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 includes a blade 230 having a root portion 235 and a block assembly groove, a disk 210 having a disk slot 213 into which the root portion is inserted, a block insertion groove, and a pin insertion hole, and a fixing assembly 250 provided to fix the axial and radial positions of the blade with respect to the disk, the fixing assembly including a block assembly groove, a block portion 251 inserted into the block insertion groove, and a pin portion 255 that penetrates the pin insertion hole and connects with the block portion.

Description

Technical Field

[0001] This application claims the benefit of priority based on Korean Patent Application No. 10-2024-0171882 filed on November 27, 2024, and all the contents disclosed in the document of the Korean patent application are incorporated herein by reference. 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 includes 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 central parts 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 of 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 greatly reduced, and it has the advantage of being able to perform 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 project] [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 separating from the disk in the axial and circumferential directions 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 having a root portion and a block assembly groove, a disk having a disk slot into which the root portion is inserted, a block insertion groove, and a pin insertion hole, and a fixing assembly provided to fix the axial and radial positions of the blade with respect to the disk, wherein the fixing assembly includes a block portion inserted into the block assembly groove and the block insertion groove, and a pin portion that penetrates the pin insertion hole and connects with the block portion.

[0014] The disk further includes a disk body in which the disk slot is formed, and the block insertion groove is formed in the disk body, is concave in shape so as to which the block portion is inserted, and can extend in the circumferential direction. The block insertion groove can be formed to open radially outward and toward the blade.

[0015] The pin insertion hole can be drilled in the disk body so as to connect the inside and outside of the block insertion groove, and can be formed to extend in the axial direction. The blade may further include a blade body and a platform portion formed between the blade body and the root portion.

[0016] The block assembly groove can be formed in a concave shape in the platform portion so that the block portion can be inserted, and can be formed to open radially outward and toward the block insertion groove.

[0017] When assembling the blade and the disc, the block assembly groove and the block insertion groove both form a fixed block groove, and the fixed block groove can be formed in a shape corresponding to the block portion so that the block portion is inserted.

[0018] The fixed block groove is divided into a block assembly groove located on one side and a block insertion groove located on the other side, with respect to the circumferential direction, and an opening is formed that opens radially outward, so that a part of the block is inserted into the block assembly groove and the remaining part of the block is inserted into the block insertion groove.

[0019] When assembling the blade, the disc, and the fixing assembly, the pin portion can be assembled so as to be exposed to the outside of the pin insertion hole, and the block portion can be assembled so as to be exposed to the outside of the fixing block groove. The block portion and the pin portion can be connected by screws. [Effects of the Invention]

[0020] According to embodiments of the present invention, the fixed assembly can prevent the blades from detaching from the disk in the axial and circumferential directions under any operating conditions of the gas turbine.

[0021] 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.

[0022] Furthermore, according to the embodiment 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.

[0023] Furthermore, when using the fixed assembly according to the embodiment of the present invention, the blade and disc can be manufactured and assembled with a simple structure, thus improving work efficiency and reducing costs.

Brief Description of the Drawings

[0024] [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 assembled structure of a disk and blades 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, blades, and a fixing assembly in an enlarged manner. [Figure 4] It is a perspective view showing a fixing assembly according to an embodiment of the present invention. [Figure 5] It is a top view of a disk according to an embodiment of the present invention as viewed from above. [Figure 6] It is a front view of a disk according to an embodiment of the present invention as viewed from the front. [Figure 7] It is a perspective view showing a disk according to an embodiment of the present invention. [Figure 8] It is a top view of a blade according to an embodiment of the present invention as viewed from above. [Figure 9] It is a front view of a blade according to an embodiment of the present invention as viewed from the front. [Figure 10] It is a perspective view showing a blade according to an embodiment of the present invention. [Figure 11a] It is a perspective view showing a state in which a blade and a disk according to an embodiment of the present invention are assembled. [Figure 11b] It is a perspective view showing a state in which a block portion according to an embodiment of the present invention is assembled to a blade and a disk. [Figure 11c] It is a perspective view showing a state in which a pin portion according to an embodiment of the present invention is assembled. [Figure 11d] It is a perspective view for explaining a caulking operation according to an embodiment of the present invention.

