Wheel disk assembly and gas turbine

Abstract

The application provides a wheel disc assembly and a gas turbine. The wheel disc assembly comprises a blade component, a wheel disc component and a sealing component. The blade component is connected in the circumferential direction of the wheel disc component, and a joint is formed between the blade component and the wheel disc component. The sealing component is arranged between the blade component and the wheel disc component and located on one side of the joint in the axial direction of the wheel disc component. The sealing component has a first side and a second side in the radial direction of the wheel disc component. The first side of the sealing component is matched with the blade component, and the second side of the sealing component is matched with the wheel disc component. The embodiment can effectively improve the sealing performance of the joint position of the blade disc, adapt to the high-temperature transient thermal deformation working condition and reduce the risk of structural collision and abrasion.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, specifically relating to a disc assembly and a gas turbine. Background Technology

[0002] In related technologies, when a gas turbine is working, it is necessary to draw low-temperature mainstream cold air from the compressor end to cool the turbine blades. In order to avoid structural rubbing between the turbine disk and the blades due to transient thermal deformation, and to reduce the impact of cold air leakage on the performance of the gas turbine, various sealing structures are usually used between the rotor and the stator, such as brush seals, grate seals, labyrinth seals, sealing plates, etc. This makes it difficult to control the structural sealing performance and structural reliability. Summary of the Invention

[0003] This invention is based on the inventor's discoveries and understanding of the following facts and problems:

[0004] The inventors recognized that different materials are often used between adjacent parts of turbine blades, resulting in differences in their coefficients of thermal expansion and thermal response speeds. The sealing structure is subjected to varying load conditions during variable operating conditions, leading to a lower service life than expected. In order to minimize cold air leakage, related technologies reduce the gap between the seal and the adjacent structure. At this time, the boundary conditions of the sealing structure change drastically during transient processes, making it prone to thermomechanical fatigue.

[0005] The present invention aims to at least partially solve one of the technical problems in the related art.

[0006] Therefore, embodiments of the present invention provide a wheel assembly with good sealing performance and high reliability.

[0007] An embodiment of the present invention provides a gas turbine.

[0008] The roulette wheel assembly of this invention includes: Blade components; A wheel assembly, wherein the blade assembly is connected circumferentially to the wheel assembly, and a joint is formed between the blade assembly and the wheel assembly; A sealing component is disposed between the blade component and the wheel component, and is located on one side of the axial direction of the joint on the wheel component. The sealing component has a first side and a second side in the radial direction of the wheel component. The first side of the sealing component mates with the blade component, and the second side of the sealing component mates with the wheel component.

[0009] This embodiment achieves targeted sealing by setting a sealing component at the blade disk joint, effectively improving the sealing performance of the blade disk connection position, while adapting to high-temperature transient thermal deformation conditions and reducing the risk of structural impact and abrasion.

[0010] In some embodiments, the sealing member is annular and includes a plurality of sealing plates arranged sequentially along the circumference of the wheel component.

[0011] In some embodiments, the sealing plate has a first overlapping portion and a second overlapping portion in the circumferential direction of the wheel component, and two adjacent sealing plates are respectively a first sealing plate and a second sealing plate, and the first overlapping portion of the first sealing plate and the second overlapping portion of the second sealing plate are arranged to overlap in the axial direction of the wheel component.

[0012] In some embodiments, a portion of the first overlapping portion and a portion of the second overlapping portion are fitted together, and a gap exists between another portion of the first overlapping portion and another portion of the second overlapping portion.

[0013] In some embodiments, the first overlap portion and the second overlap portion are in line contact, and one or more line contact portions are formed between the first overlap portion and the second overlap portion; And / or, the first overlapping portion and the second overlapping portion are in surface contact, and one or more surface contact portions are formed between the first overlapping portion and the second overlapping portion; And / or, the surface of the first overlapping portion facing the second overlapping portion includes at least one of a curved segment, a planar segment, or a serrated segment; And / or, the surface of the second overlap facing the first overlap includes at least one of a curved segment, a planar segment, or a serrated segment.

