially contoured surface or openings can serve as a guide channel for cooling gas to enter the gap between the thrust disk 2 and the axial bearing 23, ensuring that the gas from the cooling gas supply channel 13 can be smoothly and evenly guided to the heat-generating core area.

[0057] The bearing cover 134 and bearing housing 132 securely enclose the axial bearing 23, while the retaining ring 133 fills part of the gap between them and defines the gas flow path. When cooling gas enters from the air inlet 1311 of the heat dissipation end cover 131, it flows through the annular airflow channel formed by the heat dissipation end cover 131 and the bearing housing 132. Then, part of the airflow is guided by the channel designed on the retaining ring 133, and finally directly enters the narrow gap between the thrust plate 2 and the axial bearing 23. This tight fit ensures that the cooling gas can overcome huge flow resistance and flow precisely and continuously. The heat is delivered to the friction-generating interface, which is the most difficult to cool but also the most in need of cooling, thereby efficiently removing the frictional heat generated by the thrust disc 2 and axial bearing 23 during high-speed rotation. Furthermore, this systematic coordination not only significantly reduces the operating temperature of the thrust disc 2 and axial bearing 23, effectively controls their thermal deformation, and maintains the stability of the operating clearance, but also substantially enhances the reliability and service life of the entire compressor due to the improved cooling effect. At the same time, this built-in flow guiding structure avoids unnecessary energy loss and improves the overall energy efficiency of the cooling system.

[0058] In a specific embodiment, such as Figure 8As shown, the retaining ring 133 has a circular structure with multiple evenly distributed protrusions 1331 on both sides. The thickness of the protrusions 1331 is 0.8-1.2mm and the central angle is 15°-25°.

[0059] The retaining ring 133 has a circular structure with multiple bosses 1331 evenly distributed along the circumference on both end faces of the ring. The axial thickness of these bosses 1331 is controlled between 0.8 mm and 1.2 mm, and the central angle occupied by each boss on the plane of the ring is between 15 degrees and 25 degrees. More specifically, this evenly distributed boss structure 1331 ensures that when the retaining ring 133 is installed between the bearing housing 132 and the bearing cover plate 134, the bosses on both sides will contact the surfaces of these two adjacent parts respectively, thereby supporting a very precise and stable axial clearance at multiple equally spaced positions on the ring. This clearance defined by the thickness of the bosses, together with the unoccupied arc areas between the bosses, constitutes multiple paths that allow cooling gas to flow.

[0060] With the structure of this embodiment, on the one hand, the boss thickness of 0.8-1.2 mm ensures that the retaining ring 133 itself has sufficient structural strength and rigidity, can withstand the assembly preload, and maintain a stable geometry over a long period of time, thereby reliably maintaining the relative position between the bearing housing 132 and the bearing cover plate 134, providing a stable installation environment for the axial bearing 23; on the other hand, the evenly distributed boss layout with a central angle of 15°-25° means that gas can flow evenly to the surrounding area through the fan-shaped area between the bosses. This design optimizes the uniformity of gas flow distribution, avoids local flow dead zones, and ensures that cooling gas can be efficiently and evenly introduced from the annular airflow channel to the contact area between the thrust plate 2 and the axial bearing 23, which requires the most heat dissipation; furthermore, while realizing the flow guiding function, the annular shape and uniform support characteristics of this structure also ensure the coaxiality and balance of the entire bearing mounting component, thereby indirectly contributing to the smooth operation of the compressor rotor.

[0061] In a specific embodiment, the first cooler 12 and the second cooler 14 are integrated into a dual-channel cooling module. The dual-channel cooling module has an independent first cooling channel and a second cooling channel. The first cooling channel is used to cool the gas from the bleed air channel 11, and the second cooling channel is used to cool the gas from the cooling area of ​​the thrust disk 2.

[0062] The first cooler 12 and the second cooler 14 are not two independent heat dissipation components, but are designed and manufactured as a single integrated dual-channel cooling module. Inside this integrated module, there are two completely independent flow channels: the first cooling channel and the second cooling channel. High-pressure gas from the first-stage volute outlet, supplied from the bleed air channel 11, enters the first cooling channel for cooling; while heated gas flowing out of the thrust plate 2 cooling area, having absorbed heat, enters the second cooling channel for cooling. Although these two channels share a single module housing in their physical structure, their flow paths are separated, ensuring that the two gases from different sources and temperatures do not mix during the cooling process, and each efficiently exchanges heat with the cooling medium inside the module. This integrated design produces many positive effects, the most direct being a significant simplification of external piping connections and the overall system layout, resulting in a more compact cooling structure and saving installation space, making it particularly suitable for applications with strict space constraints. Furthermore, concentrating the two heat exchange processes within an optimized module can often improve the overall efficiency and controllability of thermal management. For example, it makes it easier to manage the flow and temperature of the cooling medium in a unified manner, thereby achieving precise and efficient cooling of the two gases.

