Gas turbine

Abstract

A gas turbine (100) includes a blade (230), in which a root part (235) is formed and a block assembly groove (237) is formed, a disk (210), in which a disk slot (213), into which the root part (235) is inserted, is formed, a block insertion groove (215) is formed, and a pin insertion hole (216) is formed; and a fixing assembly (250) configured to fix an axial position and a radial position of the blade (230) with respect to the disk (210). The fixing assembly (250) includes: a block part (251) inserted into the block assembly groove (237) and the block insertion groove (215); and a pin part (255) passing through the pin insertion hole (216) to be coupled to the block part (251).

Description

[0001] This application claims the benefit of priority to Korean Patent Application No. 10-2024-0171882, filed in the Korean Intellectual Property Office on November 27, 2024.TECHNICAL FIELD

[0002] The present disclosure relates to a gas turbine.BACKGROUND

[0003] A turbine is a mechanical apparatus that obtains rotational force with impulse or reaction power by using a flow of a compressible fluid, such as steam or gas, and examples thereof include a steam turbine using steam and a gas turbine using high-temperature combustion gas.

[0004] Among these, the gas turbine mainly includes 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 a compressor casing.

[0005] The combustor supplies fuel to compressed air that is compressed in the compressor and ignites it with a burner, and thus, high-temperature and high-pressure combustion gas is generated.

[0006] The turbine has a plurality of turbine vanes and turbine blades that are alternately disposed in a turbine casing. Furthermore, a rotor is disposed to pass through the compressor, the combustor, the turbine, and a center of an exhaust chamber.

[0007] Opposite ends of the rotor are rotatably supported by bearings. Furthermore, a plurality of disks are fixed to the rotor, and the respective blades are connected thereto, and a drive shaft, such as a power generator, is connected to an end of the exhaust chamber.

[0008] The gas turbine does not have a reciprocating mechanism such as pistons of a four-stroke engine, and thus, there are no mutual frictional portions, such as a piston and a cylinder, resulting in extremely low consumption of lubricating oil, significantly reduced vibration characteristic of reciprocating machines, and high-speed operation.

[0009] Briefly describing the operation of the gas turbine, the air compressed in the compressor is mixed with the fuel and burned to generate high-temperature combustion gas, and the combustion gas generated in this way is injected toward the turbine. The injected combustion gas generates rotational force while passing through the turbine vanes and the turbine blades, and thus, the rotor is rotated.

[0010] The compressor and the turbine may have a structure, in which a plurality of blades are coupled to a disk. In this case, by fixing the blade to the disk by using a fixing component, the blade may be prevented from being separated from the disk during the operation of the gas turbine.

[0011] A conventional component for fixing the blade to the disk has a structure, in which three or more components are assembled, and one of the plurality of components for assembly includes a bent component.

[0012] However, in such a structure, the bent component has to be repurchased when the assembly is disassembled and reassembled, and due to the characteristics of the bent shape, it is difficult to ensure the assembly reliability of the bent component. Furthermore, it is difficult to visually identify it when the conventional method is used.SUMMARY

[0013] The present disclosure has been made to solve the above-mentioned problems occurring in the prior art while advantages achieved by the prior art are maintained intact.

[0014] An aspect of the present disclosure provides a gas turbine capable of preventing a blade from being separated from a disk in an axial direction and a circumferential direction under any operating condition of the gas turbine.

[0015] An aspect of the present disclosure also provides a gas turbine that is easy to manage in terms of fixing components and allows reuse of the components.

[0016] An aspect of the present disclosure also provides a gas turbine, by which blade replacement operations are facilitated, assembly and disassembly performance is improved, and costs are reduced.

[0017] The technical problems to be solved by the present disclosure are not limited to the aforementioned problems, and any other technical problems not mentioned herein will be clearly understood from the following description by those skilled in the art to which the present disclosure pertains.

