Turbine mechanism and steam turbine system

Abstract

This application relates to the field of heat engine equipment technology, and in particular to turbine mechanisms and steam turbine systems. It includes a cylinder block, a rotating shaft, a first turbine assembly, and a second turbine assembly. The rotating shaft extends through the cylinder block along a first direction. The second turbine assembly is positioned opposite to the first turbine assembly along the first direction. A first air inlet is located between the first and second turbine assemblies, and a first exhaust port is located at the end of the second turbine assembly furthest from the first turbine assembly. Airflow entering from the first air inlet passes through the first and second turbine assemblies and exits the cylinder block through the first exhaust port. This turbine mechanism maintains the high efficiency of a large turbine by only reversing the orientation of the second turbine assembly, making it opposite to the first turbine assembly, thus achieving forward and reverse flow of supercritical carbon dioxide, balancing axial thrust, reducing the number of equipment and connecting parts, lowering costs and energy losses, simplifying the control system, and improving operational stability and maintenance convenience.

Description

Technical Field

[0001] This application relates to the field of heat engine equipment technology, and in particular to turbine mechanisms and steam turbine systems. Background Technology

[0002] Traditional steam turbine systems achieve energy conversion by having supercritical carbon dioxide flow through the turbine mechanism.

[0003] A traditional steam turbine system includes a shaft, a first turbine assembly, and a second turbine assembly. Supercritical carbon dioxide is supplied to both the first and second turbine assemblies, expands within them to perform work, and is then discharged through an exhaust system. This parallel configuration requires additional piping and valves to distribute and collect the supercritical carbon dioxide, and a control system to coordinate the operation of the two small turbines. The first and second turbine assemblies are coaxial, arranged in opposite directions, and have the same intake volume to cancel out axial thrust and ensure the safety of the turbine unit.

[0004] However, in the aforementioned steam turbine system, the structure of the first turbine assembly and the second turbine assembly diverts supercritical carbon dioxide, resulting in a decrease in expansion power, reduced system output power, and structural complexity. Summary of the Invention

[0005] Therefore, it is necessary to provide a turbine mechanism and steam turbine system to address the problems of reduced expansion power, decreased system output power, and complex structure.

[0006] A turbine mechanism, comprising:

[0007] A cylinder block, the cylinder block defining a first air inlet and a first exhaust outlet;

[0008] A rotating shaft that extends through the cylinder body along a first direction;

[0009] A first turbine assembly is mounted on the shaft;

[0010] A second turbine assembly is disposed on the rotating shaft, and the second turbine assembly is disposed opposite to the first turbine assembly along the first direction;

[0011] The first air inlet is located between the first turbine assembly and the second turbine assembly, and the first exhaust port is located at the end of the second turbine assembly away from the first turbine assembly. The airflow entering from the first air inlet passes through the first turbine assembly and the second turbine assembly, and is discharged from the cylinder block through the first exhaust port.

[0012] In one embodiment, the first turbine assembly includes:

[0013] The first stationary vane is disposed on the inner wall of the cylinder;

[0014] The first mover is disposed on the rotating shaft, and the first air inlet is located on the side of the first stator vane away from the first mover;

[0015] A flow guide extends from the side of the first mover away from the first stator blade towards the second turbine assembly, and the flow guide is in communication with the second turbine assembly;

[0016] The second turbine assembly includes:

[0017] The second stationary vane is disposed on the inner wall of the cylinder;

[0018] The second mover is disposed on the rotating shaft and is located on the side of the second stator vane away from the first turbine assembly.

[0019] In one embodiment, the first stator vane and the first mover are in multiple groups, and each group of the first stator vane and each group of the first mover are alternately arranged in a direction away from the first air inlet.

[0020] And / or, the second stationary blade and the second mover are in multiple groups, with each group of the second stationary blade and each group of the second mover being alternately arranged in a direction away from the first turbine assembly.

[0021] In one embodiment, the first mover includes a plurality of first moving blades, which are circumferentially spaced along the rotating shaft. There are a plurality of guide tubes, which are axially spaced along the rotating shaft. One end of each guide tube corresponds to the spacing between two adjacent first moving blades, and the other end of each guide tube is located at the end of the second turbine assembly near the first turbine assembly.