[0063] During operation, when the air compressor starts, such as Figure 10 As shown, the first stage impeller of its compression structure 3 starts to work, compresses the air and sends it into the outlet of the first stage volute. At this time, the air intake channel 11 is directly connected to the outlet, and a part of the high-pressure gas is drawn out. This high-pressure gas then enters the first cooler 12. In the airflow channel inside the first cooler 12, the gas exchanges heat with the cooling medium, and the temperature is significantly reduced. The cooled gas then flows into the cooling gas supply channel 13, the beginning of which may include a pipe. The gas then reaches the heat dissipation end cap 131 and enters through the air inlet 1311 on it. The diameter of the air inlet 1311 is between 4 and 8 mm, and there are 1 to 3 in number, which are symmetrically arranged to ensure airflow balance. After the gas enters through the air inlet 1311, it does not rush directly to the thrust plate 2, but first enters the annular airflow channel formed between the heat dissipation end cover 131 and the bearing seat 132. This annular space effectively reduces the flow resistance, allowing the gas to be distributed smoothly. Subsequently, the gas passes through the retaining ring 133 installed between the bearing housing 132 and the bearing cover plate 134. The retaining ring 133 is a ring-shaped structure with multiple evenly distributed protrusions 1331 on both sides. The thickness of the protrusions is 0.8 to 1.2 mm and the central angle is 15° to 25°. While supporting the bearing housing 132 and the bearing cover plate 134, these protrusions 1331 form gaps that allow gas to pass through, thereby guiding the gas to the air outlet 1312 on the heat dissipation end cover 131. After the gas flows out of the air outlet 1312, it directly enters the tiny gap between the thrust disk 2 and the axial bearing 23. The thrust disk 2 is firmly mounted on the short shaft 21 with an interference fit and is axially fixed by the lock nut 22 to ensure stable position during high-speed rotation. The axial bearing 23 is fixed on the bearing housing 132, which is very close to the thrust disk 2. In this gap, the cooling gas comes into contact with the surface of the high-speed rotating thrust disk 2 and the axial bearing 23, absorbing a large amount of heat generated by friction, thus effectively cooling the thrust disk 2 and the axial bearing 23. After absorbing heat, the gas temperature rises and then flows out from the thrust disk area into the second cooler 14. For secondary cooling, if an integrated design is adopted, the first cooler 12 and the second cooler 14 will be integrated into a dual-channel cooling module. The independent first cooling channel cools the gas from the bleed gas channel 11, and the independent second cooling channel cools the gas from the thrust plate 2 region. The gas after secondary cooling is finally sent back to the first stage inlet of the compressor through the return gas channel 15 to re-participate in the compression cycle. In the whole process, the bleed gas channel 11, the first cooler 12, the cooling gas supply channel 13, the second cooler 14 and the return gas channel 15 together form a closed-loop cooling system in which the gas circulates and is continuously reused. More specifically, this closed-loop working process not only utilizes high-pressure gas to overcome the high flow resistance in the thrust disk 2 region, ensuring sufficient flow of cooling gas, but also significantly reduces the gas temperature through two-stage cooling, thereby continuously controlling the temperature rise of the thrust disk 2 and the axial bearing 23. Furthermore, the coordinated operation of all components, from gas extraction, cooling, and flow guidance to heat exchange and recirculation, forms a highly efficient and stable cooling mechanism. While reducing the operating temperature of the thrust disk 2 and extending the life of components, it also improves the overall operational reliability and energy efficiency of the compressor, ultimately solving the stability problem caused by excessive temperature rise in the background technology.

[0064] Furthermore, through comparative testing, the operating temperature of the thrust disc is approximately 220°C when using a traditional external cooling solution for high-pressure fans. However, after applying the closed-loop cooling structure of this embodiment, the operating temperature of the thrust disc is significantly reduced to approximately 180°C, a temperature drop of 18%. Although the temperature resistance of the relevant bearings can reach 250°C, this invention can control the operating temperature at a lower level. This effectively reduces thermal deformation of the thrust disc and bearings caused by high temperatures, thereby reducing the probability of abnormalities during operation and improving the overall long-term operational stability of the compressor.

[0065] Example 2 This embodiment provides an air compressor, which includes a compression structure 3 and a cooling structure 1 as described in Embodiment 1. The compression structure 3 has a first-stage outlet 31 and a first-stage inlet 32. The air intake channel 11 of the cooling structure 1 is connected to the first-stage outlet 31, and the air return channel 15 of the cooling structure 1 is connected to the first-stage inlet 32.

