A turbine drive shaft and air circulator

Abstract

The application provides a turbine transmission shaft and an air circulating machine, the turbine transmission shaft comprises a first shaft section, a second shaft section and a thrust section, the first shaft section, the thrust section and the second shaft section are sequentially arranged, the first shaft section, the thrust section and the second shaft section are integrally formed and can conduct heat between each other; the axial side surface of the thrust section towards the first shaft section is a first thrust disc surface, the axial side surface of the thrust section towards the second shaft section is a second thrust disc surface, the radial outer periphery of the thrust section can introduce cooling gas and can divide the cooling gas into at least two streams, one of which can pass through the first thrust disc surface and reach the outer peripheral wall of the first shaft section, and the other of which can pass through the second thrust disc surface and reach the outer peripheral wall of the second shaft section. According to the application, flow distribution is not needed for the cooling of the first shaft section and the second shaft section, and the problem of flow distribution involved in the cooling of the aerodynamic bearing at different positions of the existing air circulating machine is solved.

Description

Technical Field

[0001] This invention relates to the field of air circulator technology, specifically to a turbine drive shaft and an air circulator. Background Technology

[0002] Air circulators used in compressed air refrigerant systems have rotors supported by pneumatic bearings that rotate at high speed. The heat generated by air friction between the bearings and the rotor needs to be dissipated promptly; otherwise, the accumulated heat will burn out the bearings, and the air circulator will not function properly.

[0003] Patent 201410083009.3 discloses a shaft diameter with a sealing disc. This shaft diameter needs to be assembled with another thrust bearing shaft to form a complete shaft assembly for guiding cooling gas. However, assembling the shaft presents challenges in controlling assembly precision, as the high-precision shaft assembly requirements increase processing costs and quality control difficulties. The sealing disc on the shaft diameter, designed to control the flow distribution of cooling air, undoubtedly increases structural complexity, assembly control difficulty, and prototype manufacturing costs.

[0004] Patent 201110432497.0 discloses a thrust bearing shaft that functions as both a radial shaft and a thrust disk. The thrust bearing shaft needs to be assembled with another radial shaft to form a complete shaft assembly that guides cooling gas. However, assembling the shaft presents challenges in controlling assembly precision, as the high-precision shaft assembly requirements increase processing costs and the difficulty of quality control.

[0005] Because existing air circulators require flow distribution for cooling pneumatic bearings at different locations, which leads to technical problems such as flow distribution difficulties when cooling pneumatic bearings at different locations, this invention studies and designs a turbine drive shaft and an air circulator. Summary of the Invention

[0006] Therefore, the technical problem to be solved by the present invention is to overcome the defect in the prior art that the air circulator needs to distribute the flow for cooling the pneumatic bearings at different positions, which leads to the flow distribution involved when cooling the pneumatic bearings at different positions, thereby providing a turbine drive shaft and an air circulator.

[0007] To address the above problems, the present invention provides a turbine drive shaft, comprising:

[0008] The first shaft segment, the second shaft segment, and the thrust segment are arranged sequentially along the axial direction of the turbine drive shaft. The thrust segment is connected between the first shaft segment and the second shaft segment, and the first shaft segment, the thrust segment, and the second shaft segment are integrally formed and can conduct heat between each other.

[0009] The axial side of the thrust section facing the first shaft section is the first thrust plate surface, and the axial side of the thrust section facing the second shaft section is the second thrust plate surface. Cooling gas can be introduced into the radial outer periphery of the thrust section and can be divided into at least two streams. One stream can pass through the first thrust plate surface and reach the outer peripheral wall of the first shaft section, and the other stream can pass through the second thrust plate surface and reach the outer peripheral wall of the second shaft section.

[0010] In some implementations...

[0011] The first shaft segment has a first inner shaft hole extending along the axial direction, and the second shaft segment has a second inner shaft hole extending along the axial direction. The first inner shaft hole extends to the inner circumference of the thrust segment and communicates with the second inner shaft hole. The first shaft segment also has a first flow hole that penetrates its inner and outer peripheral walls. The first flow hole communicates with the first inner shaft hole so that cooling gas from the outer peripheral wall of the first shaft segment can be introduced into the first inner shaft hole and then into the second inner shaft hole. The second shaft segment also has a second flow hole that penetrates its inner and outer peripheral walls. The second flow hole communicates with the second inner shaft hole so that cooling gas from the outer peripheral wall of the second shaft segment can be introduced into the second inner shaft hole.

[0012] In some implementations...

[0013] There are multiple first flow holes, which are spaced apart along the circumferential direction of the first shaft segment; there are multiple second flow holes, which are spaced apart along the circumferential direction of the second shaft segment.

[0014] In some implementations...

[0015] The outer diameter of the first shaft segment is smaller than the outer diameter of the second shaft segment, the outer diameter of the second shaft segment is smaller than the outer diameter of the thrust segment, the inner diameter of the first shaft segment is smaller than the inner diameter of the second shaft segment, and the outer diameter of the first shaft segment is smaller than the inner diameter of the second shaft segment.

[0016] In some implementations...

[0017] The outer diameter of the second shaft segment is D0, the diameter of the first flow hole is D1, and D1 / D0 = 0.02 to 0.2, and the diameter of the second flow hole is D2, and D2 / D0 = 0.02 to 0.2.