[0022] In one embodiment, the flow guide includes:

[0023] A connecting portion is located on the inner wall of the cylinder body. One end of the connecting portion is a second exhaust port, which is located at the end of the second turbine assembly close to the first turbine assembly. The other end extends in the direction away from the exhaust end of the first turbine assembly.

[0024] The bending section has one end as a second air inlet and the other end connected to the end of the connecting section away from the second turbine assembly.

[0025] In one embodiment, the number of stages of the first stator cascade and the first mover in the first turbine assembly is the same as the number of stages of the second stator cascade and the second mover in the second turbine assembly.

[0026] In one embodiment, the turbine mechanism further includes:

[0027] A partition is disposed perpendicular to the rotating shaft and sleeved on the rotating shaft. The partition divides the cylinder into a first chamber and a second chamber. The first turbine assembly is located in the first chamber, and the second turbine assembly is located in the second chamber.

[0028] In one embodiment, the inner diameter of the first chamber gradually increases in the direction away from the second turbine assembly;

[0029] And / or, along a direction away from the first turbine assembly, the inner diameter of the second chamber gradually increases.

[0030] In one embodiment, the turbine mechanism further includes an intake pipe, which is a bend that bends within the cylinder toward the first turbine assembly.

[0031] And / or, the turbine mechanism further includes two intake pipes, which are spaced apart circumferentially along the cylinder body.

[0032] A steam turbine system including the turbine mechanism as described above.

[0033] The aforementioned turbine mechanism and steam turbine system include a cylinder block, a rotating shaft, a first turbine assembly, and a second turbine assembly. The rotating shaft extends through the cylinder block along a first direction. The first turbine assembly and the second turbine assembly are mounted on the rotating shaft, and are positioned opposite each other along the first direction. A first air inlet is located between the first and second turbine assemblies, and a first exhaust port is located at the end of the second turbine assembly furthest from the first turbine assembly. Airflow entering from the first air inlet passes through the first and second turbine assemblies and exits the cylinder block through the first exhaust port. During the operation of the turbine mechanism, supercritical carbon dioxide flows through the first and second turbine assemblies, and through staged expansion, the thermal energy contained in the supercritical carbon dioxide is efficiently converted into mechanical energy, thereby driving the rotating shaft to rotate at high speed, achieving efficient energy conversion. This turbine mechanism integrates two turbine assemblies, has high energy conversion efficiency, and offers significant advantages in miniaturization and high efficiency, making it suitable for various energy conversion scenarios. This turbine mechanism maintains the high efficiency of a large turbine by only reversing the second turbine component to make it opposite to the first turbine component, thereby achieving the forward and reverse flow of supercritical carbon dioxide, balancing the axial thrust, reducing the number of equipment and connecting parts, lowering costs and energy losses, simplifying the control system, and improving operational stability and maintenance convenience. Attached Figure Description

[0034] Figure 1This is a schematic diagram of the turbine mechanism provided in one embodiment of this application.

[0035] Figure 2 This is a cross-sectional structural diagram of a turbine mechanism provided in one embodiment of this application.

[0036] Explanation of reference numerals in the attached figures:

[0037] 100 - Cylinder block; 110 - First air intake port; 120 - First exhaust port; 130 - First chamber; 140 - Second chamber;

[0038] 200-spindle;

[0039] 300 - First turbine assembly; 310 - First stator vane; 320 - First mover; 330 - Guide tube; 331 - Connecting part; 332 - Bending part; 333 - Second air inlet; 334 - Second exhaust port;

[0040] 400 - Second turbine assembly; 410 - Second stator vane; 420 - Second mover;

[0041] 500-partition;

[0042] 600 - Intake pipe. Detailed Implementation

[0043] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0044] In the description of this application, it should be understood that if terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and 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 of this application.

