gas turbine

Abstract

The present invention provides a gas turbine that prevents the blades from detaching from the disk in the axial and circumferential directions under any operating conditions, facilitates the management of fixed parts, and allows for the reuse of parts. [Solution] The gas turbine 200 includes a blade 230 with a root portion 235 formed therein, a disk 210 with a disk slot 213 into which the root portion is inserted, and a fixing block 250 which is inserted circumferentially into the groove formed in the blade and the groove formed in the disk, and is provided to fix the axial position and radial position of the blade with respect to the disk.

Description

Technical Field

[0001] This application claims the benefit of priority based on Korean Patent Application No. 10-2024-0171881 filed on November 27, 2024, and all the contents disclosed in the literature of the Korean patent application are incorporated herein by reference in their entirety. The present invention relates to a gas turbine.

Background Art

[0002] A turbine is a mechanical device that obtains rotational force by impulse or reaction force using the flow of a compressible fluid such as steam or gas, and examples include a steam turbine using steam and a gas turbine using high-temperature combustion gas.

[0003] Among them, a gas turbine is mainly composed of a compressor, a combustor, and a turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged in the compressor casing.

[0004] The combustor supplies fuel to the compressed air compressed by the compressor and ignites it with a burner, thereby generating high-temperature and high-pressure combustion gas. The turbine has a plurality of turbine vanes and turbine blades alternately arranged in the turbine casing. Also, a rotor is arranged so as to penetrate the centers of the compressor, the combustor, the turbine, and the exhaust chamber.

[0005] Both ends of the rotor are rotatably supported by bearings. A plurality of disks are fixed to the rotor, each blade is connected, and a drive shaft such as a generator is connected to the end on the exhaust chamber side.

[0006] Such a gas turbine does not have a reciprocating mechanism like a piston in a four-stroke engine, so there are no mutually friction parts like a piston-cylinder, the consumption of lubricating oil is extremely small, the amplitude, which is a characteristic of a reciprocating machine, is significantly reduced, and it has the advantage of being capable of high-speed movement.

[0007] To briefly explain the operation of a gas turbine, compressed air from a compressor is mixed with fuel and burned to produce high-temperature combustion gases, which are then injected into the turbine. The injected combustion gases pass through the turbine vanes and blades, generating rotational force, which in turn causes the rotor to rotate.

[0008] The compressor and turbine may consist of a structure in which multiple blades are coupled to a disk. In this case, fixing the blades to the disk using fastening components can prevent the blades from detaching from the disk during operation of the cassette bin.

[0009] Traditionally, the components that secure the blade and disc consist of a structure assembled from three or more parts, and for assembly, one of the multiple parts includes a bent (bending) component.

[0010] However, with this type of structure, the bent parts necessitate the repurchase of parts during reassembly after disassembly, and the characteristics of the bent shape make it difficult to ensure the assembly reliability of the bent parts. In addition, using conventional methods presents the problem of difficulty in visual inspection. [Overview of the Initiative] [Problems that the invention aims to solve]

[0011] The present invention has been made to solve the aforementioned problems, and aims to provide a gas turbine that can prevent the blades from axially separating from the disk under any operating conditions of the gas turbine.

[0012] The present invention aims to provide a gas turbine that facilitates the management of fixed components and allows for the reuse of components. The present invention aims to provide a gas turbine that facilitates blade replacement, improves assembly and disassembly efficiency, and reduces costs. [Means for solving the problem]

[0013] To achieve the above objective, the gas turbine according to the present invention includes a blade with a root portion formed therein, a disk with a disk slot into which the root portion is inserted, a groove formed in the blade, and a fixing block inserted circumferentially into the groove formed in the disk, and provided to fix the axial and radial positions of the blade with respect to the disk.

[0014] The disk may include a disk body in which the disk slot is formed, and a block insertion groove extending in the circumferential direction into which the fixing block is inserted. The block insertion groove can be formed with a T-shaped cross-section perpendicular to the circumferential direction.

[0015] The disk body further includes a pair of anti-detachment projections for forming the block insertion groove, wherein one of the pair of anti-detachment projections extends radially and the other extends toward the central axis of the disk and is formed to face each other, so that the block insertion groove is formed in a T-shape and the block insertion groove is formed to open toward one side in the axial direction.