[0018] According to an aspect of the present disclosure, a gas turbine includes a blade, in which a root part is formed and a block assembly groove is formed, a disk, in which a disk slot, into which the root part is inserted, is formed, a block insertion groove is formed, and a pin insertion hole is formed, and a fixing assembly that fixes an axial position and a radial position of the blade with respect to the disk, and the fixing assembly may include a block part that is inserted into the block assembly groove and the block insertion groove, and a pin part that passes through the pin insertion hole to be coupled to the block part.

[0019] The disk may further include a disk body, in which the disk slot may be formed, and the block insertion groove may be formed in the disk body, may be concavely formed such that the block part is inserted thereinto, and may extend in a circumferential direction.

[0020] The block insertion groove may be formed to be opened in a radially outward direction and a direction facing the blade.

[0021] The pin insertion hole may be formed in the disk body to communicate an interior and an exterior of the block insertion groove and may be formed to extend in an axial direction.

[0022] The blade may further include a blade body, and a platform part that is formed between the blade body and the root part.

[0023] The block assembly groove may be concavely formed in the platform part such that the block part is inserted thereinto, and may be formed to be opened in a radially outward direction and a direction that faces the block insertion groove.

[0024] When the blade and the disk are assembled, the block assembly groove and the block insertion groove together may form a fixing block groove, and the fixing block groove may be formed in a shape corresponding to the block part such that the block part is inserted thereinto.

[0025] The fixing block groove may be divided into the block assembly groove located on one side and the block insertion groove located on an opposite side with respect to the circumferential direction, and an opening opened toward a radially outer side may be formed, and a portion of the block part may be inserted into the block assembly groove, and the remaining portion of the block part may be inserted into the block insertion groove.

[0026] When the blade, the disk, and the fixing assembly are assembled, the pin part may be assembled to be exposed to an exterior of the pin insertion hole, and the block part may be assembled to be exposed to an exterior of the fixing block groove.

[0027] The block part and the pin part may be screw-coupled to each other.BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and other objects, features and advantages of the present disclosure will be more apparent from the following detailed description taken in conjunction with the accompanying drawings: FIG. 1 is a cross-sectional view illustrating a schematic structure of a gas turbine, to which an embodiment of the present disclosure is applied; FIG. 2 is an exploded perspective view illustrating an example of an assembly structure of a disk and a blade, to which an embodiment of the present disclosure is applied; FIG. 3 is a perspective view illustrating a gas turbine according to an embodiment of the present disclosure, and is an enlarged perspective view illustrating an assembled portion of a disk, a blade, and a fixing assembly; FIG. 4 is a perspective view illustrating a fixing assembly according to an embodiment of the present disclosure; FIG. 5 is a top view illustrating a disk according to an embodiment of the present disclosure, when viewed from a top; FIG. 6 is a front view illustrating a disk according to an embodiment of the present disclosure, when viewed from a front side; FIG. 7 is a perspective view illustrating a disk according to an embodiment of the present disclosure; FIG. 8 is a top view illustrating a blade according to an embodiment of the present disclosure, when viewed from a top; FIG. 9 is a front view illustrating a blade according to an embodiment of the present disclosure, when viewed from a front side; FIG. 10 is a perspective view illustrating a blade according to an embodiment of the present disclosure; FIG. 11A is a perspective view illustrating a state, in which a blade and a disk are assembled according to an embodiment of the present disclosure; FIG. 11B is a perspective view illustrating a state, in which a block part is assembled in a blade and a disk according to an embodiment of the present disclosure; FIG. 11C is a perspective view illustrating a state, in which a pin part is assembled according to an embodiment of the present disclosure; and FIG. 11D is a perspective view illustrating a caulking operation according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0029] Hereinafter, an embodiment of the present disclosure will be described in detail with reference to the accompanying drawings.