[0045] Furthermore, where the terms "first" and "second" appear, these terms are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, where the term "multiple" appears, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0046] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0047] In this application, unless otherwise expressly specified and limited, the use of descriptions such as "above" or "below" the second feature indicates that the first and second features are in direct contact or indirect contact via an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. Similarly, "below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0048] It should be noted that if an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. If an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. If so, the terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application are for illustrative purposes only and do not represent the only possible implementation.

[0049] See Figures 1-2 , Figure 1 A schematic diagram of the turbine mechanism provided in one embodiment of this application is shown. Figure 2 A cross-sectional structural schematic diagram of a turbine mechanism provided in one embodiment of this application is shown.

[0050] like Figure 1As shown, the turbine mechanism includes a cylinder 100, which defines a first air inlet 110 and a first exhaust port 120. The working fluid enters the cylinder 100 through the first air inlet 110 and exits through the first exhaust port 120. In this embodiment, the working fluid is supercritical carbon dioxide. Supercritical carbon dioxide combines the low viscosity of a gas with the high density of a liquid. This characteristic allows it to significantly reduce flow resistance and improve heat transfer efficiency when flowing in a turbine, while also reducing equipment size and manufacturing costs.

[0051] Such as 1 and Figure 2 As shown, the turbine mechanism also includes a rotating shaft 200, a first turbine assembly 300, and a second turbine assembly 400. The rotating shaft 200 passes through the cylinder block 100 along a first direction. The first turbine assembly 300 is disposed on the rotating shaft 200, and the second turbine assembly 400 is disposed on the rotating shaft 200. The second turbine assembly 400 and the first turbine assembly 300 are disposed opposite to each other along the first direction. The first air inlet 110 is located between the first turbine assembly 300 and the second turbine assembly 400. The first exhaust port 120 is located at the end of the second turbine assembly 400 away from the first turbine assembly 300. The airflow entering from the first air inlet 110 passes through the first turbine assembly 300 and the second turbine assembly 400, and is discharged from the cylinder block 100 through the first exhaust port 120. During the operation of the turbine mechanism, supercritical carbon dioxide flows through the first turbine component 300 and the second turbine component 400. Through staged expansion, the thermal energy contained in the supercritical carbon dioxide is efficiently converted into mechanical energy, which in turn drives the rotating shaft 200 to rotate at high speed, achieving efficient energy conversion. This turbine mechanism integrates two turbine components, has high energy conversion efficiency, and has significant advantages in miniaturization and high efficiency, making it suitable for various energy conversion scenarios.

[0052] Because supercritical carbon dioxide generates a certain axial thrust along the shaft 200 when performing work, this turbine mechanism, with the first turbine assembly 300 and the second turbine assembly 400 positioned opposite each other, helps to counteract the axial thrust of the first turbine assembly 300 and the second turbine assembly 400. Compared to related technologies that require two small turbines to balance the axial thrust, this turbine mechanism maintains the high efficiency of a large turbine. It achieves forward and reverse flow of supercritical carbon dioxide by only using the second turbine assembly 400 in reverse configuration, opposite to the first turbine assembly 300, thus balancing the axial thrust. This also reduces the number of equipment and connecting parts, lowers costs and energy losses, simplifies the control system, and improves operational stability and maintenance convenience.

[0053] Meanwhile, when the total supply of supercritical carbon dioxide is the same, dividing it into two parts and supplying them to two turbines results in smaller turbine structures and reduced power output from the expansion of supercritical carbon dioxide within the two smaller turbines. In this embodiment, however, because the turbine mechanism maintains the expansion work of a single large turbine, the same supply of supercritical carbon dioxide is directly supplied to this mechanism without diversion. This improves the efficiency of the turbine mechanism and avoids the efficiency reduction and structural complexity issues caused by the smaller turbine power in related technologies that use two smaller turbines.

[0054] Specifically, this turbine mechanism can replace two small turbines, eliminating the need for separate intake and exhaust systems, additional pipes, valves, etc. This simplifies the structure, reduces costs, and facilitates maintenance, thereby lowering repair difficulty and time, and ultimately reducing maintenance costs. Furthermore, by simplifying the structure, this turbine mechanism reduces the number of bends, interfaces, and throttling elements that supercritical carbon dioxide needs to pass through during flow, thus reducing flow resistance and energy loss.