[0014] In some embodiments, the blade component has a first mating groove, the wheel component has a second mating groove, a first side of the sealing component is inserted into the first mating groove, and a second side of the sealing component is inserted into the second mating groove.

[0015] In some embodiments, the first mating groove and the second mating groove are arranged opposite each other in the radial direction of the wheel component; And / or, the bottom surface of the first mating groove and the bottom surface of the second mating groove are radially larger than the radially larger of the sealing component in the wheel disc component.

[0016] In some embodiments, a connecting component is further included, which connects the sealing component and the blade component, or the sealing component and the wheel component.

[0017] In some embodiments, the connecting component includes a latch and an end plate connected together, the blade component or the wheel component is provided with a lock hole, the latch is inserted into the lock hole, and the end plate is connected to the sealing component by fasteners; And / or, there are multiple connecting components, and the multiple connecting components are arranged spaced apart from each other along the circumference of the wheel component; And / or, the sealing component is provided with a connecting hole, the connecting component passes through the connecting hole, and the dimension d of the connecting hole and the first side or the second side of the sealing component in the radial direction of the wheel component satisfies the condition that d / D is greater than or equal to 0.5 and less than or equal to 0.8.

[0018] The gas turbine of this invention includes the disk assembly described in any of the above embodiments. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the wheel assembly according to an embodiment of the present invention.

[0020] Figure 2 This is a schematic diagram of the sealing plate according to an embodiment of the present invention.

[0021] Figure 3 This is a schematic diagram of two adjacent sealing plates according to an embodiment of the present invention.

[0022] Figure label: 100. Roulette wheel assembly; 1. Blade assembly; 11. First mating groove; 2. Wheel assembly; 21. Second mating groove; 22. Lock hole; 3. Sealing component; 31. First sealing plate; 32. Second sealing plate; 33. First overlapping portion; 34. Second overlapping portion; 35. Connecting hole; 4. Connecting components; 41. Locking tongue; 42. End plate; 43. Fasteners; 5. Seams. Detailed Implementation

[0023] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0024] The sealing structures in related technologies have poor adaptability to the high temperature, high pressure, high speed and transient thermal deformation conditions of gas turbines. They are prone to problems such as changes in sealing gaps, structural wear and sealing failure. This makes it difficult to balance sealing performance and structural reliability, resulting in large cold gas leakage, which leads to a decrease in gas turbine cycle efficiency and an increase in energy consumption. At the same time, the structure is prone to fatigue damage during long-term operation, affecting the overall operational stability and service life of the gas turbine.

[0025] See Figures 1 to 3This disclosure presents a disk assembly 100, which can be applied to gas turbines and used as power equipment such as aviation gas turbines and industrial gas turbines. The disk assembly 100 of this embodiment includes a blade component 1, a disk component 2, and a sealing component 3. The blade component 1 is connected circumferentially to the disk component 2, and a joint 5 is formed between the blade component 1 and the disk component 2. The sealing component 3 is disposed between the blade component 1 and the disk component 2, and is located on one side of the joint in the axial direction of the disk component 2. The sealing component 3 has a first side and a second side in the radial direction of the disk component 2. The first side of the sealing component 3 mates with the blade component 1, and the second side of the sealing component 3 mates with the disk component 2.