[0030] First of all, embodiments described below are suitable for understanding technical characteristics of a gas turbine according to an embodiment of the present disclosure. However, the present disclosure is applied only to embodiments described below, or technical features of the present disclosure are not limited by the described embodiments. Various modified implementations are possible within the technical scope of the present disclosure.

[0031] FIG. 1 is a cross-sectional view illustrating a schematic structure of a gas turbine, to which an embodiment of the present disclosure is applied, and FIG. 2 is an exploded perspective view illustrating an example of an assembly structure of a disk and a blade, to which an embodiment of the present disclosure is applied.

[0032] FIG. 3 is a perspective view illustrating a gas turbine according to an embodiment of the present disclosure, and is an enlarged perspective view illustrating an assembled portion of a disk, a blade, and a fixing assembly, FIG. 4 is a perspective view illustrating a fixing assembly according to an embodiment of the present disclosure,

[0033] FIG. 5 is a top view illustrating a disk according to an embodiment of the present disclosure, when viewed from a top, FIG. 6 is a front view illustrating a disk according to an embodiment of the present disclosure, when viewed from a front side, FIG. 7 is a perspective view illustrating a disk according to an embodiment of the present disclosure, FIG. 8 is a top view illustrating a blade according to an embodiment of the present disclosure, when viewed from a top, FIG. 9 is a front view illustrating a blade according to an embodiment of the present disclosure, when viewed from a front side, and FIG. 10 is a perspective view illustrating a blade according to an embodiment of the present disclosure.

[0034] FIG. 11A is a perspective view illustrating a state, in which a blade and a disk are assembled according to an embodiment of the present disclosure, FIG. 11B is a perspective view illustrating a state, in which a block part is assembled in a blade and a disk according to an embodiment of the present disclosure, FIG. 11C is a perspective view illustrating a state, in which a pin part is assembled according to an embodiment of the present disclosure, and FIG. 11D is a perspective view illustrating a caulking operation according to an embodiment of the present disclosure.

[0035] Hereinafter, an embodiment of a turbine blade including a dovetail according to the present disclosure will be described in detail with reference to FIGS. 1 and 2.

[0036] Referring to FIG. 1, an example of a gas turbine 100, on which an embodiment of a turbine blade according to the present disclosure, is mounted is illustrated. The gas turbine includes a housing 102, and a diffuser 106, through which combustion gas of the turbine is discharged, is provided on a rear side of the housing 102. Furthermore, a combustor 104 that receives and burns compressed air is disposed on a front side of the diffuser 106.

[0037] When described with respect to a flow direction of air, a compressor section 110 is located on an upstream side of the housing 102, and a turbine section 120 is disposed on a downstream side thereof. Furthermore, a torque tube 130 that serves as a torque transmission member that transmits rotational torque generated in the turbine section 120 to the compressor section 110 is disposed between the compressor section 110 and the turbine section 120.

[0038] The compressor section 110 includes a plurality of compressor rotor disks 140 (for example, fourteen disks), and the respective compressor rotor disks 140 are fastened by tie bolts 150 not to be spaced apart from each other axially.

[0039] Specifically, the respective compressor rotor disks 140 are aligned with each other axially, with the tie bolt 150 passing through a substantial center thereof. Here, facing surfaces of adjacent respective compressor rotor disks 140 are pressed by the tie bolt 150, so that relative rotation thereof is not allowed.

[0040] A plurality of blades 144 are radially coupled to an outer peripheral surface of the compressor rotor disk 140. Each of the blades 144 includes a dovetail part 146 and is fastened to the compressor rotor disk 140.

[0041] A vane (not illustrated) that is disposed to be fixed to the housing is located between the respective rotor disks 140. The vane is fixed not to be rotated, unlike the rotor disks, and serves to align a flow of compressed air that has passed through the blades of the compressor rotor disk and guide the air to the blades of a rotor disk located on a downstream side.