[0018] In some implementations...

[0019] The first flow hole is positioned close to the thrust section relative to the second flow hole, so that the gas entering the first shaft inner hole through the first flow hole flows into the second shaft inner hole and mixes with the gas entering the second shaft inner hole through the second flow hole. After mixing, the mixture is discharged through the axial end of the second shaft section away from the thrust section.

[0020] In some implementations...

[0021] The distance between the first flow hole along the axial direction and the second thrust plate surface of the thrust section is L1, the distance between the second flow hole along the axial direction and the second thrust plate surface of the thrust section is L2, the outer diameter of the second shaft section is D0, and L1 / D0 = 0.05~0.5, L2 / D0 = 0.4~2.0.

[0022] The present invention also provides an air circulator, which includes the aforementioned turbine drive shaft, and further includes a first thrust bearing and a second thrust bearing.

[0023] The first thrust bearing is disposed on the outer periphery of the first shaft segment and faces the first thrust plate to provide thrust resistance to the thrust segment. The second thrust bearing is disposed on the outer periphery of the second shaft segment and faces the second thrust plate to provide thrust resistance to the thrust segment. One stream of the cooling gas introduced into the radial outer periphery of the thrust segment can enter the first gap between the first thrust plate and the first thrust bearing for cooling, and then reach the outer peripheral wall of the first shaft segment. Another stream can enter the second gap between the second thrust plate and the second thrust bearing for cooling, and then reach the outer peripheral wall of the second shaft segment.

[0024] In some implementations...

[0025] A radial bearing is also provided on the outer periphery of the second shaft segment. A third gap is provided between the first thrust bearing and the first shaft segment. The first flow hole is radially opposite to the first thrust bearing. The first gap communicates with the first flow hole through the third gap, so that the gas cooled and heat-exchanged after passing through the first gap enters the inner hole of the first shaft through the first flow hole.

[0026] There is a fourth gap between the second thrust bearing and the second shaft segment, and a fifth gap between the radial bearing and the second shaft segment. The second gap, the fourth gap, and the fifth gap are connected in sequence, so that the gas cooled and heat-exchanged through the second gap enters the fourth gap and the fifth gap in sequence. The second flow hole is provided on the axial side of the radial bearing away from the second thrust bearing, and the fifth gap is connected to the inner hole of the second shaft through the second flow hole.

[0027] In some implementations...

[0028] The axial end of the radial bearing that is away from the second thrust bearing does not extend beyond the second flow hole, so that the second flow hole is not opposite to the radial bearing.

[0029] In some implementations...

[0030] A compressor impeller is connected to one end of the second shaft segment away from the thrust section. The compressor impeller has an inner bore. The end of the second shaft inner bore away from the first shaft segment communicates with the inner bore of the compressor impeller, so that the gas entering the inner bore of the first shaft and the gas entering the inner bore of the second shaft both enter the inner bore of the compressor impeller through the inner bore of the second shaft.

[0031] In some implementations...

[0032] The outer periphery of the thrust section has a cavity. The air circulator includes an expander and a connecting structure. The expander includes an expander volute, an expander inlet, a first channel, and a second channel. The first channel connects a portion of the gas inside the expander volute inlet to the outside, and the second channel connects the gas outside the expander volute to the cavity. The connecting structure is connected to the expander volute, and a channel inside the connecting structure connects the first channel and the second channel.

[0033] The turbine drive shaft and air circulator provided by this invention have the following beneficial effects:

[0034] 1. This invention configures the turbine drive shaft as comprising a first shaft section, a second shaft section, and a thrust section, with the thrust section connecting the first and second shaft sections. Cooling gas is introduced around the outer periphery of the thrust section, splitting into two streams: one flowing towards the first shaft section and the other towards the second shaft section. The gas flowing towards the first thrust bearing can cool and exchange heat between the first thrust bearing and the thrust section, and the gas flowing towards the second thrust bearing can cool and exchange heat between the second thrust bearing and the thrust section. Because the first shaft section, the thrust section, and the second shaft section are integrally formed and can conduct heat between each other, they can form a single unit. This eliminates the need for flow distribution of the two gas streams, allowing each stream to act independently on the integrally structured turbine drive shaft to cool and exchange heat. Its cooling, for example, if the gas flow rate to the first shaft section is greater than the flow rate to the second shaft section, the cooling effect of the cooling gas on the first thrust bearing and the thrust section is greater than the cooling effect on the second thrust bearing and the thrust section, and the cooling effect on the first shaft section is greater than the cooling effect on the second shaft section. However, since the first and second shaft sections and the thrust section are integrally formed, heat can be transferred between the first and second shaft sections through the thrust section. That is, the cooling capacity of the first shaft section will be transferred to the second shaft section. Therefore, the cooling effect of the first and second shaft sections and the first and second thrust bearings can eventually be balanced, and there is no need to distribute the flow rate for cooling the first and second shaft sections. This solves the problem of flow rate distribution when cooling pneumatic bearings at different positions in existing air circulators.