Modes for Carrying Out the Invention

[0025] 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.

[0026] 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.

[0027] 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 disk, blade and fixed assembly; Figure 4 is a perspective view showing a fixed assembly 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 front view of the disk according to an embodiment of the present invention, viewed from the front; Figure 7 is a perspective view showing the disk according to an embodiment of the present invention; Figure 8 is a top view of the blade according to an embodiment of the present invention, viewed from above; Figure 9 is a front view of the blade according to an embodiment of the present invention, viewed from the front; and Figure 10 is a perspective view showing the blade according to an embodiment of the present invention.

[0028] Figure 11a is a perspective view showing the assembled blade and disc according to an embodiment of the present invention; Figure 11b is a perspective view showing the assembled block portion of the present invention on the blade and disc; Figure 11c is a perspective view showing the assembled pin portion according to an embodiment of the present invention; and Figure 11d is a perspective view illustrating the caulking work according to an embodiment of the present invention.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] 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.

[0043] 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 to the liner side.

[0044] 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.

[0045] 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] Referring to Figures 2 to 11d, the gas turbine 200 according to an embodiment of the present invention includes blades 230, disks 210, and a fixed assembly 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 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.

[0056] 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.

[0057] The blade 230 has a root portion 235 and a block assembly groove 237. The disk 210 has a disk slot 213 into which the root portion 235 is inserted, a block insertion groove 215, and a pin insertion hole 216.

[0058] Specifically, the disk 210 is formed in a disc shape, and multiple disk slots 213 can be formed along the circumferential direction on its outer circumference. 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.

[0059] The disk 210 has a block insertion groove 215 formed therein, which can be concave and open outward in the circumferential direction. The pin insertion hole 216 can be formed to communicate with the block insertion groove 215.

[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. A block assembly groove 237 is formed in the blade 230, and the block assembly groove 237 can be formed in a concave shape.

[0061] The fixed assembly 250 is provided to fix the axial and radial positions of the blade 230 relative to the disk 210. Specifically, the fixed assembly 250 is intended to prevent the blades 230, which are axially coupled to the disk 210, from detaching during operation of the gas turbine 200, and plays a role in fixing the blades 230 to the disk 210.

[0062] More specifically, the fixed assembly 250 includes a block portion 251 and a pin portion 255. The block portion 251 is inserted into the block assembly groove 237 and the block insertion groove 215. The pin portion 255 then passes through the pin insertion hole 216 and connects with the block portion 251.

[0063] The block portion 251 is assembled between the blade 230 and the disk 210, preventing the blade 230 from detaching in the axial direction. The pin portion 255 is assembled between the block portion 251 and the disk 210, preventing the block portion 251 from detaching in the circumferential direction, and as a result, indirectly preventing the blade 230 from detaching. In this way, the fixing assembly 250 can fix the blade 230 to the disk 210 by applying a simple coupling structure of the block portion 251 and the pin portion 255.

[0064] For example, the block portion 251 and the pin portion 255 can be connected by screws. After the block portion 251 is inserted into the block assembly groove 237 and the block insertion groove 215, the pin portion 255 can be assembled with the block portion 251 by passing through the pin insertion hole 216. For example, a screw thread may be formed on the outer surface of the end of the pin portion 255, and a screw groove may be formed in the block portion 251 to screw-connect the end of the pin portion 255. With such a structure, the block portion 251 and the pin portion 255 can be screw-connected.

[0065] However, the screw connection structure between the block portion 251 and the pin portion 255 is not limited to the one described above; it can be modified and implemented in various structures as long as the pin portion 255 can be screw-connected to the block portion. Furthermore, the connection between the block portion 251 and the pin portion 255 is not limited to a screw connection structure.

[0066] On the other hand, the disk 210 may further include a disk body 211 into which the disk slot 213 is formed. The block insertion groove 215 is formed in the disk body 211, is concave in shape so that the block portion 251 is inserted, and may extend in the circumferential direction.

[0067] 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 251 so that a part of the block portion 251 is inserted into it, and can extend in the circumferential direction.