[0055] As a key component for working fluid transmission, the outer cylinder has its inner surface precisely machined to an IT5 level of precision to ensure that the concentricity error with the rotating shaft 200 does not exceed 0.02mm, and the inner surface roughness Ra≤0.8μm to ensure the smooth flow of the working fluid.

[0056] Specifically, the first air inlet 110 is connected to the first turbine assembly 200, the first turbine assembly 200 is connected to the second turbine assembly 300, and the second turbine assembly 300 is connected to the first exhaust port 120.

[0057] In one embodiment, the first turbine assembly 300 includes a first stator vane 310, a first rotor 320, and a guide pipe 330. The first stator vane 310 is disposed on the inner wall of the cylinder 100; the first rotor 320 is disposed on the rotating shaft 200, and the first air inlet 110 is located on the side of the first stator vane 310 away from the first rotor 320; the guide pipe 330 extends from the side of the first rotor 320 away from the first stator vane 310 toward the second turbine assembly 400, and the guide pipe 330 communicates with the second turbine assembly 400. Supercritical carbon dioxide flows sequentially from the air inlet through the first stator vane 310 and the first rotor, expands and performs work, driving the first rotor 320 to rotate the rotating shaft 200.

[0058] Optionally, a certain gap is maintained between the first stationary vane 310 and the rotating shaft 200, and a certain gap is maintained between the first rotor 320 and the inner wall of the cylinder 100, so that the supercritical carbon dioxide expands as much as possible through the first stationary vane 310 and the diameter of the first rotor, avoiding flow in the gap.

[0059] The second turbine assembly 400 includes a second stator vane 410 and a second mover 420. The second stator vane 410 is disposed on the inner wall of the cylinder block 100; the second mover 420 is disposed on the rotating shaft 200, and the second mover 420 is located on the side of the second stator vane 410 away from the first turbine assembly 300, thus forming a situation where the second turbine assembly 400 and the first turbine assembly 300 are arranged opposite to each other. The supercritical carbon dioxide gas that has been expanded in the first turbine assembly 300 flows back into the second turbine assembly 400, and further expands under the action of the second stator vane 410, driving the second mover 420 to rotate, thereby driving the bearing to rotate.

[0060] Optionally, a certain gap is maintained between the second stator vane 410 and the rotating shaft 200, and a certain gap is maintained between the second mover 420 and the inner wall of the cylinder 100, so that the supercritical carbon dioxide expands as much as possible through the second stator vane 410 and the diameter of the second rotor, avoiding flow in the gap.

[0061] Since the first stationary blade 310 and the first mover 320 are arranged facing the second stationary blade 410 and the second mover 420, the axial thrust generated by them is in opposite directions, thus achieving a canceling effect.

[0062] Optionally, the first air inlet 110 is connected through a pipeline inside the cylinder block 100. The first air inlet 110 bends toward the first turbine assembly 300, so that after supercritical carbon dioxide enters the cylinder block 100, it flows directly toward the first turbine assembly 300 and expands.

[0063] Furthermore, the first stationary vane 310 includes multiple stationary vanes, which are spaced apart along the inner wall of the cylinder body 100. The first mover 320 includes multiple moving vanes, which are also spaced apart along the inner wall of the cylinder body 100. The stationary vanes form a certain angle with the airflow direction flowing into the first air inlet 110, causing supercritical carbon dioxide to collide with the first stationary vanes at a certain angle. Then, the airflow within the first stationary vane 310 and the first mover 320 drives the first mover 320 to rotate, thereby driving the rotating shaft 200 to rotate.

[0064] The cross-sectional shape of the stationary blades is similar to that of a crescent moon, and the bending direction of multiple stationary blades is the same. The cross-sectional shape of the moving blades is also crescent moon, and the bending direction of the moving blades is opposite to that of the stationary blades. The spacing between the moving blades and the two adjacent stationary blades is set accordingly.

[0065] Meanwhile, the structure of the second stationary blade 410 is the same as that of the first stationary blade 310, and the structure of the second mover 420 is the same as that of the first mover 320, only the direction is reversed, which will not be described in detail here.