[0035] 2. Furthermore, the present invention further enables the introduction of cooling gas from the outer peripheral wall of the first shaft segment into the first shaft inner hole via the first shaft inner hole and the first flow hole penetrating the inner and outer peripheral walls of the first shaft segment. Similarly, it enables the introduction of cooling gas from the outer peripheral wall of the second shaft segment into the second shaft inner hole via the second shaft inner hole and the second flow hole penetrating the inner and outer peripheral walls of the second shaft segment. The first shaft inner hole and the second shaft inner hole are connected, allowing the cooling gas from the outer peripheral wall of the first shaft segment to be introduced into the first shaft inner hole and then into the second shaft inner hole, thereby achieving a gas path from... The air passage structure connecting the inner bore of the first shaft to the inner bore of the second shaft forms a cooling flow path. The heat of the first shaft section is carried away by the gas in the inner bore of the first shaft, and then the heat of the second shaft section is carried away in the inner bore of the second shaft. This creates a sequential heat transfer effect on the first shaft section, the thrust section, and the second shaft section. This further makes the cooling effect of the first and second shaft sections, the first and second thrust bearings, and the radial bearing more balanced, further improving the uniformity of heat exchange and further solving the problem of flow distribution involved in cooling pneumatic bearings at different positions in existing air circulators.

[0036] 3. The present invention also allows a certain amount of cooling gas drawn in from the expander inlet to be introduced into the first channel through the first and second channels opened on the expander volute. The gas is then introduced into the cavity on the outer periphery of the thrust section through the internal and second channels of the external connection structure. The working gas of the air circulator itself is used to cool the internal bearing components, thereby realizing the self-cooling function of the pneumatic bearings of the support shaft system. This ensures the reliability of the high-speed rotating rotor system. Compared with the method of introducing cooling gas through external pipes, the channel opened on the volute can shorten the gas flow path, reduce airflow loss and pressure loss, and make the structure more compact. Attached Figure Description

[0037] Figure 1 This is a schematic diagram of the air circulator of the present invention;

[0038] Figure 2 This is a schematic diagram of the assembly structure of the turbine drive shaft and impeller of the present invention;

[0039] Figure 3 This is a schematic diagram of the cooling flow of the air circulator of the present invention in the turbine drive shaft section;

[0040] Figure 4 This is a longitudinal sectional view of the turbine drive shaft of the present invention;

[0041] Figure 5 yes Figure 4 AA section view;

[0042] Figure 6 yes Figure 4 BB cross-sectional view.

[0043] The attached figures are labeled as follows:

[0044] T01, expander inlet; T02, expander outlet; C01, compressor inlet; C02, compressor outlet; F01, fan inlet; F02, fan outlet;

[0045] 01. Turbine drive shaft; C. First shaft section; D. Second shaft section; E. Thrust section; F. Expander volute; 02. Expander impeller; 03. Compressor impeller; 04. First thrust bearing; 05. Second thrust bearing; 06. Radial bearing; 07. Connecting structure; L11. First airflow; Q01. Cavity; L21. Second airflow; L22. Second airflow'; 0107. First thrust plate; 0108. Second thrust plate; 0101. First flow hole; 0102. First shaft inner hole; 0103. Second shaft inner hole; 0104. Second flow hole; 0301. Compressor impeller inner hole; L3. Third airflow; T0101. First channel; T0102. Second channel. Detailed Implementation

[0046] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0047] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0048] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0049] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0050] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0051] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0052] like Figure 1-6 As shown, the present invention provides a turbine drive shaft, which includes:

[0053] The first shaft segment C, the second shaft segment D, and the thrust segment E are arranged sequentially along the axial direction of the turbine drive shaft. The thrust segment E is connected between the first shaft segment C and the second shaft segment D. The first shaft segment C, the thrust segment E, and the second shaft segment D are integrally formed and can conduct heat between each other.

[0054] The axial side of the thrust section E facing the first shaft section C is the first thrust plate surface 0107, and the axial side of the thrust section E facing the second shaft section D is the second thrust plate surface 0108. Cooling gas can be introduced into the radial outer periphery of the thrust section E and can be divided into at least two streams. One stream can pass through the first thrust plate surface 0107 and reach the outer peripheral wall of the first shaft section C, and the other stream can pass through the second thrust plate surface 0108 and reach the outer peripheral wall of the second shaft section D.

[0055] This invention configures a turbine drive shaft comprising a first shaft section, a second shaft section, and a thrust section, with the thrust section connecting the first and second shaft sections. Cooling gas is introduced around the outer periphery of the thrust section, splitting into two streams: one flowing towards the first shaft section and the other towards the second shaft section. The gas flowing towards the first thrust bearing can cool and exchange heat between the first thrust bearing and the thrust section, while the gas flowing towards the second thrust bearing can cool and exchange heat between the second thrust bearing and the thrust section. Because the first shaft section, the thrust section, and the second shaft section are integrally formed and can conduct heat between each other, they can form a single unit. This eliminates the need for flow distribution of the two gas streams, allowing each stream to act independently on the integrally structured turbine drive shaft. In terms of cooling, for example, if the gas flow rate to the first shaft section is greater than the flow rate to the second shaft section, the cooling effect of the cooling gas on the first thrust bearing and the thrust section is greater than that on the second thrust bearing and the thrust section, and the cooling effect on the first shaft section is greater than that on the second shaft section. However, since the first and second shaft sections and the thrust section are integrally formed, heat can be transferred between the first and second shaft sections through the thrust section. That is, the cooling capacity of the first shaft section will be transferred to the second shaft section. Therefore, the cooling effect of the first and second shaft sections and the first and second thrust bearings can eventually be balanced, and there is no need to distribute the flow rate for cooling the first and second shaft sections. This solves the problem of flow rate distribution when cooling pneumatic bearings at different positions in existing air circulators.