[0042] Fastening types of the dovetail part 146 include a tangential type and an axial type. They may be selected depending on a required structure of a commercial gas turbine, and may have a generally known dovetail or fir-tree shape. In some cases, the blades may be fastened to the rotor disk by using other fastening devices, than the shapes described above, for example, fixtures, such as a key or a bolt.

[0043] The tie bolt 150 is disposed to pass through centers of the plurality of compressor rotor disks 140 and turbine rotor disks 180, with one end fastened in the compressor rotor disk located on a most upstream side, and an opposite end fastened by a fixing nut 190.

[0044] A shape of the tie bolt 150 may have various structures depending on the gas turbine, and is not necessarily limited to the shape illustrated in FIG. 1. That is, as illustrated, a single tie bolt may have a form, in which it passes through a central portion of the rotor disk, a plurality of tie bolts may have a form, in which they are disposed circumferentially, and a combination thereof is also possible.

[0045] Although not illustrated, a vane that serves as a guide blade may be installed at a next position of a diffuser to adjust a flow angle of fluid that enters an inlet of a combustor after increasing a pressure of the fluid to a design flow angle, in the compressor of the gas turbine, and this is referred to as a deswirler.

[0046] In the combustor 104, the introduced compressed air is mixed with fuel and burned to generate high-energy, high-temperature, and high-pressure combustion gas, and in an isobaric combustion process, a combustion gas temperature is increased up to a heat resistance limit that the combustor and turbine components may withstand.

[0047] A plurality of combustors that constitute a combustion system of a gas turbine may be arranged in a casing formed in a cell form, and each of them includes a burner including a fuel ejection nozzle and the like, a combustor liner that forms a combustion chamber, and a transition piece that is a connection part of the combustor and the turbine.

[0048] Specifically, the liner provides a combustion space, in which the fuel ejected by the fuel nozzle is mixed with the compressed air of a compressor and is 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 forms an annular space while surrounding the flame tube. Furthermore, a fuel nozzle is coupled to a front end of the liner, and an ignition plug is coupled to a side wall thereof.

[0049] Meanwhile, a transition piece is connected to a rear end of the liner so that the combustion gas burned by the ignition plug may be sent toward a turbine. An outer wall of the transition piece is cooled by the compressed air supplied from the compressor so that damage due to a high temperature of combustion gas may be prevented.

[0050] For this purpose, the transition piece is provided with cooling holes for injecting air into an interior, and the compressed air cools a body in the interior through the holes and then flows toward the liner.

[0051] The cooling air that has cooled the above-described transition piece flows through an annular space of the liner, and compressed air may be supplied as cooling air to an outer wall of the liner from the outside of a flow sleeve through the cooling holes provided in the flow sleeve and may collide.

[0052] Meanwhile, the high-temperature and high-pressure combustion gas discharged from the combustor is supplied to the above-described turbine section 120. A rotational torque is caused by providing an impact and a repulsive force to the rotary blades of the turbine while the supplied high-temperature and high-pressure combustion gas is expanded, the obtained rotational torque is transmitted to the compressor section via the above-described torque tube, and power that exceeds the power required for driving the compressor is used to drive a generator and the like.

[0053] 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 disks 180 that are similar to the compressor rotor disks of the compressor section. Accordingly, the turbine rotor disks 180 also include a plurality of turbine blades 184 that are disposed radially. The turbine blades 184 may also be coupled to the turbine rotor disks 180 in a dovetail manner or the like. In addition, vanes (not illustrated) that are fixed to the housing are also provided between the blades 184 of the turbine rotor disks 180 to guide a flow direction of the combustion gas that has passed through the blades.

[0054] Referring to FIG. 2, the turbine rotor disk 180 has a substantially disk shape, and a plurality of coupling slots 180a are formed at an outer periphery thereof. The coupling slot 180a is formed to have a curved surface in a fir-tree shape.

[0055] The turbine blade 184 is fastened to the coupling slot 180a. In FIG. 2, the turbine blade 184 has a platform part 184a in a substantially plate shape at a central portion thereof. A side surface of the platform part 184a contacts the platform part 184a of an adjacent turbine blade to maintain a spacing between the blades.

