Turbine cooling structure and method, brayton power cycle system

Abstract

The application provides a turbine cooling structure and method and a Brayton power generation cycle system. The turbine cooling structure comprises three or more turbine discs, each of which is provided with a plurality of forward balance holes and reverse balance holes. The airflow direction in the forward balance holes is the same as the turbine main stream gas flow direction, and the airflow direction in the reverse balance holes is opposite to the turbine main stream gas flow direction. The reverse balance holes on the reverse side of the last stage turbine disc are provided with bleed air grooves in the radial direction, which are communicated with the hollow cavities of the last stage exhaust connection section. The forward balance holes on the reverse side of the last stage turbine disc are provided with bleed air grooves in the radial direction, which are communicated with the turbine disc rim. The forward balance holes and the reverse balance holes on the front side of the first stage turbine disc are provided with bleed air grooves in the radial direction, which are communicated with the hollow cavities of the first stage intake connection section. The forward balance holes of adjacent turbine discs are communicated with each other, and the reverse balance holes of adjacent turbine discs are communicated with each other. The application can significantly increase the contact area of the cooling gas and the turbine disc in a limited space, which helps to improve the cooling effect and ensure the long-term safe and stable operation of the turbine.

Description

Technical Field

[0001] This invention relates to the field of power generation technology, and in particular to a turbine cooling structure and method, as well as a Brayton power generation cycle system. Background Technology

[0002] The closed-loop helium Brayton cycle is an ideal heat-to-work conversion system for high-temperature nuclear energy, using helium as the working fluid. It is integrated directly or indirectly with the reactor core and can be widely applied to various fourth-generation high-temperature nuclear reactor types, including gas-cooled fast reactors, thorium-based molten salt reactors, and ultra-high-temperature gas-cooled reactors, as well as future high-temperature nuclear fission reactors. Compared to traditional nuclear power plants, the closed-loop helium Brayton cycle features a compact structure, high power generation efficiency, and high safety. Theoretically, it can achieve a power generation efficiency of up to 50% when the core outlet temperature reaches 950°C.

[0003] From a thermodynamic cycle perspective, the Brayton cycle includes four thermodynamic processes: adiabatic compression, isobaric heating, adiabatic expansion, and isobaric cooling. To improve cycle efficiency, regeneration and intercooling are often added. The core equipment of a closed-loop helium Brayton cycle power generation system mainly includes a low-pressure compressor, a high-pressure compressor, a turbine, a precooler, an intercooler, and a regenerator. Among these, the turbine is a key component that converts the energy of high-temperature, high-pressure helium into mechanical energy (electrical energy). It is a typical hot-end component, similar to aircraft engines and ground gas turbines. To ensure high-intensity operation, helium turbines require cooling of their turbine disks. However, compared to turbines using air as the working fluid, helium has poor compressibility, necessitating a significant increase in compressor speed to achieve the design pressure ratio. This also increases the speed of the helium turbine coaxial with the compressor, further increasing the centrifugal load on the turbine disk. Combined with the high operating temperature, this ultimately reduces the safe operating coefficient of the helium turbine disk. Therefore, improving the turbine cooling structure and methods to ensure the long-term safe and stable operation of the helium turbine disk is essential.

[0004] It should be noted that the above introduction to the technical background is only for the purpose of providing a clear and complete explanation of the technical solutions of this application and facilitating understanding by those skilled in the art. It should not be assumed that these technical solutions are known to those skilled in the art simply because they have been described in the background section of this application. Summary of the Invention

[0005] In view of the shortcomings of the prior art described above, the purpose of this invention is to provide a turbine cooling structure and method, as well as a Brayton power generation cycle system, to improve the cooling effect of the turbine disk and ensure that the helium turbine disk can work safely and stably for a long time.

[0006] To achieve the above and other related objectives, the present invention provides a turbine cooling structure comprising three or more turbine disks. Each turbine disk is provided with multiple forward balancing holes and multiple reverse balancing holes. The airflow direction inside the forward balancing holes is the same as the mainstream gas flow direction of the turbine, and the airflow direction inside the reverse balancing holes is opposite to the mainstream gas flow direction of the turbine. The reverse balancing holes on the reverse side of the last-stage vortex disk have radially opened air intake grooves communicating with the hollow cavity of the last-stage exhaust connection section. The forward balancing holes on the reverse side of the last-stage vortex disk have radially opened air intake grooves communicating with the edge of the turbine disk. The forward and reverse balancing holes on the front side of the first-stage turbine disk both have air intake grooves communicating with the hollow cavity of the first-stage intake connection section. The forward balancing holes of adjacent turbine disks are interconnected, and the reverse balancing holes are interconnected.