[0056] In some implementations...

[0057] The first shaft segment C has a first inner shaft hole 0102 extending along the axial direction, and the second shaft segment D has a second inner shaft hole 0103 extending along the axial direction. The first inner shaft hole 0102 extends to the inner circumference of the thrust segment E and communicates with the second inner shaft hole 0103. The first shaft segment C also has a first flow hole 0101 that penetrates its inner and outer peripheral walls. The first flow hole 0101 communicates with the first inner shaft hole 0102 so that cooling gas from the outer peripheral wall of the first shaft segment C can be introduced into the first inner shaft hole 0102 and then into the second inner shaft hole 0103. The second shaft segment D also has a second flow hole 0104 that penetrates its inner and outer peripheral walls. The second flow hole 0104 communicates with the second inner shaft hole 0103 so that cooling gas from the outer peripheral wall of the second shaft segment D can be introduced into the second inner shaft hole 0103.

[0058] The present invention further utilizes a first shaft inner hole inside the first shaft segment and a first flow hole penetrating the inner and outer peripheral walls of the first shaft segment to introduce cooling gas from the outer peripheral wall of the first shaft segment into the first shaft inner hole. Similarly, it utilizes a second shaft inner hole inside the second shaft segment and a second flow hole penetrating the inner and outer peripheral walls of the second shaft segment to introduce cooling gas from the outer peripheral wall of the second shaft segment into the second shaft inner hole. The first shaft inner hole and the second shaft inner hole are connected, allowing cooling gas from the outer peripheral wall of the first shaft segment to be introduced into the first shaft inner hole and then into the second shaft inner hole. This achieves a continuous airflow structure from the first shaft inner hole to the second shaft inner hole, forming a cooling flow path. Heat from the first shaft segment is carried away by the gas in the first shaft inner hole, and subsequently, heat from the second shaft segment is carried away in the second shaft inner hole. This creates a sequential heat transfer effect on the first shaft segment, the thrust section, and the second shaft segment, further balancing the cooling effect of the first and second shaft segments, the first and second thrust bearings, and the radial bearing. This further improves the uniformity of heat exchange and solves the problem of flow distribution during the cooling of pneumatic bearings at different positions in existing air circulators.

[0059] In some implementations...

[0060] There are multiple first flow holes 0101, which are spaced apart along the circumferential direction of the first shaft segment C; there are multiple second flow holes 0104, which are spaced apart along the circumferential direction of the second shaft segment D. This is a preferred structural form of the first and second flow holes of the present invention. The multiple first flow holes can increase the conduction area, further increasing the flow rate of airflow from the outer peripheral wall of the first shaft segment to the inner hole of the first shaft, thereby improving the cooling effect on the first shaft segment; the multiple second flow holes can increase the conduction area, further increasing the flow rate of airflow from the outer peripheral wall of the second shaft segment to the inner hole of the second shaft, thereby improving the cooling effect on the second shaft segment.

[0061] In some implementations...

[0062] The outer diameter of the first shaft segment C is smaller than the outer diameter of the second shaft segment D, the outer diameter of the second shaft segment D is smaller than the outer diameter of the thrust segment E, the inner diameter of the first shaft segment C is smaller than the inner diameter of the second shaft segment D, and the outer diameter of the first shaft segment C is smaller than the inner diameter of the second shaft segment D.

[0063] This is the preferred dimensional relationship of the first shaft segment, the second shaft segment, and the thrust segment of the present invention. The outer diameter of the first shaft segment is smaller than that of the second shaft segment, which can form a step between them. The thrust segment is set at the step position between them. The outer diameter of the thrust segment is the largest and extends outward to set the first thrust bearing and the second thrust bearing on both sides to thrust the drive shaft. The inner diameter of the first shaft segment is smaller than that of the second shaft segment, which can form a stepped structure inside, thereby enhancing the disturbance of the airflow and improving the cooling performance of the airflow on the first and second shaft segments. The outer diameter of the first shaft segment is smaller than that of the inner diameter of the second shaft segment, which can further increase the height of the internal stepped structure, further improving the disturbance effect on the airflow and further improving the cooling performance.

[0064] In some implementations...

[0065] The outer diameter of the second shaft segment D is D0, the diameter of the first flow hole 0101 is D1, and D1 / D0 = 0.02 to 0.2, and the diameter of the second flow hole 0104 is D2, and D2 / D0 = 0.02 to 0.2.