[0016] The blade may further include a blade body and a platform portion formed between the blade body and the root portion. The root portion may include a block assembly groove extending in the circumferential direction, into which the fixed block is inserted.

[0017] The block assembly groove, together with the block insertion groove, can form a slide groove into which the fixed block is inserted when the blade and the disk are joined.

[0018] The slide groove is divided, with respect to the circumferential direction, into a block assembly groove located in the central region and block insertion grooves located on both sides of the block assembly groove, and an opening is formed that opens toward one side in the axial direction, so that a part of the fixed block is inserted into the block assembly groove and the remaining part of the fixed block is inserted into the block insertion groove.

[0019] The root portion further includes assembly ribs that extend toward the central axis of the disk and form the block assembly groove, and the axial end of the assembly rib can be located further from the central axis of the disk than the axial end of the root portion.

[0020] The fixed block includes an insertion portion that is inserted into the block assembly groove and the block insertion groove, and an exposed portion that is formed integrally with the insertion portion and protrudes in one direction in the axial direction, wherein the exposed portion can be provided to be exposed to the outside of the slide groove through the opening when the fixed block is assembled into the slide groove.

[0021] The aforementioned fixing block can be formed with a T-shaped cross-section perpendicular to the circumferential direction. Multiple fixing blocks are provided, and the slide groove has openings at both ends in the circumferential direction, and the multiple fixing blocks can be arranged in the slide groove along the circumferential direction. [Effects of the Invention]

[0022] According to embodiments of the present invention, the fixed block prevents the blades from axially separating from the disk under any operating conditions of the gas turbine.

[0023] Furthermore, according to the embodiments of the present invention, since there are no bent portions in the fixed assembly parts, there are advantages such as easier management of parts and the ability to reuse parts.

[0024] Further, according to the embodiment of the present invention, when replacing the blade, only the fixing assembly for fixing the blade needs to be disassembled and reassembled, so that the blade replacement operation becomes easy.

[0025] And when using the fixing assembly according to the embodiment of the present invention, the blade and the disk can be manufactured and assembled with a simple structure, so that the workability is improved and the cost can be reduced.

Brief Description of the Drawings

[0026] [Figure 1] It is a cross-sectional view showing a schematic structure of a gas turbine to which an embodiment of the present invention is applied. [Figure 2] It is an exploded perspective view showing an example of an assembly structure of a disk and a blade to which an embodiment of the present invention is applied. [Figure 3] It is a perspective view showing a gas turbine according to an embodiment of the present invention, and is an enlarged perspective view showing an assembled portion of a disk, a blade, and a fixing block in an enlarged manner. [Figure 4] It is a perspective view showing a fixing block according to an embodiment of the present invention. [[ID=​​​​​​​​​​​​​​​​​​​​​This is a perspective view showing a fixed block according to an embodiment of the present invention being moved circumferentially along a block insertion groove formed in a disk. [Figure 11c] This is a perspective view illustrating the process by which a blade according to an embodiment of the present invention is assembled onto a disk. [Figure 11d] This is a perspective view showing the process of inserting a fixed block according to an embodiment of the present invention into a block insertion groove and a block assembly groove. [Figure 12] This is an enlarged view of a part of a gas turbine according to an embodiment of the present invention, showing a state in which fixed blocks are continuously assembled in the circumferential direction. [Modes for carrying out the invention]

[0027] Embodiments of the present invention will be described in detail below with reference to the attached drawings. First, the embodiments described later are suitable for understanding the technical features of the gas turbine according to the present invention. However, the technical features of the present invention are not limited to the embodiments described later, and various modifications can be implemented within the technical scope of the present invention.

[0028] Figure 1 is a cross-sectional view showing a schematic structure of a gas turbine to which an embodiment of the present invention is applied, and Figure 2 is an exploded perspective view showing an example of a disk and blade assembly structure to which an embodiment of the present invention is applied.

[0029] Figure 3 is a perspective view showing a gas turbine according to an embodiment of the present invention, and is an enlarged perspective view showing an enlarged portion of the assembly of the disk, blade and fixed block. Figure 4 is a perspective view showing the fixed block according to an embodiment of the present invention. Figure 5 is a top view of the disk according to an embodiment of the present invention, viewed from above. Figure 6 is a side view of the disk according to an embodiment of the present invention, viewed from the side. Figure 7 is a perspective view showing the disk according to an embodiment of the present invention. Figure 8 is a bottom view of the blade according to an embodiment of the present invention, viewed from below. Figure 9 is a side view of the blade according to an embodiment of the present invention, viewed from the side. Figure 10 is a perspective view showing the blade according to an embodiment of the present invention.