[0007] Optionally, each turbine disk has four forward balance holes and four reverse balance holes, and the forward balance holes and reverse balance holes are evenly spaced and alternately arranged on the same circumferential surface of the turbine disk.

[0008] Optionally, no bleed slots are opened on the front and back sides of the intermediate stage turbine disk, the back side of the first stage turbine disk, and the front side of the last stage turbine disk.

[0009] Optionally, there are five or more turbine disks.

[0010] Optionally, the turbine cooling structure further includes several annular positioning disks, which are arranged one-to-one between adjacent turbine disks. The positioning disks are provided with openings that connect the forward balance holes and reverse balance holes of adjacent turbine disks respectively.

[0011] Optionally, the outer end face of the positioning disk is U-shaped, and the inner end face of the positioning disk is provided with an opening that communicates with the opening and is used to introduce cooling gas into the disk cavity of the positioning disk.

[0012] Optionally, the turbine cooling structure further includes several bleed air rings, which are interference-fitted with the positioning disk to connect the reverse balance holes of the intermediate stage turbine disk.

[0013] Optionally, sealing teeth are provided on the outer peripheral surface of the connection between adjacent turbine disks.

[0014] The present invention also provides a turbine cooling method, which is based on the turbine cooling structure described in any of the preceding claims. The turbine cooling method includes: passing cooling gas through an exhaust connection section, entering the reverse balance hole of the last-stage turbine disk through an air intake groove, and flowing sequentially through the reverse balance holes of each intermediate stage to the first-stage turbine disk; then entering the hollow cavity of the intake connection section through an air intake groove on the front side of the first-stage turbine disk; entering the forward balance hole of the first-stage turbine disk through a forward balance hole air intake groove; then sequentially entering the cavity between each stage of turbine disks through the forward balance holes of each intermediate stage; and finally introducing the cooling gas into the turbine mains channel through the forward balance hole air intake groove on the reverse side of the last-stage turbine disk, thereby completing the cooling of each stage of turbine disks.

[0015] The present invention also provides a Brayton cycle power generation system, the Brayton cycle power generation system including a turbine cooling structure as described in any of the above embodiments.

[0016] As described above, the turbine cooling structure and method, and the Brayton power generation cycle system of the present invention have the following beneficial effects:

[0017] The ingeniously designed structure of this invention guides the flow of cryogenic cooling gas on the turbine, significantly increasing the contact area between the cooling gas and the turbine disk within a limited space. This helps improve the cooling effect and ensures the turbine's long-term safe and stable operation. The structure is simple, easy to install and use, and contributes to the simplification of the overall equipment structure. Attached Figure Description

[0018] Figure 1 and 2 The diagram shows exemplary cross-sectional views of the turbine cooling structure provided by the present invention from different directions.

[0019] Figure 3 Displayed as Figure 1 An illustrative back-side structural diagram of the primary turbine disk.

[0020] Figure 4 Displayed as Figure 1 An illustrative front view of the primary turbine disk.

[0021] Figure 5 Displayed as Figure 1 An illustrative back-side structural diagram of the intermediate stage turbine disk.

[0022] Figure 6 Displayed as Figure 1 An illustrative front view of the intermediate stage turbine disk.

[0023] Figure 7 Displayed as Figure 1 An illustrative back-side structural diagram of the final-stage turbine disk.

[0024] Figure 8 Displayed as Figure 1 An illustrative front view of the final stage turbine disk.

[0025] Figure 9 Displayed as Figure 1 An illustrative structural diagram of the positioning disk in the diagram.

[0026] Figure 10 Displayed as Figure 1 An illustrative structural diagram of the air guide ring in the diagram. Detailed Implementation

[0027] The following specific examples illustrate the embodiments of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. For ease of explanation, when detailing the embodiments of the present invention, the cross-sectional views showing the device structure are partially enlarged, not according to the general scale, and the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. Furthermore, in actual manufacturing, the three-dimensional spatial dimensions of length, width, and depth should be included.