[0066] like Figure 4-6 As shown. The first flow hole 0101 and the second flow hole 0104 are preferably perpendicular to the axis of the rotating shaft and are evenly arranged circumferentially. The number of holes is preferably 2 to 12. Too many holes weaken the strength of the shaft, and too few holes make it difficult to ensure the flow area. The preferred number of holes is 8. Considering both the strength of the rotor shaft and the flow loss of the cooling fluid, the hole diameter ratio D1 / D0 = 0.02 to 0.2 and the hole diameter ratio D2 / D0 = 0.02 to 0.2 are both suitable. Considering the economics of processing, D1 / D0 = D2 / D0 = 0.06 is preferred. A smaller hole diameter ratio results in higher rotor shaft strength but greater flow loss of the cooling fluid; a larger hole diameter ratio results in less flow loss of the cooling fluid but lower rotor shaft strength. Therefore, the present invention uses D1 / D0 = D2 / D0 = 0.02 to 0.2, which can reduce the flow loss of the cooling fluid while improving the structural strength of the rotor shaft.

[0067] In some implementations...

[0068] The first flow hole 0101 is positioned close to the thrust section E relative to the second flow hole 0104, so that the gas entering the first shaft inner hole 0102 through the first flow hole 0101 flows into the second shaft inner hole 0103 and mixes with the gas entering the second shaft inner hole 0103 through the second flow hole 0104. After mixing, the mixture is discharged through the axial end of the second shaft section D away from the thrust section E.

[0069] This is the preferred relative position of the first and second flow holes of the present invention. The first flow hole is positioned closer to the thrust section than the second flow hole, so that the pressure of the gas flowing into the inner hole of the first shaft is relatively high. The gas in the second flow hole enters the inner hole of the second shaft after passing through the radial bearing for heat exchange. Therefore, it can effectively ensure that the airflow in the inner hole of the first shaft flows to the inner hole of the second shaft under the drive of the pressure difference and flows in a unilateral direction, so that the first shaft section, the thrust section and the second shaft section achieve uniform cooling. This further solves the problem of needing to distribute the flow rate for cooling the pneumatic bearing at different positions, eliminating the need for flow rate distribution for the pneumatic bearing and improving the cooling effect.

[0070] In some implementations...

[0071] The distance between the first flow hole 0101 and the second thrust plate surface 0108 of the thrust section E along the axial direction is L1, the distance between the second flow hole 0104 and the second thrust plate surface 0108 of the thrust section E along the axial direction is L2, the outer diameter of the second shaft section D is D0, and L1 / D0 = 0.05~0.5, L2 / D0 = 0.4~2.0.

[0072] like Figure 1 and Figure 4 As shown. To support the rotor (i.e., the turbine drive shaft 01), the position of the radial bearing 06 relative to the turbine drive shaft positioning surface (i.e., the second thrust plate surface 0108) is fixed. To avoid the second flow hole 0104 damaging the effective bearing surface of the radial bearing 06, the distance L2 from the cross-section of the second flow hole 0104 to the shaft positioning surface cannot be too small. Considering the compactness of the air circulator structure, L2 cannot be too large. Taking all factors into account, the length-to-diameter ratio L2 / D0 is determined to be 0.4 to 2.0, preferably 1.194. If the distance L1 from the first flow hole 0101 along the axial direction within the cross-section AA to the second thrust plate surface 0108 is too large, the structural compactness will be poor. If L1 is too small, machining will be difficult. Therefore, considering both structural compactness and machining feasibility, this invention uses L1 / D0 = 0.05 to 0.5, preferably L1 / D0 = 0.2, which ensures the compactness of the air circulator while improving machining feasibility.

[0073] The present invention also provides an air circulator, which includes the aforementioned turbine drive shaft 01, and further includes a first thrust bearing 04 and a second thrust bearing 05.

[0074] The first thrust bearing 04 is disposed on the outer periphery of the first shaft segment C and faces the first thrust plate surface 0107 to provide thrust resistance to the thrust segment E. The second thrust bearing 05 is disposed on the outer periphery of the second shaft segment D and faces the second thrust plate surface 0108 to provide thrust resistance to the thrust segment E. One stream of the cooling gas introduced into the radial outer periphery of the thrust segment E can enter the first gap between the first thrust plate surface 0107 and the first thrust bearing 04 for cooling, and then reach the outer peripheral wall of the first shaft segment C. Another stream can enter the second gap between the second thrust plate surface 0108 and the second thrust bearing 05 for cooling, and then reach the outer peripheral wall of the second shaft segment D.

[0075] This invention configures a turbine drive shaft comprising a first shaft section, a second shaft section, and a thrust section, with the thrust section connecting the first and second shaft sections. Cooling gas is introduced around the outer periphery of the thrust section, splitting into two streams: one flowing towards the first thrust bearing, and the other towards the second thrust bearing. The gas flowing towards the first thrust bearing can cool and exchange heat between the first thrust bearing and the thrust section, and the gas flowing towards the second thrust bearing can cool and exchange heat between the second thrust bearing and the thrust section. Because the first shaft section, the thrust section, and the second shaft section are integrally formed and can conduct heat between each other, they can form a single unit. This eliminates the need for flow distribution of the two gas streams, allowing each stream to act independently on the integrally structured turbine drive shaft. For cooling, if the gas flow rate to the first shaft section is greater than that to the second shaft section, the cooling effect of the cooling gas on the first thrust bearing and the thrust section is greater than that on the second thrust bearing and the thrust section, and the cooling effect on the first shaft section is greater than that on the second shaft section. However, since the first, second, and thrust sections are integrally formed, heat can be transferred between the first and second shaft sections through the thrust section. That is, the cooling capacity of the first shaft section will be transferred to the second shaft section. Therefore, the cooling effect of the first and second shaft sections and the first and second thrust bearings can be made more balanced. There is no need to distribute the flow rate for cooling the first and second shaft sections, thus solving the problem of flow rate distribution when cooling pneumatic bearings at different positions in existing air circulators.