[0056] A blade portion 184c is formed on an upper surface of the platform part 184a. The blade portion 184c is formed to have a blade shape that is optimized according to specifications of the gas turbine, and has a leading edge that is disposed on an upstream side and a trailing edge that is disposed on a downstream side with respect to a flow direction of the combustion gas.

[0057] Here, unlike the blades of the compressor section, the blades of the turbine section directly contact the high-temperature and high-pressure combustion gas. Because a temperature of the combustion gas reaches as high as 1700°C, a cooling means is required. For this purpose, a cooling passage that extracts compressed air from some parts of the compressor section and supply it to the blades in the turbine section is provided.

[0058] The cooling passage may extend from an outside of the housing as an exterior passage, may extend through an interior of the rotor disk as an interior passage, and may also use both the exterior and the interior passages. In FIG. 2, a plurality of film cooling holes 184d are formed on a surface of the blade portion, and the film cooling holes 184d communicate with a cooling passage (not illustrated) formed in an interior of the blade portion 184c to supply cooling air to the surface of the blade portion 184c.

[0059] A root part, that is, a dovetail part 184b, is formed on a bottom surface of the platform part 184a. The dovetail part 184b has a so-called axial-type form, in which it is inserted into the coupling slot 180a of the above-described rotor disk 180 along an axial direction of the rotor disk 180.

[0060] The dovetail part 184b has a substantially fir-tree-shaped curved portion, which is formed to correspond to a shape of the curved portion formed in the coupling slot. Here, a coupling structure of the dovetail part is not necessarily required to have a fir-tree shape, and may be formed to have a dovetail shape.

[0061] Here, a plurality of coupling slots 180a are radially disposed along an outer peripheral surface of the rotor disk. Furthermore, an interior shape of the coupling slot 180a has a shape corresponding to a shape of the dovetail part 184b. Typically, the coupling slot 180a is formed to be larger than the dovetail part 184b, so that a gap is formed between a surface of the dovetail part and a surface of the coupling slot in a coupled state. Such a gap allows the dovetail part to be fastened to the coupling slot more easily. By coupling the dovetail part to the coupling slot, the blades are fixed not to be moved with respect to a radial direction of the rotor disk.

[0062] Furthermore, although not illustrated, a coupling pin for fixing an axial movement of the dovetail part is fastened between the dovetail part and the coupling slot.

[0063] Referring to FIGS. 2 to 11D, a gas turbine 200 according to an embodiment of the present disclosure includes a blade 230, a disk 210, and a fixing assembly 250.

[0064] It relates to an assembly structure of the disk 210 and the blade 230 described in FIGS. 2 to 11D. Here, the disk 210 may be the compressor rotor disk 140 illustrated in FIG. 1, or may be the turbine rotor disk 180 illustrated in FIGS. 1 and 2. Furthermore, the blade may be a compressor blade 144 illustrated in FIG. 1, or may be the turbine blade 184 illustrated in FIGS. 1 and 2. All of them have a common aspect that a rotating blade is fixed to the disk under a centrifugal force by fitting and coupling concave and convex portions of a dovetail or fir-tree shape.

[0065] Hereinafter, the compressor rotor disk 140 and the turbine rotor disk 180 will be collectively referred to as the disk 210. Furthermore, the compressor blade 144 and the turbine blade 184 will also be collectively referred to as the blade 230.

[0066] In the blade 230, a root part 235 is formed, and a block assembly groove 237 is formed. Furthermore, in the disk 210, a disk slot 213, into which the root part 235 is inserted, is formed, a block insertion groove 215 is formed, and a pin insertion hole 216 is formed.

[0067] Specifically, the disk 210 is formed in a disk shape, and a plurality of disk slots 213 may be formed along a circumferential direction at an outer periphery thereof. A curved surface may be formed in the disk slot 213. Here, the disk slot 213 has a shape that is different from the above-described coupling slot 180a (see FIG. 2), but performs the same function.