[0068] Here, the block insertion groove 215 can be formed to open radially outward and toward the blade 230. The block insertion groove 215 opens radially outward, allowing the block portion 251 to be easily inserted into the block insertion groove 215. The block insertion groove 215 can communicate with the block assembly groove 237 when inserted in the direction toward the blade 230, i.e., in the circumferential direction.

[0069] The pin insertion hole 216 is drilled in the disk body 211 so as to connect the inside and outside of the block insertion groove 215, and can extend in the axial direction. Specifically, the pin insertion hole 216 is formed by drilling into the disk body 211 and can be formed to extend in the axial direction. The pin insertion hole 216 can communicate with the block insertion groove 215 and can also communicate the block insertion groove 215 with the outside of the disk body 211. As a result, when the pin portion 255 is inserted into the pin insertion groove, one axial end of the pin portion 255 can be coupled to the block portion 251, and the other axial end of the pin portion 255 can be exposed to the outside of the disk 210.

[0070] On the other hand, 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 inner side of the platform portion 233 in the direction toward the axis.

[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 block assembly groove 237 is formed in a concave shape in the platform portion 233 so that the block portion 251 can be inserted, and it can be formed to open radially outward and toward the block insertion groove 215.

[0074] Specifically, the block assembly groove 237 can be formed in a concave shape in the platform portion 233 and open radially outward. This allows the block portion to be easily inserted into the block assembly groove 237. Furthermore, the block assembly groove 237 can communicate with the block insertion groove 215 by being formed to open toward the block insertion groove 215.

[0075] During the assembly of the blade 230 and the disc 210, both the block assembly groove 237 and the block insertion groove 215 can form a fixed block groove. The fixed block groove can then be formed to a shape corresponding to the block portion 251 so that the block portion 251 can be inserted.

[0076] Specifically, the fixed block groove refers to the groove formed by the block assembly groove 237 and the block insertion groove 215 when the disc 210 and the blade 230 are joined. In other words, the fixed block groove is a groove formed in the assembled state of the disc 210 and the blade 230. A portion of the block portion 251 is inserted into the block assembly groove 237, and the remaining portion is inserted into the block insertion groove 215. In this case, the fixed block groove can extend in the circumferential direction. As a result, when the block portion 251 is inserted into the fixed block groove, the block portion 251 can prevent the blade 230 from axially separating from the disc 210.

[0077] The fixing block groove can be formed in a shape corresponding to the block portion 251. For example, the block portion 251 is formed in a hexahedral shape as shown in the illustrated embodiment, and the fixing block groove can be formed in a shape corresponding to it.

[0078] In other words, the fixed block groove is divided into a block assembly groove 237 located on one side and a block insertion groove 215 located on the other side, with respect to the circumferential direction, and an opening can be formed that opens radially outward.

[0079] The block portion 251 can be configured such that a part of it is inserted into the block assembly groove 237, and the remaining part of the block portion 251 is inserted into the block insertion groove 215.

[0080] This allows the block section 251 to be assembled to the disk 210 and the blade 230 simultaneously. As a result, the fixed assembly 250 can prevent the blade 230 from detaching from the disk 210.

[0081] When assembling the blade 230, disc 210, and fixed assembly 250, the pin portion 255 is assembled so that it is exposed to the outside of the pin insertion hole 216, and the block portion 251 is assembled so that it is exposed to the outside of the fixed block groove.

[0082] Specifically, one end of the pin portion 255 in the extension direction is screw-connected to the block portion 251, and the other end can be exposed to the outside by passing through the pin insertion hole 216. The fixing block groove opens radially outward, and the block portion 251 can be exposed to the outside after assembly by being inserted through the open portion of the fixing block groove.

[0083] This allows the worker to visually confirm that the block section 251 and pin section 255 are assembled to 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 assembly 250 can be confirmed by 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 or other component, and the resulting image is observed.

[0084] The process of assembling the disk 210, blade 230, and fixed assembly 250 will be described below with reference to Figures 11a to 11d. First, referring to Figure 11a, the root portion 235 of the blade 230 can be inserted into the disk slot 213 of the disk 210 in a direction D1 parallel to the axial direction.