[0030] Figure 11a is a perspective view showing a fixed block inserted axially into a disk according to an embodiment of the present invention; Figure 11b is a perspective view showing a fixed block according to an embodiment of the present invention moved circumferentially along a block insertion groove formed in the disk; Figure 11c is a perspective view illustrating the process of assembling a blade according to an embodiment of the present invention onto a disk; Figure 11d is a perspective view showing the process of inserting a fixed block according to an embodiment of the present invention into a block insertion groove and a block assembly groove; and Figure 12 is an enlarged view of a part of a gas turbine according to an embodiment of the present invention, showing a state in which the fixed blocks are continuously assembled in the circumferential direction.

[0031] Hereinafter, an embodiment of a turbine blade including a dovetail according to the present invention will be described in detail with reference to Figures 1 and 2. Referring to Figure 1, an example of a gas turbine 100 to which one embodiment of the turbine blades according to the present invention is attached is shown. The gas turbine comprises a housing 102, and a diffuser 106 is provided on the rear side of the housing 102 to discharge the combustion gas that has passed through the turbine. A combustor 104 is positioned in front of the diffuser 106 to receive a supply of compressed air and burn it.

[0032] To explain in terms of the direction of airflow, the compressor section 110 is located upstream of the housing 102, and the turbine section 120 is located downstream. Between the compressor section 110 and the turbine section 120, a torque tube 130 is positioned as a torque transmission member that transmits the rotational torque generated in the turbine section to the compressor section.

[0033] The compressor section 110 is provided with a plurality (for example, 14) of compressor rotor discs 140, and each of the compressor rotor discs 140 is fastened together by tie bolts 150 so as not to be separated in the axial direction.

[0034] Specifically, each of the compressor rotor discs 140 is aligned axially with respect to each other, with the tie bolt 150 passing through approximately their center. Here, adjacent compressor rotor discs 140 are positioned such that their opposing surfaces are pressed together by the tie bolt 150, making relative rotation impossible.

[0035] Multiple blades 144 are radially connected to the outer circumferential surface of the compressor rotor disk 140. Each of the blades 144 is equipped with a dovetail portion 146 and is fastened to the compressor rotor disk 140.

[0036] Between each of the rotor discs 140, there are vanes (not shown) fixed to the housing. Unlike the rotor discs, the vanes are fixed so as not to rotate and serve to align the flow of compressed air that has passed through the blades of the compressor rotor discs, guiding the air to the blades of the rotor disc located downstream.

[0037] The fastening method for the dovetail portion 146 can be tangential or axial. This can be selected according to the required structure of the commercial gas turbine and can have the commonly known dovetail or fir-tree form. In some cases, the blades can be fastened to the rotor disk using other fastening devices other than those described above, such as fasteners such as keys or bolts.

[0038] The tie bolt 150 is positioned to penetrate the center of the multiple compressor rotor discs 140 and turbine rotor discs 180, with one end fastened into the compressor rotor disc located on the upstream side, and the other end fastened by a fixing nut 190.

[0039] The form of the tie bolt 150 can consist of various structures depending on the gas turbine, and is not necessarily limited to the form shown in Figure 1. That is, as shown, it may have a form in which a single tie bolt penetrates the center of the rotor disc, or it may have a form in which multiple tie bolts are arranged around the circumference, and combinations of these are also possible.

[0040] Although not shown in the diagram, gas turbine compressors can be equipped with vanes that act as guide vanes after the diffuser to adjust the flow angle of the fluid flowing into the combustor inlet to the design flow angle after increasing the fluid pressure; these vanes are called deswarlers.

[0041] In the combustor 104, the incoming compressed air is mixed with fuel and burned to generate a high-energy, high-temperature, high-pressure combustion gas, and the temperature of the combustion gas is raised to the heat resistance limit that the combustor and turbine components can withstand during the isobaric combustion process.

[0042] The combustors that make up the combustion system of a gas turbine can be arranged in multiples within a casing formed in a cell shape, and consist of a burner including fuel injection nozzles, a combustor liner that forms the combustion chamber, and a transition piece that connects the combustor to the turbine.