[0068] In the disk 210, a block insertion groove 215 may be formed, and the block insertion groove 215 may be formed, to be concave and have a shape that is opened to an outer side in a circumferential direction. A pin insertion hole 216 may be formed to communicate with the block insertion groove 215.

[0069] The blade 230 may be radially disposed at a periphery of the disk 210, and may be coupled in a dovetail shape. Specifically, the root part 235 of the blade 230 may be inserted into the disk slot 213 of the disk 210. The root part 235 may have a curved surface that is engaged with a curved surface of the disk slot 213, and the root part 235 may have an axial type shape that is inserted into the disk slot 213 along an axial direction. Here, the root part 235 has a shape that is different from that of the above-described dovetail part 184b (see FIG. 2), but may perform the same function.

[0070] In the blade 230, a block assembly groove 237 may be formed, and the block assembly groove 237 may be formed to be concave.

[0071] The fixing assembly 250 is provided to fix an axial position and a radial position of the blade 230 with respect to the disk 210.

[0072] Specifically, the fixing assembly 250 is for preventing the blade 230 axially coupled to the disk 210 from being separated during an operation of the gas turbine 200, and serves to fix the blade 230 to the disk 210.

[0073] More specifically, the fixing assembly 250 includes a block part 251 and a pin part 255.

[0074] The block part 251 is inserted into the block assembly groove 237 and the block insertion groove 215. Furthermore, the pin part 255 passes through the pin insertion hole 216 to be coupled to the block part 251.

[0075] The block part 251 is assembled between the blade 230 and the disk 210 to prevent an axial separation of the blade 230. Because the pin part 255 is assembled between the block part 251 and the disk 210 to prevent a circumferential separation of the block part 251, it indirectly prevents separation of the blade 230 as a result. In this way, the fixing assembly 250 may fix the blade 230 to the disk 210 by applying a simple coupling structure of the block part 251 and the pin part 255.

[0076] For example, the block part 251 and the pin part 255 may be screw-coupled to each other.

[0077] After the block part 251 is inserted into the block assembly groove 237 and the block insertion groove 215, the pin part 255 may pass through the pin insertion hole 216 to be assembled with the block part 251. For example, a screw thread may be formed on an outer surface of an end of the pin part 255, and a screw groove, to which the end of the pin part 255 is screw-coupled, may be formed in the block part 251. With this structure, the block part 251 and the pin part 255 may be screw-coupled to each other.

[0078] However, the screw coupling structure of the block part 251 and the pin part 255 is not limited to the above description, and it may be modified in various structures as long as the pin part 255 may be screw-coupled to the block part 251. Furthermore, the coupling of the block part 251 and the pin part 255 is not limited to a screw-coupling structure.

[0079] Meanwhile, the disk 210 may further include a disk body 211, in which the disk slot 213 is formed. Furthermore, the block insertion groove 215 may be formed in the disk body 211, may be formed to be concave such that the block part 251 is inserted thereinto, and may extend in the circumferential direction.

[0080] The disk body 211 is a body that constitutes the disk 210, and the block insertion groove 215 may be concavely formed in the disk body 211. The block insertion groove 215 may be formed to correspond to a shape of the block part 251 such that a portion of the block part 251 is inserted thereinto, and may extend in the circumferential direction.

[0081] The block insertion groove 215 may be formed to be opened in a direction that faces a radially outer side and the blade 230.

[0082] Because the block insertion groove 215 is opened to a radially outer side, the block part 251 may be easily inserted into the block insertion groove 215. Because the block insertion groove 215 is inserted in a direction that faces the blade 230, that is, in a circumferential direction, it may communicate with the block assembly groove 237.

[0083] The pin insertion hole 216 may be formed in the disk body 211 to communicate an inside and an outside of the block insertion groove 215, and may extend in an axial direction.