[0076] In some implementations...

[0077] A radial bearing 06 is also provided on the outer periphery of the second shaft segment D. A third gap is provided between the first thrust bearing 04 and the first shaft segment C. The first flow hole 0101 is radially opposite to the first thrust bearing 04. The first gap is connected to the first flow hole 0101 through the third gap, so that the gas cooled and heat-exchanged after passing through the first gap enters the first shaft inner hole 0102 through the first flow hole 0101.

[0078] There is a fourth gap between the second thrust bearing 05 and the second shaft segment D, and a fifth gap between the radial bearing 06 and the second shaft segment D. The second gap, the fourth gap and the fifth gap are connected in sequence, so that the gas cooled and heat-exchanged through the second gap enters the fourth gap and the fifth gap in sequence. The second flow hole 0104 is provided on the axial side of the radial bearing 06 away from the second thrust bearing 05, and the fifth gap is connected to the second shaft inner hole 0103 through the second flow hole 0104.

[0079] The present invention further utilizes a first shaft inner hole inside the first shaft segment and a first flow hole penetrating the inner and outer peripheral walls of the first shaft segment to introduce cooling gas from the outer peripheral wall of the first shaft segment into the first shaft inner hole. Similarly, it utilizes a second shaft inner hole inside the second shaft segment and a second flow hole penetrating the inner and outer peripheral walls of the second shaft segment to introduce cooling gas from the outer peripheral wall of the second shaft segment into the second shaft inner hole. The first shaft inner hole and the second shaft inner hole are connected, allowing cooling gas from the outer peripheral wall of the first shaft segment to be introduced into the first shaft inner hole and then into the second shaft inner hole. This achieves a continuous airflow structure from the first shaft inner hole to the second shaft inner hole, forming a cooling flow path. Heat from the first shaft segment is carried away by the gas in the first shaft inner hole, and subsequently, heat from the second shaft segment is carried away in the second shaft inner hole. This creates a sequential heat transfer effect on the first shaft segment, the thrust section, and the second shaft segment, further balancing the cooling effect of the first and second shaft segments, the first and second thrust bearings, and the radial bearing. This further improves the uniformity of heat exchange and solves the problem of flow distribution during the cooling of pneumatic bearings at different positions in existing air circulators.

[0080] In some implementations...

[0081] The axial end of the radial bearing 06, away from the second thrust bearing 05, does not extend beyond the second flow hole 0104, so that the second flow hole 0104 is not opposite to the radial bearing 06. This is the preferred location of the second flow hole in the present invention, that is, it is located outside the axial end of the radial bearing, which is farthest from the second thrust bearing. This ensures that the radial bearing does not obstruct the airflow of the second flow hole, thereby improving the cooling effect on the radial bearing and the second shaft segment.

[0082] In some implementations...

[0083] A compressor impeller 03 is connected to the end of the second shaft segment D away from the thrust segment E. The compressor impeller 03 has a compressor impeller inner hole 0301. The end of the second shaft inner hole 0103 away from the first shaft segment C communicates with the compressor impeller inner hole 0301, so that the gas entering the first shaft inner hole 0102 and the gas entering the second shaft inner hole 0103 both enter the compressor impeller inner hole 0301 through the second shaft inner hole 0103.

[0084] The present invention further preferably connects the end of the second shaft segment away from the thrust section to the compressor impeller, and connects the inner hole of the compressor impeller to the inner hole of the second shaft. This can effectively mix the gas after it has been cooled by the first thrust bearing, the first shaft segment, the thrust section, the second thrust bearing, the second shaft segment, and the radial bearing, and introduce it into the inner hole of the compressor impeller for compression in the compressor. Since the gas temperature is effectively increased and the pressure is effectively reduced after passing through the above-mentioned multiple shaft segments and multiple bearings, the compressor intake standards and requirements are effectively met, the intake superheat is increased, the gas can be recycled, and the system energy efficiency of the air circulator is improved.

[0085] In some implementations...

[0086] The outer periphery of the thrust section E has a cavity Q01. The air circulator includes an expander and a connecting structure 07. The expander includes an expander volute F, on which an expander inlet T01 is opened. The expander volute F has a first channel T0101 and a second channel T0102. The first channel T0101 can connect part of the gas inside the inlet of the expander volute F to the outside. The second channel T0102 can connect the gas outside the expander volute F to the cavity Q01. The connecting structure 07 is connected to the expander volute F, and the channel inside the connecting structure 07 connects the first channel T0101 and the second channel T0102.

[0087] The present invention also allows a certain amount of cooling gas drawn in from the expander inlet to be introduced into the first channel through the first and second channels opened on the expander volute. The gas is then introduced into the cavity on the outer periphery of the thrust section through the internal and second channels of the external connection structure. The working gas of the air circulator itself is used to cool the internal bearing components, thereby realizing the self-cooling function of the pneumatic bearings of the support shaft system. This ensures the reliability of the high-speed rotating rotor system. Compared with the method of introducing cooling gas through external pipes, the channel opened on the volute can shorten the gas flow path, reduce airflow loss and pressure loss, and make the structure more compact.