[0043] Specifically, the liner provides a combustion space in which fuel injected by a fuel nozzle is mixed with compressed air from a compressor and burned. Such a liner may include a flame tube that provides a combustion space in which the fuel mixed with air is burned, and a flow sleeve that surrounds the flame tube and forms an annular space. A fuel nozzle is coupled to the front end of the liner, and a spark plug is coupled to the side wall.

[0044] Meanwhile, a transition piece is connected to the rear end of the liner to allow combustion gases, which are burned by the spark plug, to be sent to the turbine. The outer wall of such a transition piece is cooled by compressed air supplied from the compressor to prevent damage from the high temperature of the combustion gases.

[0045] For this purpose, the transition piece is provided with cooling holes that allow air to be injected into it. The compressed air flows through the holes to cool the main body inside before flowing towards the liner.

[0046] Cooling air, which has cooled the transition piece described above, flows through the annular space of the liner, and compressed air from outside the flow sleeve can be supplied as cooling air through cooling holes provided in the flow sleeve and collide with the outer wall of the liner.

[0047] Meanwhile, the high-temperature, high-pressure combustion gases discharged from the combustor are supplied to the turbine section 120. The expansion of the supplied high-temperature, high-pressure combustion gases impulses and reaction forces on the turbine blades, generating rotational torque. This rotational torque is transmitted to the compressor section via the torque tube, and any power exceeding the power required to drive the compressor is used to drive a generator or the like.

[0048] The turbine section is basically similar in structure to the compressor section. That is, the turbine section 120 is also provided with a plurality of turbine rotor discs 180 similar to the compressor rotor disc of the compressor section. Therefore, the turbine rotor discs 180 also include a plurality of turbine blades 184 arranged radially. The turbine blades 184 can also be coupled to the turbine rotor discs 180 by a method such as a dovetail. Furthermore, vanes (not shown) fixed to the housing are provided between the blades 184 of the turbine rotor discs 180 to guide the flow direction of the combustion gases passing through the blades.

[0049] Referring to Figure 2, the turbine rotor disk 180 has a substantially disc shape, and a plurality of coupling slots 180a are formed on its outer circumference. The coupling slots 180a are formed to have a fir-tree-shaped curved surface.

[0050] The turbine blade 184 is fastened to the coupling slot 180a. In Figure 2, the turbine blade 184 has a flat platform portion 184a in its approximate center. The platform portion 184a of an adjacent turbine blade is in contact with the platform portion 184a of that blade and its side surface, and plays a role in maintaining the spacing between the blades.

[0051] A blade portion 184c is formed on the upper surface of the platform portion 184a. The blade portion 184c is formed to have an airfoil shape optimized according to the specifications of the gas turbine, and has a leading edge positioned on the upstream side and a trailing edge positioned on the downstream side with respect to the direction of combustion gas flow.

[0052] Unlike the blades of the compressor section, the blades of the turbine section are in direct contact with the high-temperature, high-pressure combustion gas. Since the temperature of the combustion gas reaches a high temperature of approximately 1700°C, a cooling means is required. For this purpose, the compressor section has a cooling channel that extracts compressed air from a portion of it and supplies it to the blades on the turbine section side.

[0053] The cooling channel may extend from outside the housing (external channel) or penetrate through the inside of the rotor disk (internal channel), and both external and internal channels may be used. In Figure 2, a plurality of film cooling holes 184d are formed on the surface of the blade portion, and the film cooling holes 184d communicate with a cooling channel (not shown) formed inside the blade portion 184c, and serve to supply cooling air to the surface of the blade portion 184c.

[0054] A root portion, or dovetail portion, 184b, is formed on the bottom surface of the platform portion 184a. The dovetail portion 184b has a so-called axial-type configuration, which is inserted into the coupling slot 180a of the rotor disk 180 along the axial direction of the rotor disk 180.

[0055] The dovetail portion 184b has a substantially fir-shaped bend, which is formed to correspond to the shape of the bend formed in the coupling slot. Here, the coupling structure of the dovetail portion does not necessarily have to be fir-shaped, and may be formed to have a dovetail shape.