[0084] Specifically, the pin insertion hole 216 may be formed in the disk body 211 by being bored, and may be formed to extend in the axial direction. The pin insertion hole 216 may be formed to allow the block insertion groove 215 and an outside of the disk body 211 to communicate with each other while communicating with the block insertion groove 215. Accordingly, when the pin part 255 is inserted into the pin insertion groove, one axial end of the pin part 255 may be coupled to the block part 251, and an opposite axial end of the pin part 255 may be exposed to an outside of the disk 210.

[0085] Meanwhile, the blade 230 may further include a blade body 231, and a platform part 233 that is formed between the blade body 231 and the root part 235.

[0086] Specifically, the platform part 233 may be formed at a radial center of the blade 230, the blade body 231 may be provided at a radially outer side of the platform part 233, and the root part 235 may be formed at an axially inner side of the platform part 233.

[0087] For example, the platform part 233 may be inserted into the disk 210, as illustrated in FIG. 3, or may be disposed outside the disk 210, as illustrated in FIG. 2, so that side surfaces of the platform parts 233 of adjacent blades 230 contact each other to maintain a gap between the blades 230.

[0088] The block assembly groove 237 may be concavely formed in the platform part 233 such that the block part 251 is inserted thereinto, and may be formed to be opened in a direction that faces a radially outer side and the block insertion groove 215.

[0089] Specifically, the block assembly groove 237 may be concavely formed in the platform part 233, and may be formed to be opened to a radially outer side. Accordingly, the block part may be easily inserted into the block assembly groove 237. Furthermore, because the block assembly groove 237 is formed to be opened in a direction that faces the block insertion groove 215, it may communicate with the block insertion groove 215.

[0090] When the blade 230 and the disk 210 are assembled, the block assembly groove 237 and the block insertion groove 215 may together form a fixing block groove. Furthermore, the fixing block groove may be formed in a shape corresponding to the block part 251 such that the block part 251 is inserted thereinto.

[0091] Specifically, the fixing block groove refers to a groove that is formed together by the block assembly groove 237 and the block insertion groove 215 when the disk 210 and the blade 230 are coupled to each other. That is, the fixing block groove is a groove that is formed in an assembled state of the disk 210 and the blade 230. A portion of the block part 251 is inserted into the block assembly groove 237, and the remaining portion thereof may be inserted into the block insertion groove 215. In this case, the fixing block groove may extend in a circumferential direction. Accordingly, when the block part 251 is inserted into the fixing block groove, the block part 251 may prevent the blade 230 from being axially separated from the disk 210.

[0092] The fixing block groove may be formed in a shape corresponding to the block part 251. As an example, the block part 251 may be formed in a rectangular parallelepiped shape as illustrated in the embodiment, and the fixing block groove may be formed in a shape corresponding thereto.

[0093] That is, the fixing block groove may be divided into the block assembly groove 237 located on one side and the block insertion groove 215 located on an opposite side with respect to a circumferential direction, and an opening that is opened toward a radially outer side may be formed.

[0094] A portion of the block part 251 may be inserted into the block assembly groove 237, and a remaining portion of the block part 251 may be inserted into the block insertion groove 215.

[0095] As a result, the block part 251 may be assembled in the disk 210 and the blade 230 at the same time. Accordingly, the fixing assembly 250 may prevent the blade 230 from being separated from the disk 210.

[0096] When the blade 230, the disk 210, and the fixing assembly 250 are assembled, the pin part 255 may be assembled to be exposed to an outside of the pin insertion hole 216, and the block part 251 may be assembled to be exposed to an outside of the fixing block groove.

[0097] Specifically, one end of the pin part 255 in an extension direction may be screw-coupled to the block part 251, and an opposite end thereof may pass through the pin insertion hole 216 to be exposed to an outside. The fixing block groove may be opened to a radially outer side, and the block part 251 may be inserted through an opened portion of the fixing block groove to be exposed to an outside after assembly.