[0028] For ease of description, spatial relation terms such as “below,” “under,” “lower than,” “below,” “above,” and “upper” may be used herein to describe the relationship between one element or feature shown in the accompanying drawings and other elements or features. It will be understood that these spatial relation terms are intended to include directions other than those depicted in the drawings for devices in use or operation. Furthermore, when a layer is referred to as being “between” two layers, it may be the only layer between the two layers, or there may be one or more layers in between.

[0029] In the context of this application, the structure described above the first feature may include embodiments in which the first and second features are formed in direct contact, or embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact.

[0030] It should be noted that the illustrations provided in this embodiment are only schematic representations of the basic concept of the present invention. Therefore, the drawings only show components related to the present invention and are not drawn according to the actual number, shape, and size of the components in the actual implementation. In the actual implementation, the form, quantity, and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex. To keep the illustrations as concise as possible, not all structures are shown in the figures.

[0031] like Figures 1 to 10As shown, the present invention provides a turbine cooling structure, or it can be defined as a turbine with a built-in cooling structure. The turbine cooling structure includes three or more turbine disks 11. If defined by their location, these turbine disks 11 can be defined as the first-stage turbine disk 11 at the front, the last-stage turbine disk 11 at the rear, and intermediate-stage turbine disks 11 in the middle. The intermediate-stage turbine disks 11 can be single or two or more, depending on the needs, such as cooling requirements and / or the dimensions of each turbine disk 11. In a preferred example, the number of turbine disks 11 is five or more; this embodiment will use six turbine disks 11 as an example. Correspondingly, the number of intermediate-stage turbine disks 11 is four. Each turbine disk 11 is provided with multiple forward balancing holes 111 and multiple reverse balancing holes 112. The forward balancing holes 111 and reverse balancing holes 112 are not differences in physical structure, but only differ in the direction of gas flow they guide. For example, the airflow direction inside the forward balance hole 111 is the same as the mainstream gas flow direction of the turbine, while the airflow direction inside the reverse balance hole 112 is opposite to the mainstream gas flow direction of the turbine. Furthermore, the reverse balance hole 112 on the reverse side of the final stage vortex disk has a radially opening air duct communicating with the hollow cavity of the final stage exhaust connection section 12, defined in this embodiment as reverse balance hole air duct 114; the forward balance hole 111 on the reverse side of the final stage vortex disk has a radially opening air duct communicating with the edge of the turbine disk 11, defined in this embodiment as forward balance hole air duct 113. Both the forward balance hole 111 and the reverse balance hole 112 on the front side of the first stage turbine disk 11 have air ducts communicating with the hollow cavity of the first stage intake connection section 13. All balance holes on the front and back sides of the intermediate stage turbine disk 11, the reverse side of the first stage turbine disk 11, and the front side of the final stage turbine disk 11, including the forward balance hole 111 and the reverse balance hole 112, are preferably without air ducts to interfere with the gas flow direction. The forward balance holes 111 of adjacent turbine disks 11 are interconnected, and the reverse balance holes 112 are interconnected. Typically, the forward balance holes 111 and reverse balance holes on each stage of turbine disk 11 are identical, thus ensuring that the forward balance holes 111 and reverse balance holes 112 of adjacent turbine disks 11 are interconnected one-to-one. It should be noted that in this embodiment, the "reverse side" refers to the side facing away from the turbine's main gas flow direction, while the "front side" refers to the side facing the turbine's main gas flow direction. The main gas refers to the gas that drives the turbine to perform work. In other examples, the definitions of "front side" and "reverse side" can be interchanged, and the positions of the first and last stage turbine disks will be interchanged accordingly. Both the forward balance holes 111 and the reverse balance holes 112 are through holes, meaning they penetrate the turbine disk 11 along its thickness direction, i.e., along a direction parallel to the turbine disk's axial direction. The bleed-out grooves, however, are blind grooves, meaning their depth is less than the turbine disk's thickness and does not penetrate the turbine disk 11.

[0032] The exemplary working principle of the turbine cooling structure provided by this invention is as follows: Figure 1 and 2As shown, cooling gas, such as cryogenic helium, is introduced through the exhaust connection section 12, through the reverse balance hole 114 into the reverse balance hole 112 of the final stage turbine disk 11, and then flows through the reverse balance holes 112 of each intermediate stage to the first stage turbine disk 11. It then enters the hollow cavity of the intake connection section 13 through the air sluice on the front of the first stage turbine disk 11, and enters the forward balance hole 111 of the first stage turbine disk 11 through the forward balance hole 113. It then enters the cavity between each stage turbine disk 11 through the forward balance holes 111 of each intermediate stage turbine disk 11, and finally enters the turbine mains channel through the forward balance hole 113 on the back of the final stage turbine disk 11, thus completing the cooling of each stage turbine disk 11.