[0026] Figure 1 The arrows shown indicate the direction of cold air flow. In this embodiment, the wheel component 2 serves as the load-bearing base for the gas turbine rotor, used for circumferentially assembling and fixing the multi-stage blade component 1, and is the main force-bearing structure for the high-speed rotation of the rotor. The blade component 1 is arranged around the outer periphery of the wheel component 2 and is fixedly assembled with the wheel component 2. The assembly connection between the blade component 1 and the wheel component 2 naturally forms an annular seam. This seam is the main channel for cold air leakage and airflow movement, and is also a critical area for thermal deformation and abrasion. In this embodiment, the sealing component 3 is arranged on one axial side of the seam to fully cover and seal the assembly seam between the blade and the wheel. The sealing component 3 has two radially distinct mating structures. The first side precisely fits and limits the blade component 1, and the second side fits snugly with the wheel component 2. By sealing the seam gap through a double-sided, bidirectional mating method, the leakage of cooling air from the seam is prevented.

[0027] This embodiment addresses the shortcomings of traditional seals, such as poor adaptability and unstable sealing gaps. By setting a sealing component 3 at the impeller joint, targeted sealing is achieved, effectively improving the sealing performance at the impeller joint. At the same time, it adapts to high-temperature transient thermal deformation conditions and reduces the risk of structural impact and abrasion.

[0028] See Figure 2 and Figure 3 In some embodiments, the sealing component 3 is annular and includes multiple sealing plates arranged sequentially along the circumference of the wheel component 2.

[0029] In this embodiment, the sealing component 3 can be constructed as a ring structure, which is compatible with the ring joint shape of the turbine disk and blades, enabling full-circumference sealing. Furthermore, the ring sealing structure in this embodiment is not a single, integrated structure, but rather assembled from multiple independent sealing plates sequentially along the circumference of the turbine disk. This segmented sealing plate structure effectively adapts to the thermal expansion and contraction characteristics of gas turbines under high-temperature operating conditions. Compared to a single ring seal, the multi-segmented structure can release thermal deformation stress, preventing the sealing structure from being squeezed, deformed, warped, or cracked under high-temperature conditions, thus preventing seal failure. Simultaneously, the segmented structure is easy to disassemble and assemble, facilitating later maintenance and replacement, and reducing operation and maintenance costs.

[0030] See Figure 2 and Figure 3 In some embodiments, the sealing plate has a first overlapping portion 33 and a second overlapping portion 34 in the circumferential direction of the wheel component 2, and two adjacent sealing plates are a first sealing plate 31 and a second sealing plate 32, respectively. The first overlapping portion 33 of the first sealing plate 31 and the second overlapping portion 34 of the second sealing plate 32 are stacked in the axial direction of the wheel component 2.

[0031] In this embodiment, each sealing plate has a first overlapping portion 33 and a second overlapping portion 34 at both ends of its circumference, serving as a splicing and mating structure for adjacent sealing plates. Adjacent first sealing plates 31 and second sealing plates 32 are axially overlapped through their end overlapping portions. The front and rear sealing plates overlap each other in the axial direction, effectively eliminating circumferential splicing gaps between the segmented sealing plates. This overlapping structure blocks cold air leakage channels at the segmented splicing locations, solving the problem of air leakage at the splicing gaps of traditional segmented sealing plates and ensuring the continuity and sealing performance of the entire sealing structure.

[0032] See Figure 2 and Figure 3 In some embodiments, a portion of the first overlapping portion 33 and a portion of the second overlapping portion 34 are fitted together, and there is a gap between another portion of the first overlapping portion 33 and another portion of the second overlapping portion 34.

[0033] In this embodiment, adjacent overlapping portions adopt a composite fitting method of partial contact and partial gaps. Partially, the overlapping portions are in close contact to ensure a tight seal at the joint, preventing cold air penetration and leakage. The remaining areas of the overlapping portions have small gaps to create stress release space and reduce friction. Under the high-temperature operating conditions of the gas turbine, the sealing plates undergo thermal expansion and deformation. The reserved gaps provide sufficient deformation allowance to offset the compressive stress generated by thermal expansion, preventing adjacent sealing plates from pressing against each other, warping, or deforming and dislodging from their mating positions. This balances sealing performance with thermal deformation adaptability, improving the structural operational reliability.