[0088] like Figure 1 As shown. This is an air circulator used in a compressed air refrigeration system. The working gas enters the expander through inlet T01, expands, and performs work. The temperature of the gas decreases after this work, and the low-temperature gas flows out from the expander outlet T02 and is transported to the area requiring cooling. Part of the expansion work is used to drive the compressor impeller, drawing the working gas into the compressor inlet CO1, compressing it, and discharging it from the compressor outlet CO2. The other part is used to drive the fan impeller, drawing cooling air into the fan inlet F01, passing it through the fan blades, and discharging it from the fan outlet F02.

[0089] like Figure 2 As shown, the turbine drive shaft 01 connects the expander impeller 02 and the compressor impeller 03. Gas is drawn into the expander through the expander inlet T01 and performs work. After the work is done, the gas temperature decreases, and the low-temperature gas flows out from the expander outlet T02. Through the turbine drive shaft 01, the expansion work of the expander impeller 02 is transmitted to the compressor impeller 03, driving the compressor to draw in gas through the compressor inlet C01 and compress the gas before discharging it from the compressor outlet C02.

[0090] like Figure 3 As shown. The turbine drive shaft 01 is supported axially by a first thrust bearing 04 and a second thrust bearing 05, and radially by a radial bearing 06. The turbine drive shaft 01 is supported by the bearings in the ACM and rotates at high speed, generating heat through friction.

[0091] This invention provides a first channel T0101 and a second channel T0102 at the expander inlet T01, and a connecting structure 07 to introduce a first airflow L11 from the expander inlet T01 into the cavity Q01. In the cavity Q01, the gas splits into two airflows: a second airflow L21 and a second airflow L22. The second airflow L21 flows through the gap between the turbine drive shaft 01 and the first thrust bearing 04, carrying away the frictional heat between the turbine drive shaft 01 and the first thrust bearing 04. Simultaneously, the second airflow L21 exchanges heat with the turbine drive shaft disc surface (first thrust disc surface 0107), carrying away the frictional heat between the turbine drive shaft 01 and the second thrust bearing 05. The gas then flows into the first shaft inner hole 0102 through the first flow hole 0101 of the turbine drive shaft. The second airflow L21 flows from the first shaft inner hole 0102 through the second shaft inner hole 0103, where it exchanges heat with the second shaft inner hole 0103, carrying away the frictional heat between the turbine drive shaft 01 and the radial bearing 06. The second airflow L22 flows through the gap between the turbine drive shaft 01 and the second thrust bearing 05, carrying away the frictional heat between the turbine drive shaft 01 and the second thrust bearing 05. Simultaneously, the second airflow L22 exchanges heat with the turbine drive shaft disc surface (second thrust disc surface 0108), carrying away the frictional heat between the turbine drive shaft 01 and the first thrust bearing 04. Then, it flows through the gap between the turbine drive shaft 01 and the radial bearing 06, carrying away the frictional heat between the turbine drive shaft 01 and the radial bearing 06. The second airflow L22 flows into the second shaft inner bore 0103 from the second flow hole 0104 of the drive shaft. In the compressor impeller inner bore 0301, the second airflow L21 and the second airflow L22 combine to form a third airflow L3, which flows out of the turbine drive shaft 01.

[0092] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A turbine drive shaft, characterized in that: include: The first shaft segment (C), the second shaft segment (D), and the thrust segment (E) are arranged sequentially along the axial direction of the turbine drive shaft. The thrust segment (E) is connected between the first shaft segment (C) and the second shaft segment (D). The first shaft segment (C), the thrust segment (E), and the second shaft segment (D) are integrally formed and can conduct heat between each other. The axial side of the thrust section (E) facing the first shaft section (C) is a first thrust plate surface (0107), and the axial side of the thrust section (E) facing the second shaft section (D) is a second thrust plate surface (0108). Cooling gas can be introduced into the radial outer periphery of the thrust section (E) and can be divided into at least two streams. One stream can pass through the first thrust plate surface (0107) and reach the outer peripheral wall of the first shaft section (C), and the other stream can pass through the second thrust plate surface (0108) and reach the outer peripheral wall of the second shaft section (D). The first shaft segment (C) has a first inner shaft hole (0102) extending along the axial direction, and the second shaft segment (D) has a second inner shaft hole (0103) extending along the axial direction. The first inner shaft hole (0102) extends to the inner circumference of the thrust segment (E) and communicates with the second inner shaft hole (0103). The first shaft segment (C) also has a first flow hole (0101) that penetrates its inner and outer peripheral walls. The first flow hole (0101) is connected to the first... The shaft inner hole (0102) is connected so that the cooling gas of the outer peripheral wall of the first shaft segment (C) can be introduced into the first shaft inner hole (0102) and enter the second shaft inner hole (0103). The second shaft segment (D) is also provided with a second flow hole (0104) through its inner and outer peripheral walls. The second flow hole (0104) is connected to the second shaft inner hole (0103) so that the cooling gas of the outer peripheral wall of the second shaft segment (D) can be introduced into the second shaft inner hole (0103). The first flow hole (0101) is positioned close to the thrust section (E) relative to the second flow hole (0104), such that the gas entering the first shaft inner hole (0102) through the first flow hole (0101) flows into the second shaft inner hole (0103) and mixes with the gas entering the second shaft inner hole (0103) through the second flow hole (0104). After mixing, the mixture is discharged through the axial end of the second shaft section (D) away from the thrust section (E).