[0056] Here, the coupling slots 180a are arranged radially along the outer circumferential surface of the rotor disk. The internal shape of the coupling slots 180a corresponds to the shape of the dovetail portion 184b. Typically, when the coupling slots 180a are formed to be larger than the dovetail portion 184b and coupled, a gap is formed between the surface of the dovetail portion and the surface of the coupling slot. Such a gap allows the dovetail portion to be more easily fastened to the coupling slot. By coupling the dovetail portion to the coupling slot, the blade is fixed so as not to move in the radial direction of the rotor disk. Furthermore, although not shown in the diagram, a coupling pin is fastened between the dovetail portion and the coupling slot to fix the axial movement of the dovetail portion.

[0057] Referring to Figures 1 to 12, the gas turbine 200 according to an embodiment of the present invention includes blades 230, disks 210, and a fixed block 250. Figures 2 to 11d relate to the assembly structure of the disk 210 and the blade 230. Here, the disk 210 may be the compressor rotor disk 140 shown in Figure 1, or the turbine rotor disk 180 shown in Figures 1 and 2. The blade 230 may be the compressor blade 144 shown in Figure 1, or the turbine blade 184 shown in Figures 1 and 2. All of them basically have in common that the rotating blade is fixed to the disk under centrifugal force by fitting together dovetail or rump-shaped concave and convex bends.

[0058] Hereinafter, the compressor rotor disc 140 and the turbine rotor disc 180 will be collectively referred to as disc 210. The compressor blade 144 and the turbine blade 184 will be collectively referred to as blade 230.

[0059] The blade 230 has a root portion 235 formed therein. The disk 210 has a disk slot 213 into which the root portion 235 is inserted. Specifically, the disk 210 is formed in a disc shape, and multiple disk slots 213 can be formed on its outer circumference along the circumferential direction. Bent surfaces can be formed in the disk slots 213. Here, the disk slots 213 have a different shape from the aforementioned coupling slots 180a (see Figure 2), but they perform the same function. Grooves extending along the circumferential direction can be formed in the disk 210.

[0060] The blades 230 can be arranged radially around the edge of the disk 210 and can be joined in a dovetail configuration. Specifically, the root portion 235 of the blade 230 can be inserted into the disk slot 213 of the disk 210. The root portion 235 can have a curved surface that engages with the curved surface of the disk slot 213, and the root portion 235 can have an axial-type configuration that is inserted into the disk slot 213 along the axial direction. Here, the root portion 235 has a different configuration from the dovetail portion 184b (see Figure 2) described above, but can perform the same role.

[0061] The blade 230 can have grooves formed that extend along the circumferential direction. The fixing block 250 is inserted circumferentially into grooves formed in the blade 230 and grooves formed in the disk 210, and is provided to fix the axial and radial positions of the blade 230 relative to the disk 210.

[0062] Specifically, the fixing block 250 is intended to prevent the blade 230, which is of the axial type and coupled to the disk 210, from detaching during operation of the gas turbine 200, and plays the role of fixing the blade 230 to the disk 210.

[0063] The fixing block 250 can consist of a single part, which simplifies the fixing structure and improves the ease of assembly and disassembly. Furthermore, by assembling the fixing block 250 radially to the blade 230 and the disc 210 simultaneously, it is possible to prevent the blade 230 from detaching from the disc 210 in the axial direction.

[0064] On the other hand, the disk 210 may include a disk body 211 and a block insertion groove 215. The disk body 211 can have a disk slot 213 formed therein. The block insertion groove 215 can be provided so that a fixed block 250 can be inserted, and can extend in the circumferential direction.

[0065] Specifically, the disk body 211 is the body that constitutes the disk 210, and the block insertion groove 215 can be formed in a concave shape in the disk body 211. The block insertion groove 215 can be formed to correspond to the shape of the block portion so that a part of the block portion is inserted, and can extend in the circumferential direction.

[0066] The block insertion groove 215 can be formed with a T-shaped cross-section perpendicular to the circumferential direction. Specifically, the block insertion groove 215 extends in the circumferential direction, allowing multiple fixed blocks 250 to be inserted continuously. Furthermore, the block insertion groove 215 can be configured such that its cross-sectional shape, when viewed from the side, is T-shaped, preventing the inserted fixed blocks 250 from detaching in the axial direction.