[0085] Then, as shown in the example in Figure 11b, the block portion 251 of the fixed assembly 250 can be inserted into both the block assembly groove 237 and the block insertion groove 215. In this case, the block portion 251 can extend in the circumferential direction, and the block assembly groove 237 and the block insertion groove 215 can be formed to face each other in the circumferential direction. The block portion 251 can be inserted into the block assembly groove 237 and the block insertion groove 215 in the direction D31 toward the axis.

[0086] Next, referring to Figure 11c, after the pin portion 255 is passed through the pin insertion hole 216, the pin portion 255 can be screw-connected to the block portion 251. In this case, the pin portion 255 can be inserted in a direction D1 parallel to the axis.

[0087] Subsequently, as shown in the example in Figure 11d, the gap between the pin portion 255 and the disc 210 can be minimized by caulking. Here, caulking refers to the process of using a blunt-tipped chisel 260 to tap the joint and eliminate the gap in order to maintain airtightness when riveting is performed in a pressure vessel. In the embodiment of the present invention, the chisel 260 can be used to eliminate the gap between the fixed assembly 250 and the disc 210 and blade 230.

[0088] According to such embodiments of the present invention, the fixed assembly can prevent the blades from detaching from the disk in the axial and circumferential directions under any operating conditions of the gas turbine.

[0089] According to embodiments of the present invention, the operator can visually confirm the state in which the fixed assembly is assembled to the blade and disc. 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.

[0090] Furthermore, according to the embodiment 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.

[0091] Furthermore, by using the fixed assembly according to the embodiment of the present invention, the blade and disc can be manufactured and assembled with a simple structure, thereby improving work efficiency and reducing costs.

[0092] 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]

[0093] 100, 200: Gas turbine 210: Disk 211: Disc body 213: Disk slot 215: Block insertion groove 216: Pin insertion hole 230: Blade 231: Blade Body 233: Platform Department 235: Route section 237: Block assembly groove 250: Fixed assembly 251: Block section 255: Pin part

Claims

1. A blade with a root section formed and a block assembly groove formed, A disk having a disk slot into which the root portion is inserted, a block insertion groove, and pin insertion holes, A fixing assembly is provided to fix the axial and radial positions of the blade relative to the disk, Includes, The aforementioned fixed assembly is The block portion inserted into the block assembly groove and the block insertion groove, A pin portion that penetrates the aforementioned pin insertion hole and connects with the aforementioned block portion, A gas turbine, including

2. The aforementioned disk is The disk body in which the disk slot is formed further includes The aforementioned block insertion groove is The gas turbine according to claim 1, wherein a recess is formed in the disk body into which the block portion is inserted, and extends in the circumferential direction.

3. The aforementioned block insertion groove is The gas turbine according to claim 2, which is formed to have openings in the radially outward direction and in the direction toward the blades.

4. The aforementioned pin insertion hole is The gas turbine according to claim 2, wherein the disk body is perforated so as to connect the inside and outside of the block insertion groove and is formed to extend in the axial direction.

5. The aforementioned blade is Blade body and The gas turbine according to claim 2, further comprising a platform portion formed between the blade body and the root portion.

6. The aforementioned block assembly groove is The gas turbine according to claim 5, wherein the platform portion is formed in a concave shape so as to be inserted into the block portion, and is formed to open radially outward and toward the block insertion groove.

7. When assembling the blade and the disk, The block assembly groove and the block insertion groove both form a fixed block groove. The gas turbine according to claim 6, wherein the fixed block groove is formed in a shape corresponding to the block portion so that the block portion can be inserted.

8. The aforementioned fixed block groove is Based on the circumferential direction, it is divided into a block assembly groove located on one side and a block insertion groove located on the other side, and an opening is formed that opens radially outward. The gas turbine according to claim 7, wherein a portion of the block portion is inserted into the block assembly groove, and the remaining portion of the block portion is inserted into the block insertion groove.

9. When assembling the blade, the disk, and the fixed assembly, The aforementioned pin portion is assembled so as to be exposed to the outside of the pin insertion hole. The gas turbine according to claim 7, wherein the block portion is assembled to be exposed to the outside of the fixed block groove.

10. The gas turbine according to any one of claims 1 to 9, wherein the block portion and the pin portion are screw-connected.

Images