[0034] In some embodiments, the first overlap portion 33 and the overlap portion line contact each other, and one or more line contact portions are formed between the first overlap portion 33 and the second overlap portion 34.

[0035] Alternatively, the first overlapping portion 33 and the second overlapping portion 34 are in surface contact, and one or more surface contact portions are formed between the first overlapping portion 33 and the second overlapping portion 34.

[0036] Alternatively, the surface of the first overlapping portion 33 facing the second overlapping portion 34 may include at least one of a curved segment, a flat segment, or a serrated segment.

[0037] Alternatively, the surface of the second overlap 34 facing the first overlap 33 may include at least one of a curved segment, a flat segment, or a serrated segment.

[0038] In this embodiment, adjacent overlapping portions can adopt various contact fit forms to adapt to different working conditions. The structures of the first overlapping portion 33 and the second overlapping portion 34 in this embodiment can be used individually or in combination, greatly improving the working condition adaptability of the sealing structure.

[0039] In this embodiment, when using line contact mating, multiple linear sealing barriers can be formed, resulting in a tight fit and excellent micro-gap sealing effect, making it better suited for high pressure differential sealing conditions. When using surface contact mating, the contact area is large, the structural stability is strong, and it can effectively disperse thermal deformation and extrusion stress, making it suitable for long-term stable operation. In this embodiment, the mating surfaces of the overlapping part can be flexibly set as planar sections, curved sections, or serrated sections. Planar sections are easy to process and fit smoothly; curved sections can adaptively fine-tune the fitting gap to accommodate minor thermal deformation. Serrated sections can form a multi-level labyrinth seal effect, further improving the gas barrier capability.

[0040] In some embodiments, the blade component 1 has a first mating groove 11, the wheel component 2 has a second mating groove 21, the first side of the sealing component 3 is inserted into the first mating groove 11, and the second side of the sealing component 3 is inserted into the second mating groove 21.

[0041] In this embodiment, the blade component 1 and the wheel component 2 are respectively provided with mating grooves to form a bidirectional slot limiting structure. The sealing component 3 is inserted into the corresponding first mating groove 11 and second mating groove 21 on both radial sides, and the sealing component 3 is positioned and installed through the groove nesting method. The slot insertion structure can limit the sealing component 3 in multiple dimensions in the radial, axial and circumferential directions, preventing the sealing component 3 from shifting, loosening or falling off under the conditions of high-speed rotor rotation and airflow impact, ensuring the positional stability of the sealing structure. At the same time, the groove wrapping seal can further block the interstitial airflow and improve the sealing effect.

[0042] Furthermore, the first mating groove 11 and the second mating groove 21 are arranged opposite each other in the radial direction of the wheel component 2. In this embodiment, by arranging the upper and lower sets of mating grooves radially opposite each other, the sealing component 3 is subjected to symmetrical forces on both sides and the assembly is centered, avoiding the problems of sealing tilt and uneven gap caused by unilateral load.

[0043] The bottom surface of the first mating groove 11 and the bottom surface of the second mating groove 21 in the radial direction of the wheel component 2 are larger than the radial direction of the sealing component 3 in the wheel component 2.

[0044] In this embodiment, the two mating grooves are larger in the radial direction of the wheel disk component 2 than the sealing component 3 is in the radial direction of the wheel disk component 2. This allows for a small assembly gap and thermal deformation allowance for the sealing component 3, which facilitates assembly and alignment and prevents the sealing component 3 from getting stuck inside the groove due to thermal expansion under high temperature conditions. This prevents structural compression deformation and damage and is suitable for the temperature fluctuation characteristics of the gas turbine under varying operating conditions.

[0045] In some embodiments, the wheel assembly 100 further includes a connecting member 4, which is connected between the sealing member 3 and the blade member 1, or between the sealing member 3 and the wheel assembly 2.