[0067] More specifically, the disk body 211 may further include a pair of anti-detachment projections 216 for forming a block insertion groove 215. Furthermore, by having one of the pair of anti-detachment projections 216 extend radially and the other extend toward the central axis of the disk 210 and face each other, the block insertion groove 215 can be formed to have a T-shape when viewed from the side.

[0068] In other words, a pair of anti-detachment projections 216 can be formed at the entrance of the opening of the block insertion groove 215, facing each other with respect to the radial direction, and spaced apart. This allows the size of the opening of the block insertion groove 215 to be narrower than other parts. The shape of such anti-detachment projections 216 allows the side shape or side cross-sectional shape of the block insertion groove 215 to be formed in a T shape.

[0069] The spaced-apart portions of the pair of anti-detachment projections 216 can form an opening in the block insertion groove 215. When the fixed block 250 is inserted into the block insertion groove 215, it can be exposed to the outside through the opening in the block insertion groove 215. After the assembly of the disc 210, blade 230, and fixed block 250 is complete, the worker can check the assembled state of the fixed block 250 through the opening.

[0070] The blade 230 may further include a blade body 231 and a platform portion 233 formed between the blade body 231 and the root portion 235.

[0071] Specifically, the platform portion 233 is formed at the radial center of the blade 230, the blade body 231 is provided on the radially outer side of the platform portion 233, and the root portion 235 can be formed on the axially inner side of the platform portion 233.

[0072] For example, the platform portion 233 may be inserted into the disk 210 as shown in Figure 3, or it may be positioned outside the disk 210 as shown in Figure 2, with its side surface in contact with the platform portion 233 of an adjacent blade 230, thus playing a role in maintaining the spacing between the blades 230.

[0073] The root section 235 is provided for the insertion of the fixed block 250 and may include a block assembly groove 237 extending in the circumferential direction. Specifically, the block assembly groove 237 can be formed in a concave shape in the root portion 235. The block assembly groove 237 can extend in the circumferential direction, thereby allowing the fixed block 250 to slide circumferentially out of the block assembly groove 237 and be inserted.

[0074] Furthermore, the block assembly groove 237 can be formed to open toward the central axis of the disk 210, thereby enabling it to communicate with the block insertion groove 215.

[0075] The block assembly groove 237, together with the block insertion groove 215, can form a sliding groove into which the fixed block 250 is inserted when the blade 230 and the disc 210 are joined.

[0076] Specifically, the slide groove is a groove formed by the block assembly groove 237 and the block insertion groove 215 during the assembly of the disc 210 and the blade 230. The fixed block 250 can be partially inserted into the block assembly groove 237 and the remaining part can be inserted into the block insertion groove 215. In this case, the slide groove can extend in the circumferential direction. As a result, when the fixed block 250 is inserted into the slide groove, the fixed block 250 can prevent the blade 230 from coming out in the axial direction of the disc 210.

[0077] The sliding groove can be formed in a shape that corresponds to the fixed block 250. In other words, the slide groove is divided into a block assembly groove 237 located in the central region with respect to the circumferential direction, and block insertion grooves 215 located on both sides of the block assembly groove 237, and an opening can be formed that opens toward one side in the axial direction. The slide groove is a groove formed by the block insertion groove 215 and the block assembly groove 237 when the blade 230 and the disc 210 are assembled.

[0078] Furthermore, the fixed block 250 can be configured such that a portion of it is inserted into the block assembly groove 237, and the remaining portion of the fixed block 250 is inserted into the block insertion groove 215.

[0079] This allows the fixing block 250 to be assembled to the disk 210 and the blade 230 simultaneously. This prevents the fixing block 250 from detaching from the disk 210.

[0080] The root portion 235 may further include assembly ribs 236. The assembly ribs 236 may extend toward the central axis of the disk 210 to form a block assembly groove 237. That is, the assembly ribs 236 are protruding portions that, together with the root portion 235 body, form the block assembly groove 237.

[0081] Specifically, the assembly rib 236 can extend toward the central axis of the disk 210. This shape allows the block assembly groove 237 to be formed with an opening toward the central axis of the disk 210. The open portion of the block assembly groove 237 can communicate with the block insertion groove 215. Furthermore, the side shape or side cross-sectional shape of the block assembly groove 237 can be formed in a U-shape.