[0033] The ingeniously designed structure of this invention guides the flow of cryogenic cooling gas on the turbine, significantly increasing the contact area between the cooling gas and the turbine disk within a limited space. This helps improve the cooling effect and ensures the turbine's long-term safe and stable operation. The structure is simple, easy to install and use, and contributes to the simplification of the overall equipment structure.

[0034] Except for the differences in the internal balancing holes and bleed slots, the overall outlines of each turbine disk 11 are basically the same. For example, the outer and inner diameters of each turbine disk 11 are the same, that is, the size of the central disk cavity is the same, and each turbine disk 11 has a slot on its edge for fixing the blades. More specifically, the structure of the first-stage turbine disk 11 can be referred to Figure 3 and 4 As shown in the diagram, only the forward balancing hole 111, the reverse balancing hole 112, and the screw hole 115 are visible from the back, while the forward balancing hole air intake groove 113 and the reverse balancing hole air intake groove 114, which communicate with the disk cavity, are also visible from the front. The hollow cavity in the intake connection section connected to the first-stage turbine disk 11 facilitates the return of cooling gas, which helps to improve the cooling effect. The structure of the intermediate-stage turbine disk 11 is as follows... Figure 5 and 6 As shown, its front and back sides have the same structure. Besides the conventional disk cavity and screw holes, it only has a forward balance hole 111 and a reverse balance hole 112, but not a forward balance hole sump 113 or a reverse balance hole sump 114. The structure of the final stage turbine disk 11 is shown in the reference diagram. Figure 7 and Figure 8 As shown, in contrast to the first-stage turbine disk 11, in addition to the forward balance hole 111 and the reverse balance hole 112, the reverse balance hole air duct 114 connected to the disk cavity and the forward balance hole air duct 113 connected to the disk edge can also be seen on the back side.

[0035] The number, size, and layout of the forward balancing holes 111 and reverse balancing holes 112 on each turbine disk 11 can be determined as needed, for example, according to the turbine's cooling requirements. In one example provided by the present invention, each turbine disk 11 has four forward balancing holes 111 and four reverse balancing holes 112. The forward balancing holes 111 and reverse balancing holes 112 are evenly spaced and alternately arranged on the same circumferential surface of the turbine disk 11, and preferably both the forward balancing holes 111 and reverse balancing holes 112 are circular holes with the same diameter. This helps to ensure a relatively stable cooling airflow, improve cooling / heat dissipation uniformity, and avoid the generation of local hot spots.

[0036] Adjacent turbine disks 11 can be fixed in a suitable manner, such as by welding. However, welding is costly and difficult to disassemble and replace. Therefore, in the preferred embodiment of this application, fasteners such as screws are used for fixing. For this purpose, each turbine disk 11 can be provided with multiple screw holes 115, for example, each turbine disk 11 has 8 screw holes, which are alternately arranged with the positive balance hole 111 and the negative balance hole 112 on the same circumferential surface.

[0037] In a preferred example, the turbine cooling structure further includes several annular positioning disks 14, each positioned one-to-one between adjacent turbine disks 11, with a central circular hole corresponding to the cavity of the turbine disk 11. Furthermore, each positioning disk 14 is also provided with an opening 141 that connects the forward balancing holes 111 and reverse balancing holes 112 of adjacent turbine disks 11. For example, if there are six turbine disks 11, five positioning disks 14 are required. The positioning disks 14 not only facilitate the positioning and installation of adjacent turbine disks 11, but also guide the cooling gas to flow along the forward balancing holes 111 of each turbine disk 11 and into the cavity between the turbine disks 11. A preferred structure of the positioning disks 14 can be found in [reference needed]. Figure 9 As shown, its outer end face is U-shaped, and the inner end face of the positioning disk 14 is provided with an opening communicating with the opening 141, for introducing cooling gas into the disk cavity of the positioning disk 14 to cool the disk cavity of the positioning disk 14. That is, after the cooling gas reaches the positioning disk 14, part of it flows into the positive balance hole 111 of the next stage turbine disk 11 through the opening of the positioning disk 14, and part of it enters the disk cavity of the positioning disk 14 through the opening. The U-shaped outer end face of the positioning disk 14 helps to save materials and reduce the weight of the positioning disk 14 itself, and forms a U-shaped space between adjacent turbine disks 11, which helps the turbine disk 11 to dissipate heat and release stress. The positioning disk 14 is also fixed to the turbine disk 11 by screws, so the positioning disk 14 is also provided with screw holes 142 that match the screw holes 115 of the turbine disk 11. A long threaded rod can be used to pass through each stage of turbine disk 11 and positioning disk 14, and then a nut can be used to fasten each structure.