[0066] In one embodiment, the first stator vane 310 and the first mover 320 are in multiple groups, with each group of first stator vane 310 and each group of first movers 320 alternately arranged in a direction away from the first air inlet 110. Each group of first stator vane 310 and each group of first movers 320 constitutes a stage, thus forming a multi-stage arrangement of the first turbine assembly 300, which is beneficial for improving the expansion effect of supercritical carbon dioxide in the first turbine assembly 300. Adjacent stages are arranged closely together.

[0067] Optionally, the second stator vane 410 and the second mover 420 are each in multiple groups, with each group of second stator vane 410 and each group of second movers 420 alternately arranged in a direction away from the first turbine assembly 300. Similar to the first turbine assembly 300, one group of second stator vane 410 and one group of second movers 420 constitute one stage, thereby forming a multi-stage arrangement of the second turbine assembly 400. Adjacent stages are arranged closely together.

[0068] During operation, supercritical carbon dioxide enters the first turbine assembly 300 through the intake port and flows through the first stator vane 310 and the first rotor in stages. After exiting the first rotor at the last stage, it changes direction through the guide pipe 330 and flows to the second turbine assembly 400. In the second turbine assembly 400, the supercritical carbon dioxide then flows through the second stator vane 410 and the second rotor in stages, and finally exits the cylinder block 100 through the exhaust port.

[0069] Since the axial thrust caused by supercritical carbon dioxide at the first turbine assembly 300 and the second turbine assembly 400 is in opposite directions, the thrust is eliminated.

[0070] As an alternative, the number of stages of the first stator vane 310 and the first mover 320 in the first turbine assembly 300 is the same as the number of stages of the second stator vane 410 and the second mover 420 in the second turbine assembly 400. This helps to ensure that the axial thrust between the first turbine assembly 300 and the second turbine assembly 400 is the same but in opposite directions, so as to cancel each other out.

[0071] In another embodiment, the turbine mechanism can adjust the axial thrust between the first turbine assembly 300 and the second turbine assembly 400 by changing the size and angle of the first stator vane 310 and the second stator vane 410, so that the axial thrust values ​​of the two are as similar as possible or substantially the same, but in opposite directions, even when the two are of different stages, thereby achieving axial thrust cancellation.

[0072] Optionally, multiple guide tubes 330 are provided, spaced circumferentially along the rotating shaft 200. One end of each guide tube 330 corresponds to the spacing between two adjacent moving blades, and the other end of each guide tube 330 is located at the end of the second turbine assembly 400 near the first turbine assembly 300. The guide tube 330 serves to guide airflow between the first turbine assembly 300 and the second turbine assembly 400, thereby guiding the gas flowing from the first mover 320 to the inlet end of the second turbine assembly 400. For example, the number of guide tubes 300 is the same as the number of moving blades.

[0073] The guide pipe 330 includes a connecting portion 331 and a bent portion 332. The connecting portion 331 is located on the inner wall of the cylinder block 100. One end of the connecting portion 331 is a second exhaust port 334, located at the end of the second turbine assembly 400 near the first turbine assembly 300, and the other end extends towards the exhaust end of the first turbine assembly 300. One end of the bent portion 332 is a second air inlet 333, and the other end is connected to the end of the connecting portion 331 away from the second turbine assembly 400. The guide pipe 330 uses the bent portion 332 to guide the airflow, thereby changing the airflow direction to connect the first turbine assembly 300 and the second turbine assembly 400, reducing energy waste caused by airflow dispersion. The guide pipe 330 can effectively guide supercritical carbon dioxide from axial flow in the first turbine assembly 300 to radial flow, and smoothly guide it to the connecting pipe between the cylinder block 100 and the second turbine assembly 400.

[0074] For example, in this embodiment, the cross-sectional shape of the guide tube 330 is circular. In other embodiments, the cross-sectional shape of the guide tube 330 can be any shape such as square or elliptical, and this embodiment does not limit this.