[0066] The compression structure 3 forms a gas inlet and outlet during operation, specifically having a first-stage outlet 31 and a first-stage inlet 32. These two interfaces are the starting point of the entire gas compression cycle and the end point of a specific stage. The cooling structure 1 operates through its unique bleed channel 11 and return channel 15. More specifically, the cooling structure 1 is not an independent external system; its bleed channel 11 is directly connected to the first-stage outlet 31 of the compression structure 3, from which a portion of the gas that has undergone preliminary compression and has a higher pressure is actively diverted as a cooling medium. After completing a series of heat exchange tasks inside the cooling structure 1, the gas carrying heat is sent back to the first-stage inlet 32 ​​of the compression structure 3 through the return channel 15, and rejoins the main gas flow to enter the next compression cycle.

[0067] The effects of this design are multifaceted and fundamental. It means that cooling is deeply integrated into the compressor itself, with the cooling medium directly sourced from and ultimately returned to the compression process, forming an internal self-circulating heat dissipation loop. This integrated design first solves the pressure problem of the cooling gas source. Utilizing the high-pressure gas at the first-stage outlet 31 ensures sufficient power to deliver the cooling medium through the narrow gap between the thrust plate and the axial bearing, overcoming the cooling failure problem caused by insufficient air pressure in traditional external cooling systems. Secondly, it greatly improves the system's compactness and energy efficiency. Because the cooling gas is recycled within the system, it avoids the energy loss caused by directly venting high-temperature gas or relying on a large external air-cooling system, resulting in higher overall compressor operating efficiency.

[0068] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A cooling structure, characterized in that, The cooling structure is used to cool the thrust plate of the air compressor. The cooling structure includes an air intake passage, a first cooler, and a cooling gas supply passage. The air intake passage is configured to connect to the first stage outlet of the compressor. The first cooler is connected downstream of the air intake passage. The cooling gas supply passage is connected between the outlet of the first cooler and the cooling area of ​​the thrust plate. The cooling gas supply channel includes a heat dissipation end cover, which is provided with an air inlet and an air outlet. The air inlet is connected to the outlet of the first cooler, and the air outlet is connected to the cooling area of ​​the thrust plate. The air inlet and air outlet have a diameter of 4-8mm, and there are 1-3 of them, which are symmetrically arranged on the heat dissipation end cover.

2. The cooling structure according to claim 1, characterized in that, The cooling structure further includes a second cooler and a return gas passage. The second cooler is configured to receive gas from the thrust disk cooling area, and the return gas passage is configured to connect the outlet of the second cooler to the first stage inlet of the compressor.

3. The cooling structure according to claim 2, characterized in that, The air intake channel, the first cooler, the cooling gas supply channel, the second cooler, and the return air channel constitute a closed-loop cooling system.

4. The cooling structure according to claim 3, characterized in that, The first stage outlet is the first stage volute outlet, and the air intake channel is connected to the first stage volute outlet.

5. The cooling structure according to claim 1, characterized in that, The cooling gas supply channel also includes a bearing housing, and an annular airflow channel is formed between the heat dissipation end cap and the bearing housing to reduce gas flow resistance.

6. The cooling structure according to claim 5, characterized in that, The thrust disk is mounted on a short shaft, and the cooling area of ​​the thrust disk includes the thrust disk and an axial bearing that mates with the bearing housing.

7. The cooling structure according to claim 6, characterized in that, The thrust plate and the short shaft are assembled by an interference fit and are axially fixed by a lock nut.

8. The cooling structure according to claim 6, characterized in that, The cooling gas supply channel also includes a bearing cover plate and a retaining ring. The axial bearing is disposed between the bearing housing and the bearing cover plate, and the retaining ring is disposed between the bearing housing and the bearing cover plate to create an installation space and introduce cooling gas.

9. The cooling structure according to claim 8, characterized in that, The retaining ring has a circular structure with multiple evenly distributed protrusions on both sides. The thickness of the protrusions is 0.8-1.2mm and the central angle is 15°-25°.

10. The cooling structure according to claim 2, characterized in that, The first cooler and the second cooler are integrated into a dual-channel cooling module. The dual-channel cooling module has an independent first cooling channel and a second cooling channel. The first cooling channel is used to cool the gas from the bleed air channel, and the second cooling channel is used to cool the gas from the thrust disk cooling area.

11. An air compressor, characterized in that, The air compressor includes a compression structure and a cooling structure as described in any one of claims 1 to 10, the compression structure having a first stage outlet and a first stage inlet, the bleed air passage of the cooling structure being connected to the first stage outlet, and the return air passage of the cooling structure being connected to the first stage inlet.

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