[0038] In a further example, the turbine cooling structure also includes several bleed air rings 15, which are interference-fitted with the positioning disk 14 to connect the reverse balance holes 112 of the intermediate stage turbine disk 11, thereby guiding the cooling gas to flow along the reverse balance holes 112. Preferably, no bleed air rings are provided between the forward balance holes of the intermediate stage turbine disk 11. The structure of the bleed air rings 15 can be referenced from... Figure 10 As shown, it is a cylindrical structure with the same inner diameter as the pull rod and a length equal to the inner diameter of the positioning disk 14. The positioning disk 14 and the air duct ring 15 further increase the area through which the cooling gas flows, thus improving the cooling effect.

[0039] The positioning disc 14 and the air bleed ring 15 are preferably made of the same material as the turbine disc 11, such as stainless steel or other high-strength alloys. This helps reduce thermal resistance and further improves cooling performance.

[0040] In one example, sealing teeth 16 are provided on the outer peripheral surface of the connection between adjacent turbine disks 11. The sealing teeth 16 help to reduce pressure difference and leakage area.

[0041] This invention also provides a turbine cooling method, which is based on the turbine cooling structure described in any of the above-mentioned schemes. Therefore, the foregoing content can be quoted in its entirety here, and will not be repeated for the purpose of brevity. Specifically, the turbine cooling method includes: passing cooling gas through the exhaust connection section 12, entering the reverse balance hole 112 of the last-stage turbine disk 11 through the air intake groove, and flowing sequentially through the reverse balance holes 112 of each intermediate stage to the first-stage turbine disk 11, then entering the hollow cavity of the intake connection section 13 through the air intake groove on the front of the first-stage turbine disk 11, and entering the positive balance hole 111 of the first-stage turbine disk 11 through the positive balance hole air intake groove 113, then sequentially entering the cavity between each stage of turbine disk 11 through the positive balance hole 111 of each intermediate stage, and finally introducing it into the turbine main flow channel through the positive balance hole air intake groove 113 on the reverse side of the last-stage turbine disk 11, thereby completing the cooling of each stage of turbine disk 11. With the positioning disk 14 and the bleed air ring 15 in place, the cooling gas entering the reverse balance hole 112 of the final stage turbine disk 11 first passes through the positioning disk 14 and the bleed air ring 15 in sequence before entering the reverse balance hole 112 of the intermediate stage turbine disks 11. It can be seen that, due to the turbine cooling structure provided by this invention, the flow path of the cooling gas within the turbine is greatly extended, and the contact area with the turbine interior is significantly increased, which will greatly improve cooling efficiency and enhance the cooling effect.

[0042] This invention also provides a Brayton power generation cycle system, which includes a turbine cooling structure as described in any of the above embodiments. For a detailed description of the turbine cooling structure, please refer to the foregoing content; for brevity, it will not be repeated. The Brayton power generation cycle system of this embodiment is preferably a closed-loop helium Brayton power generation cycle system, and therefore further includes components such as a low-pressure compressor, a high-pressure compressor, a turbine, a precooler, an intercooler, and a regenerator. The Brayton power generation cycle system provided by this invention, except for using the turbine cooling structure of this invention, has no significant differences from the prior art in other components. Since this part is not the focus of this invention, and other components are well known to those skilled in the art, they will not be elaborated upon. Due to the use of the turbine cooling structure of this invention, the Brayton power generation cycle system of this invention can operate safely and stably for a long period.