[0075] More specifically, the distance between the second air inlet 333 of the guide pipe 330 and the downstream of the first mover 320 of the final stage is 5mm-8mm. The inner diameter and wall thickness of the guide pipe 330 are selected in conjunction with the rated power and temperature difference level of the turbomachinery, and this embodiment does not limit them.

[0076] During the operation of the aforementioned turbine mechanism, supercritical carbon dioxide working fluid first enters the first turbine assembly 300 through the first inlet 110, flows sequentially through multiple stages of the first stator vane 310 and the first mover 320, expands and performs work within the first turbine assembly 300, converting the thermal energy of the working fluid into mechanical energy, driving the rotating shaft 200 to rotate at high speed. After performing work in the first stage, the working fluid changes its flow direction through the guide pipe 330 and enters the second turbine assembly 400. In the second turbine assembly 400, the working fluid again flows through multiple stages of the second stator vane 410 and the second mover 420, expanding and performing work in the opposite direction to that in the first turbine assembly 300.

[0077] Because the first turbine assembly 300 and the second turbine assembly 400 are arranged in opposite directions, the axial thrust generated when the working fluid flows in the first turbine assembly 300 is in the opposite direction to the axial thrust generated when it flows in the second turbine assembly 400. Through precise design and optimization of the working fluid flow rate, flow parameters, and turbine structure, the axial thrust generated by the first turbine assembly 300 and the second turbine assembly 400 is made approximately equal in magnitude and opposite in direction, thus achieving effective balance of the turbine rotor's axial thrust. This axial thrust balancing method not only improves the stability and safety of turbine operation but also reduces reliance on supporting components such as thrust bearings, thereby lowering energy loss, equipment wear, and maintenance costs.

[0078] Meanwhile, this turbine mechanism, by dividing the multi-stage axial flow turbine into a first turbine assembly 300 and a second turbine assembly 400, and employing a working fluid transmission and steering system composed of key components such as an outer cylinder, a guide pipe 330, and a flow guiding device, achieves forward and reverse flow of the supercritical carbon dioxide working fluid, thereby balancing the axial thrust of the turbine. Compared with existing technologies, the arrangement in this embodiment avoids the problems of low efficiency, complex structure, high cost, and large energy loss caused by dividing the turbine into multiple small turbines, improving the overall performance and operating efficiency of the turbine, and providing an innovative solution for the development of supercritical carbon dioxide axial flow turbine technology.

[0079] The supercritical carbon dioxide used in the turbine mechanism in this embodiment does not cause the power to be halved due to splitting, thus avoiding the low efficiency of low-power turbines and effectively improving the turbine's operating efficiency, giving full play to the turbine's performance advantages.

[0080] In one embodiment, the turbine mechanism further includes a partition 500, which is disposed perpendicular to and sleeved on the rotating shaft 200. The partition 500 divides the cylinder 100 into a first chamber 130 and a second chamber 140. A first turbine assembly 300 is located in the first chamber 130, and a second turbine assembly 400 is located in the second chamber 140. The partition 500 is used to isolate the first turbine assembly 300 and the second turbine assembly 400, so that the airflow of the first turbine assembly 300 and the second turbine assembly 400 is independent and avoids mutual disturbance.

[0081] In one embodiment, the inner diameter of the first chamber 130 gradually increases in the direction away from the second turbine assembly 400, providing flow space for supercritical carbon dioxide expansion.

[0082] Optionally, the inner diameter of the second chamber 140 gradually increases in the direction away from the first turbine assembly 300, providing flow space for supercritical carbon dioxide expansion, thereby further providing flow space for supercritical carbon dioxide expansion.

[0083] Meanwhile, through the above structure, the position corresponding to the first air inlet 110 on the cylinder 100 is the position with the smallest diameter of the cylinder 100. That is, the gas flowing out from the first turbine assembly 300 is transported to the position of the second chamber 140 with a smaller diameter under the action of the guide pipe 330, which is beneficial for the second chamber 140 to provide space for the further expansion of supercritical carbon dioxide.

[0084] Optionally, the turbine mechanism also includes an intake pipe 600, which is a bent pipe. The intake pipe 600 bends in the direction of the first turbine assembly 300 within the cylinder 100, thereby allowing high-pressure supercritical carbon dioxide gas to be directly delivered to the first turbine assembly 300, reducing the disturbance of gas flow in other directions within the cylinder 100.