[0082] Furthermore, the axial end of the assembly rib 236 can be located further from the central axis of the disk 210 than the axial end of the root portion 235. In other words, the distance from the platform portion 233 to the end of the assembly rib 236 can be shorter than the distance from the platform portion 233 to the end of the root portion 235.

[0083] This is to insert the fixed block 250 into the block assembly groove 237 formed by the assembly rib 236. The shape and size of the assembly rib 236 make it possible to stably assemble the root portion 235 into the disk slot 213 and to realize a structure in which a groove for assembling the fixed block 250 is formed.

[0084] On the other hand, referring to Figure 12, multiple fixed blocks 250 can be provided. The slide groove can have openings at both ends in the circumferential direction. Multiple fixed blocks 250 can be arranged in the slide groove along the circumferential direction.

[0085] Specifically, both circumferential ends of the slide groove are open, allowing the fixed block 250 to be inserted into the slide groove by sliding along its circumference. With this structure, if the circumferential length of the fixed block 250 is smaller than the circumferential length of the slide groove, multiple fixed blocks 250 can be repeatedly arranged along the circumference in a single slide groove. For example, multiple fixed blocks 250 can be arranged in a continuous manner as shown in the illustrated embodiment.

[0086] Furthermore, the assembly of the disc 210 and blade 230 can be assembled continuously in the circumferential direction, in which case the slide grooves provided in each assembly can be continuous. Then, as shown in the figure, the fixed block 250 can be assembled continuously. In this case, since the fixed block 250 is a single part and not a part formed by separate assembly, it is easy to assemble it continuously in a simple process.

[0087] By assembling multiple fixing blocks 250 in a continuous manner, the fixing force between the disk 210 and the blade 230 can be further improved. Therefore, it is possible to more effectively prevent the blade 230 from detaching from the disk 210 during operation of the gas turbine 200.

[0088] On the other hand, referring to Figure 4, the fixed block 250 may include an insertion portion 251 and an exposed portion 255. The insertion portion 251 can be inserted into the block assembly groove 237 and the block insertion groove 215.

[0089] The exposed portion 255 is formed integrally with the insertion portion 251 and can protrude in one axial direction. Here, the exposed portion 255 can be provided so as to be exposed to the outside of the slide groove through the opening when the fixed block 250 is assembled into the slide groove.

[0090] This allows workers to visually confirm that the fixed block 250 is assembled with the blade 230 and disk 210. Furthermore, even after the assembly of all the gas turbine 200 components is complete, the assembly status of the fixed block 250 can be checked using borescope inspection. Here, borescope inspection refers to an inspection in which an optical device combining lighting and lenses is inserted into a specific part of the engine, etc., and the resulting image is observed.

[0091] The fixed block 250 can be formed with a T-shaped cross-section perpendicular to the circumferential direction. In other words, the fixed block 250 and the slide groove can be formed in corresponding shapes. The fixed block 250 has a shape in which an exposed portion 255 protrudes from the central region of the insertion portion 251, so that the side or side cross-sectional shape can be formed in a T shape. The side or side cross-sectional shape of the slide groove can then be formed in a corresponding shape.

[0092] The process of assembling the disk 210, blade 230, and fixed block 250 will be described below with reference to Figures 11a to 11d. First, referring to Figure 11a, the fixed block 250 can be inserted into the block insertion groove 215 of the disk 210 in the direction D3 toward the axis. Here, the block insertion groove 215 can communicate with the block assembly groove 237 and can extend in the circumferential direction D2 (see Figure 11b).

[0093] Then, as shown in the example in Figure 11b, the fixed block 250 can be slid along the circumferential direction D2 of the block insertion groove 215. In this case, the fixed block 250 can be moved to an area that does not interfere with the disk slot 213, so that the root portion 235 can be easily inserted.

[0094] Referring to Figure 11c below, the root portion 235 can be inserted into the disk slot 213 in a direction D1 parallel to the axial direction. That is, the fixed block 250 can be assembled onto the disk 210 first, and then the blade 230 can be assembled onto the disk 210.

[0095] Subsequently, as shown in the embodiment in Figure 11d, the fixed block 250 can be slid in the circumferential direction D2. In this case, a portion of the fixed block 250 can be inserted into the block assembly groove 237, and the remaining portion can be inserted into the block insertion groove 215.