[0046] In this embodiment, by adding a connecting component 4 as an auxiliary fixing structure, the sealing component 3 can be selectively fastened to the blade component 1 or the wheel component 2 according to the assembly space and working conditions. Based on the insertion limit, the connecting component 4 achieves secondary locking and fixing, improving the assembly firmness of the sealing component 3, resisting the centrifugal force and high-pressure airflow impact force generated by high-speed rotation, preventing the sealing plate from vibrating and loosening, and further improving the operational reliability of the sealing structure.

[0047] Each sealing plate can be equipped with a corresponding connecting component 4, thereby ensuring the structural stability of each sealing plate.

[0048] In some embodiments, the connecting component 4 includes a locking tongue 41 and an end plate 42 connected together. The blade component 1 or the wheel component 2 has a locking hole 22, into which the locking tongue 41 is inserted. The end plate 42 is connected to the sealing component 3 via fasteners 43. In this embodiment, the connecting component 4 adopts a combined locking structure of locking tongue 41 and end plate 42. The locking tongue 41 is inserted into the locking hole 22 for positioning, achieving radial limiting. The end plate 42 is attached to the sealing plate and locked by fasteners 43, achieving axial fixation. This double-limiting structure provides reliable fixation and convenient assembly / disassembly.

[0049] There are multiple connecting parts 4, which are spaced apart from each other along the circumference of the wheel disc part 2. The multiple connecting parts 4 are evenly spaced along the circumference to ensure that the entire sealing plate is subjected to uniform force and has consistent fixing stability.

[0050] Furthermore, the sealing component 3 is provided with a connecting hole 35, and the connecting component 4 passes through the connecting hole 35. The dimension d of the connecting hole 35 and the first or second side of the sealing component 3 in the radial direction of the wheel component 2 satisfies the requirement that d / D is greater than or equal to 0.5 and less than or equal to 0.8.

[0051] Wherein, d / D can be 0.5, 0.6, 0.66, 0.7, or 0.8. This embodiment ensures that the opening size of the connecting hole 35 is sufficient to meet the assembly locking strength requirements, while avoiding excessively large openings or openings biased to one side that could damage the structural strength of the sealing plate, preventing cracking and deformation of the sealing plate, thus balancing structural tightness and integrity and improving stability in application.

[0052] The gas turbine of this invention includes the disk assembly 100 of any of the above embodiments.

[0053] In this embodiment, the gas turbine is equipped with the aforementioned turbine disk assembly, and a segmented overlapping sealing structure is applied to the joint sealing position between the blades and the turbine disk. Under the conditions of high temperature, high pressure, high speed, and transient thermal deformation of the gas turbine, it can effectively seal the cold air leakage channel at the blade disk joint, reduce cooling air loss, improve the gas turbine cycle efficiency, and at the same time, it can adapt to thermal deformation, release deformation stress, avoid structural rubbing and seal failure, and significantly improve the overall operational stability and service life of the gas turbine.

[0054] In this embodiment, during operation, an annular segmented sealing component is arranged on the axial side of the joint between the blade component and the wheel component. The radial sides of the sealing component are respectively inserted into the mating grooves of the blade and the wheel, achieving full coverage sealing of the joint gap. Multiple sealing plates are axially overlapped and spliced ​​through circumferential overlap, using a localized fitting structure to ensure the sealing effect, and using locally reserved gaps to release high-temperature thermal deformation stress, avoiding deformation and cracking.

[0055] In this embodiment, the overlapping joints optimize the sealing and barrier effect through line contact, surface contact, and diverse mating surface structures, effectively blocking cold air leakage at multiple levels. Simultaneously, the circumferentially spaced connecting components provide secondary locking and fixation of the sealing plate, better resisting high-speed centrifugal force and airflow impact, ensuring long-term positional stability of the sealing structure. The overall structure is adaptable to the transient thermal deformation conditions of the gas turbine, significantly reducing cold air leakage at the blade disk joints while avoiding structural abrasion, thus balancing sealing performance and structural reliability.