[0085] Optionally, there are two intake pipes 600, which are arranged at intervals along the circumference of the cylinder 100, so that the working fluid expands uniformly in the circumferential space inside the cylinder 100.

[0086] This embodiment also provides a steam turbine system, which includes the aforementioned turbine mechanism.

[0087] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0088] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A turbine mechanism, characterized in that, include: A cylinder block, the cylinder block defining a first air inlet and a first exhaust outlet; A rotating shaft that extends through the cylinder body along a first direction; A first turbine assembly is mounted on the shaft; A second turbine assembly is disposed on the rotating shaft, and the second turbine assembly is disposed opposite to the first turbine assembly along the first direction; The first air inlet is located between the first turbine assembly and the second turbine assembly, and the first exhaust port is located at the end of the second turbine assembly away from the first turbine assembly. The airflow entering from the first air inlet passes through the first turbine assembly and the second turbine assembly, and is discharged from the cylinder block through the first exhaust port.

2. The turbine mechanism according to claim 1, characterized in that, The first turbine assembly includes: The first stationary vane is disposed on the inner wall of the cylinder; The first mover is disposed on the rotating shaft, and the first air inlet is located on the side of the first stator vane away from the first mover; A flow guide extends from the side of the first mover away from the first stator blade towards the second turbine assembly, and the flow guide is in communication with the second turbine assembly; The second turbine assembly includes: The second stationary vane is disposed on the inner wall of the cylinder; The second mover is disposed on the rotating shaft and is located on the side of the second stator vane away from the first turbine assembly.

3. The turbine mechanism according to claim 2, characterized in that, The first stationary vane and the first mover are in multiple groups, and each group of the first stationary vane and the first mover are alternately arranged in a direction away from the first air inlet. And / or, the second stationary blade and the second mover are in multiple groups, with each group of the second stationary blade and each group of the second mover being alternately arranged in a direction away from the first turbine assembly.

4. The turbine mechanism according to claim 2, characterized in that, The first mover includes a plurality of first moving blades, which are spaced apart along the axial direction of the rotating shaft. There are a plurality of guide tubes, which are spaced apart circumferentially along the rotating shaft. One end of each guide tube is positioned at a distance corresponding to the interval between two adjacent first moving blades, and the other end of each guide tube is located at the end of the second turbine assembly near the first turbine assembly.

5. The turbine mechanism according to claim 2, characterized in that, The flow guide tube includes: A connecting portion is located on the inner wall of the cylinder body. One end of the connecting portion is a second exhaust port, which is located at the end of the second turbine assembly close to the first turbine assembly. The other end extends in the direction away from the exhaust end of the first turbine assembly. The bending section has one end as a second air inlet and the other end connected to the end of the connecting section away from the second turbine assembly.

6. The turbine mechanism according to claim 3, characterized in that, The number of stages of the first stator vane and the first mover in the first turbine assembly is the same as the number of stages of the second stator vane and the second mover in the second turbine assembly.

7. The turbine mechanism according to any one of claims 1-6, characterized in that, The turbine mechanism also includes: A partition is disposed perpendicular to the rotating shaft and sleeved on the rotating shaft. The partition divides the cylinder into a first chamber and a second chamber. The first turbine assembly is located in the first chamber, and the second turbine assembly is located in the second chamber.

8. The turbine mechanism according to claim 7, characterized in that, Along the direction away from the second turbine assembly, the inner diameter of the first chamber gradually increases; And / or, along a direction away from the first turbine assembly, the inner diameter of the second chamber gradually increases.

9. The turbine mechanism according to any one of claims 1-6, 8, characterized in that, The turbine mechanism also includes an intake pipe, which is a bent pipe that bends in the cylinder body toward the first turbine assembly. And / or, the turbine mechanism further includes two intake pipes, which are spaced apart circumferentially along the cylinder body.

10. A steam turbine system, characterized in that, Includes the turbine mechanism as described in any one of claims 1-9.

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