[0096] Through this process, the fixing block 250 can be assembled to secure the blade 230 to the disk 210. However, the process for assembling the fixing block 250 is not limited to the embodiments shown in Figures 11a and 11b, and other methods may be applied as long as the fixing block 250 can be inserted simultaneously into the block assembly groove 237 and the block insertion groove 215.

[0097] According to embodiments of the present invention, the fixed block prevents the blades from axially separating from the disk under any operating conditions of the gas turbine.

[0098] Furthermore, according to the embodiments of the present invention, since there are no bent portions in the fixed assembly parts, there are advantages such as easier management of parts and the ability to reuse parts.

[0099] Furthermore, according to the embodiments of the present invention, when replacing the blade, only the fixing assembly that secures the blade needs to be disassembled and reassembled, thus simplifying the blade replacement process. Consequently, since the blade and disc can be manufactured and assembled with a simple structure, work efficiency is improved and costs can be reduced.

[0100] Although specific embodiments of the present invention have been described above, the spirit and scope of the present invention are not limited to these specific embodiments, and various modifications and variations are possible by persons with ordinary skill in the art to which the present invention pertains, provided that the gist of the present invention as described in the claims is not altered. [Explanation of symbols]

[0101] 100, 200: Gas turbine 210: Disk 211: Disc body 213: Disk slot 215: Block insertion groove 216: Anti-detachment protrusion 230: Blade 231: Blade Body 233: Platform Department 235: Route section 236: Assembly Rib 237: Block assembly groove 250: Fixed Block 251: Insertion part 255:Exposed part

Claims

1. A blade with a root section formed, A disk having a disk slot into which the root portion is inserted, A fixing block is provided to be inserted circumferentially into the groove formed in the blade and the groove formed in the disk, and to fix the axial position and radial position of the blade relative to the disk, A gas turbine, including

2. The aforementioned disk is The disk body on which the disk slot is formed, The gas turbine according to claim 1, comprising a block insertion groove extending in the circumferential direction, provided for the insertion of the aforementioned fixed block.

3. The aforementioned block insertion groove is The gas turbine according to claim 2, wherein the cross-sectional shape perpendicular to the circumferential direction is formed in a T-shape.

4. The aforementioned disk body is It further includes a pair of detachment prevention protrusions for forming the block insertion groove, The block insertion groove is formed in a T-shape, such that one of the pair of anti-detachment projections extends radially and the other extends toward the central axis of the disk and is formed opposite to one another. The gas turbine according to claim 3, wherein the block insertion groove is formed to open toward one side in the axial direction.

5. The aforementioned blade is Blade body and A gas turbine according to any one of claims 2 to 4, further comprising a platform portion formed between the blade body and the root portion.

6. The aforementioned root section is A gas turbine according to any one of claims 2 to 4, comprising a block assembly groove extending in the circumferential direction, into which the aforementioned fixed block is inserted.

7. The aforementioned block assembly groove is The gas turbine according to claim 6, wherein, when the blade and the disk are coupled, a slide groove into which the fixed block is inserted is formed together with the block insertion groove.

8. The aforementioned slide groove is Based on the circumferential direction, it is divided into the block assembly groove located in the central region and the block insertion grooves located on both sides of the block assembly groove, and an opening is formed that is open toward one side in the axial direction. The gas turbine according to claim 7, wherein a portion of the fixed block is inserted into the block assembly groove, and the remaining portion of the fixed block is inserted into the block insertion groove.

9. The aforementioned root section is The assembly ribs further extend toward the central axis of the disk and form the block assembly groove, The position of the axial end of the assembly rib is, The gas turbine according to claim 7, wherein the position is located further from the central axis of the disk than the position of the axial end of the root portion.

10. The aforementioned fixed block is The block assembly groove and the block insertion groove are insertion parts that are inserted into each other. It includes an exposed portion formed integrally with the insertion portion and protruding in one direction in the axial direction, The exposed portion is, The gas turbine according to claim 8, wherein the fixed block is provided to be exposed to the outside of the slide groove through the opening when the fixed block is assembled into the slide groove.

11. The aforementioned fixed block is The gas turbine according to claim 8, wherein the cross-sectional shape perpendicular to the circumferential direction is formed in a T-shape.

12. Multiple fixed blocks are provided, The aforementioned slide groove has openings at both ends in the circumferential direction. The gas turbine according to claim 7, wherein the plurality of fixed blocks are arranged circumferentially in the slide groove.

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