[0056] This invention achieves dynamic coupling between the sealing plate and adjacent structures, ensuring the stability of boundary conditions throughout the entire operating cycle, increasing the service life of the sealing plate, guaranteeing the axial positioning of the blade, and reducing strong coupling between the blade and adjacent sealing structures. Furthermore, this embodiment can have grooves inside the blade root or on both sides of the blade root, satisfying both the frequency tuning requirements and weight reduction requirements of the blade.

[0057] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0058] Furthermore, the terms "first" and "second" are used 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 as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0059] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," 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, an electrical connection, or a connection that allows communication between them; 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 explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0060] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of 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. "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.

[0061] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0062] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A wheel assembly, characterized in that, include: Blade components; A wheel assembly, wherein the blade assembly is connected circumferentially to the wheel assembly, and a joint is formed between the blade assembly and the wheel assembly; A sealing component is disposed between the blade component and the wheel component, and is located on one side of the axial direction of the joint on the wheel component. The sealing component has a first side and a second side in the radial direction of the wheel component. The first side of the sealing component mates with the blade component, and the second side of the sealing component mates with the wheel component.

2. The wheel assembly according to claim 1, characterized in that, The sealing component is annular and includes multiple sealing plates arranged sequentially along the circumference of the wheel component.

3. The wheel assembly according to claim 2, characterized in that, The sealing plate has a first overlapping portion and a second overlapping portion in the circumferential direction of the wheel component. Two adjacent sealing plates are respectively a first sealing plate and a second sealing plate. The first overlapping portion of the first sealing plate and the second overlapping portion of the second sealing plate are arranged to overlap in the axial direction of the wheel component.

4. The wheel assembly according to claim 3, characterized in that, A portion of the first overlapping part and a portion of the second overlapping part are fitted together, and there is a gap between the other portion of the first overlapping part and the other portion of the second overlapping part.

5. The wheel assembly according to claim 4, characterized in that, The first overlapping portion and the second overlapping portion are in line contact, and one or more line contact portions are formed between the first overlapping portion and the second overlapping portion; And / or, the first overlapping portion and the second overlapping portion are in surface contact, and one or more surface contact portions are formed between the first overlapping portion and the second overlapping portion; And / or, the surface of the first overlapping portion facing the second overlapping portion includes at least one of a curved segment, a planar segment, or a serrated segment; And / or, the surface of the second overlap facing the first overlap includes at least one of a curved segment, a planar segment, or a serrated segment.

6. The wheel assembly according to claim 1, characterized in that, The blade component has a first mating groove, the wheel component has a second mating groove, the first side of the sealing component is inserted into the first mating groove, and the second side of the sealing component is inserted into the second mating groove.

7. The wheel assembly according to claim 6, characterized in that, The first mating groove and the second mating groove are arranged opposite each other in the radial direction of the wheel component; And / or, the bottom surface of the first mating groove and the bottom surface of the second mating groove are radially larger than the radially larger of the sealing component in the wheel disc component.

8. The wheel assembly according to claim 1, characterized in that, It also includes a connecting component that connects the sealing component and the blade component, or the sealing component and the wheel component.

9. The wheel assembly according to claim 8, characterized in that, The connecting component includes a latch and an end plate connected together. The blade component or the wheel component is provided with a lock hole. The latch is inserted into the lock hole. The end plate is connected to the sealing component by fasteners. And / or, there are multiple connecting components, and the multiple connecting components are arranged spaced apart from each other along the circumference of the wheel component; And / or, the sealing component is provided with a connecting hole, the connecting component passes through the connecting hole, and the dimension d of the connecting hole and the first side or the second side of the sealing component in the radial direction of the wheel component satisfies the condition that d / D is greater than or equal to 0.5 and less than or equal to 0.

8.

10. A gas turbine, characterized in that, The wheel assembly includes any one of claims 1 to 9.

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