2. The turbine drive shaft according to claim 1, characterized in that: There are multiple first flow holes (0101), and the multiple first flow holes (0101) are distributed at intervals along the circumferential direction of the first shaft segment (C); there are multiple second flow holes (0104), and the multiple second flow holes (0104) are distributed at intervals along the circumferential direction of the second shaft segment (D).

3. The turbine drive shaft according to claim 1, characterized in that: The outer diameter of the first shaft segment (C) is smaller than the outer diameter of the second shaft segment (D), the outer diameter of the second shaft segment (D) is smaller than the outer diameter of the thrust segment (E), the inner diameter of the first shaft segment (C) is smaller than the inner diameter of the second shaft segment (D), and the outer diameter of the first shaft segment (C) is smaller than the inner diameter of the second shaft segment (D).

4. The turbine drive shaft according to claim 1, characterized in that: The outer diameter of the second shaft segment (D) is D0, the diameter of the first flow hole (0101) is D1, and D1 / D0 = 0.02~0.2, and the diameter of the second flow hole (0104) is D2, and D2 / D0 = 0.02~0.

2.

5. The turbine drive shaft according to claim 1, characterized in that: The distance between the first flow hole (0101) and the second thrust plate surface (0108) of the thrust section (E) along the axial direction is L1, the distance between the second flow hole (0104) and the second thrust plate surface (0108) of the thrust section (E) along the axial direction is L2, the outer diameter of the second shaft section (D) is D0, and L1 / D0 = 0.05~0.5, L2 / D0 = 0.4~2.

0.

6. An air circulator, characterized in that: The turbine drive shaft, including any one of claims 1-5, further includes a first thrust bearing (04) and a second thrust bearing (05). The first thrust bearing (04) is disposed on the outer periphery of the first shaft segment (C) and faces the first thrust plate (0107) to perform a thrusting action on the thrust segment (E). The second thrust bearing (05) is disposed on the outer periphery of the second shaft segment (D) and faces the second thrust plate (0108) to perform a thrusting action on the thrust segment (E). One stream of the cooling gas introduced into the radial outer periphery of the thrust segment (E) can enter the first gap between the first thrust plate (0107) and the first thrust bearing (04) for cooling, and then reach the outer peripheral wall of the first shaft segment (C). Another stream can enter the second gap between the second thrust plate (0108) and the second thrust bearing (05) for cooling, and then reach the outer peripheral wall of the second shaft segment (D).

7. The air circulator according to claim 6, characterized in that: The outer periphery of the second shaft segment (D) is also provided with a radial bearing (06), and there is a third gap between the first thrust bearing (04) and the first shaft segment (C). The first flow hole (0101) and the first thrust bearing (04) are radially opposite each other. The first gap is connected to the first flow hole (0101) through the third gap, so that the gas cooled and heat-exchanged after passing through the first gap enters the first shaft inner hole (0102) through the first flow hole (0101). There is a fourth gap between the second thrust bearing (05) and the second shaft segment (D), and a fifth gap between the radial bearing (06) and the second shaft segment (D). The second gap, the fourth gap and the fifth gap are connected in sequence, so that the gas cooled and heat-exchanged through the second gap enters the fourth gap and the fifth gap in sequence. The second flow hole (0104) is provided on the axial side of the radial bearing (06) away from the second thrust bearing (05), and the fifth gap is connected to the second shaft inner hole (0103) through the second flow hole (0104).

8. The air circulator according to claim 7, characterized in that: The axial end of the radial bearing (06) away from the second thrust bearing (05) does not extend beyond the second flow hole (0104), so that the second flow hole (0104) is not opposite to the radial bearing (06).

9. The air circulator according to any one of claims 6-8, characterized in that: A compressor impeller (03) is connected to one end of the second shaft segment (D) away from the thrust segment (E). The compressor impeller (03) has a compressor impeller inner hole (0301). The end of the second shaft inner hole (0103) away from the first shaft segment (C) communicates with the compressor impeller inner hole (0301), so that the gas entering the first shaft inner hole (0102) and the gas entering the second shaft inner hole (0103) both enter the compressor impeller inner hole (0301) through the second shaft inner hole (0103).

10. The air circulator according to any one of claims 6-8, characterized in that: The outer periphery of the thrust section (E) has a cavity (Q01). The air circulator includes an expander and a connecting structure (07). The expander includes an expander volute (F). An expander inlet (T01) is provided on the expander volute (F). A first channel (T0101) and a second channel (T0102) are provided on the expander volute (F). The first channel (T0101) can connect part of the gas inside the expander volute (F) inlet to the outside. The second channel (T0102) can connect the gas outside the expander volute (F) to the cavity (Q01). The connecting structure (07) is connected to the expander volute (F), and the channel inside the connecting structure (07) connects the first channel (T0101) and the second channel (T0102).

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