[0043] In summary, this invention provides a turbine cooling structure and method, as well as a Brayton cycle system. The turbine cooling structure includes three or more turbine disks, each with multiple forward balancing holes and multiple reverse balancing holes. The airflow direction within the forward balancing holes is the same as the mainstream gas flow direction, while the airflow direction within the reverse balancing holes is opposite to the mainstream gas flow direction. Specifically, the reverse balancing holes on the reverse side of the last-stage vortex disk have radially extrusion slots communicating with the hollow cavity of the last-stage exhaust connection section. The forward balancing holes on the reverse side of the last-stage vortex disk have radially extrusion slots communicating with the edge of the turbine disk. Both the forward and reverse balancing holes on the front side of the first-stage turbine disk have extrusion slots communicating with the hollow cavity of the first-stage intake connection section. The forward balancing holes of adjacent turbine disks are interconnected, and the reverse balancing holes are also interconnected. This invention, through its ingeniously designed structure, guides the flow of cryogenic cooling gas on the turbine, significantly increasing the contact area between the cooling gas and the turbine disks within a limited space, thus improving the cooling effect and ensuring the long-term safe and stable operation of the turbine. This invention features a simple structure, making installation and use very convenient. It contributes to simplifying the overall equipment structure and reducing operating costs. This invention effectively overcomes the various shortcomings of existing technologies and possesses high industrial applicability.

[0044] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. A turbine cooling structure, characterized by, The turbine cooling structure comprises three or more turbine disks, each of which is provided with a plurality of forward balance holes and a plurality of reverse balance holes, the airflow direction in the forward balance holes is the same as the turbine main flow gas flow direction, and the airflow direction in the reverse balance holes is opposite to the turbine main flow gas flow direction, wherein the reverse balance holes on the reverse side of the last-stage turbine disk are provided with air bleed grooves in the radial direction, which are communicated with the hollow cavity of the last-stage exhaust connection section, the forward balance holes on the reverse side of the last-stage turbine disk are provided with air bleed grooves in the radial direction, which are communicated with the turbine disk rim, the forward balance holes and the reverse balance holes on the front side of the first-stage turbine disk are provided with air bleed grooves, which are communicated with the hollow cavity of the first-stage intake connection section, the forward balance holes and the reverse balance holes of adjacent turbine disks are communicated with each other, the forward balance holes and the reverse balance holes of adjacent turbine disks are communicated with each other through the positioning disk, and the positioning disk is provided between adjacent turbine disks.

2. The turbine cooling structure of claim 1, wherein The forward balance holes and the reverse balance holes on each turbine disk are four, and the forward balance holes and the reverse balance holes are uniformly spaced and alternately arranged on the same circumferential surface of the turbine disk.

3. The turbine cooling structure of claim 1, wherein All the balance holes on the front side and the reverse side of the intermediate-stage turbine disk, the reverse side of the first-stage turbine disk, and the front side of the last-stage turbine disk are not provided with air bleed grooves.

4. The turbine cooling structure of claim 1, wherein The turbine disks are five or more.

5. The turbine cooling structure of claim 1, wherein The outer end surface of the positioning disk is in a U-shaped form, and the inner end surface of the positioning disk is provided with an opening communicated with the opening hole and used for introducing the cooling gas into the disk cavity of the positioning disk.

6. The turbine cooling structure of claim 1, wherein The outer circumferential surface of the connection part of adjacent turbine disks is provided with a sealing tooth.

7. A method of cooling a turbine, characterized by, The turbine cooling method is based on the turbine cooling structure according to any one of claims 1 to 6, and the turbine cooling method comprises the following steps: introducing the cooling gas into the reverse balance holes of the last-stage turbine disk through the air bleed grooves of the exhaust connection section, and then sequentially flowing to the reverse balance holes of the intermediate-stage turbine disks, and then flowing to the forward balance holes of the first-stage turbine disk, and then flowing into the hollow cavity of the intake connection section through the air bleed grooves of the forward balance holes of the first-stage turbine disk, and then flowing into the forward balance holes of the first-stage turbine disk through the air bleed grooves of the forward balance holes, and then sequentially flowing into the mold cavities between the turbine disks through the forward balance holes of the intermediate-stage turbine disks, and finally flowing into the turbine main flow channel through the air bleed grooves of the forward balance holes on the reverse side of the last-stage turbine disk, so as to complete the cooling of the turbine disks.

8. A Brayton power cycle system characterized by, The Brayton power generation cycle system comprises the turbine cooling structure according to any one of claims 1 to 6.

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