[0098] Accordingly, an operator may visually identify a state, in which the block part 251 and the pin part 255 are assembled in the blade 230 and the disk 210. Furthermore, even after all components of the gas turbine 200 are completely assembled, an assembly state of the fixing assembly 250 may be identified through a bore-scope inspection. Here, the bore-scope inspection refers to an inspection of observing an image by inserting an optical device, in which a lighting and a lens are assembled, into a specific part, such as an engine.

[0099] Hereinafter, a process of assembling the disk 210, the blade 230, and the fixing assembly 250 will be described with reference to FIGS. 11A to 11D.

[0100] First, referring to FIG. 11A, the root part 235 of the blade 230 may be inserted into the disk slot 213 of the disk 210 in a direction D1 that is parallel to an axial direction.

[0101] Furthermore, as an example illustrated in FIG. 11B, the block part 251 of the fixing assembly 250 may be inserted into the block assembly groove 237 and the block insertion groove 215 together. In this case, the block part 251 may extend in a circumferential direction, and the block assembly groove 237 and the block insertion groove 215 may be formed to face each other in the circumferential direction. The block part 251 may be inserted into the block assembly groove 237 and the block insertion groove 215 in a direction D31 that faces an axis.

[0102] Next, referring to FIG. 11C, the pin part 255 may pass through the pin insertion hole 216, and the pin part 255 may be screw-coupled to the block part 251. In this case, the pin part 255 may be inserted in a direction D1 that is parallel to an axis.

[0103] Thereafter, additionally, as in an example illustrated in FIG. 11D, an operation of minimizing a gap between the pin part 255 and the disk 210 may be performed through a caulking operation. Here, the caulking operation refers to an operation of eliminating a gap by chiseling a joint by using a blunt-ended chisel 260 to maintain airtightness during riveting in a pressure vessel. In an embodiment of the present disclosure, an operation of eliminating gaps between the fixing assembly 250, the disk 210, and the blade 230 may be performed by using the chisel 260.

[0104] According to an embodiment of the present disclosure, the fixing assembly may prevent the blade from being separated from the disk in an axial direction and a circumferential direction under any operating condition of the gas turbine.

[0105] According to an embodiment of the present disclosure, an operator may visually identify a state, in which the fixing assembly is assembled in the blade and the disk.

[0106] Furthermore, according to an embodiment of the present disclosure, because there is no bent portion in the fixed assembly component, it is easy to manage the component and the component may be reused.

[0107] Furthermore, according to an embodiment of the present disclosure, when the blade is replaced, only the fixed assembly that fixes the blade may be disassembled and reassembled, so that a blade replacement operation may be facilitated.

[0108] Furthermore, by using the fixed assembly according to an embodiment of the present disclosure, the blade and the disk may be manufactured and assembled with a simple structure, so that workability may be improved and costs may be reduced.

[0109] As described above, although specific embodiments of the present disclosure have been described above, the spirit and scope of the present disclosure is not limited to these specific examples. Various modifications and variations are possible within the scope that does not change the gist of the present disclosure described in claims by those skilled in the art to which the present disclosure belongs.

Claims

1. A gas turbine comprising: a blade, in which a root part is formed and a block assembly groove is formed; a disk, in which a disk slot, into which the root part is inserted, is formed, a block insertion groove is formed, and a pin insertion hole is formed; and a fixing assembly configured to fix an axial position and a radial position of the blade with respect to the disk, wherein the fixing assembly includes: a block part inserted into the block assembly groove and the block insertion groove; and a pin part passing through the pin insertion hole to be coupled to the block part.

2. The gas turbine of claim 1, wherein the disk includes: a disk body, in which the disk slot is formed, and wherein the block insertion groove is formed in the disk body, is concavely formed such that the block part is inserted thereinto, and extends in a circumferential direction.

3. The gas turbine of claim 2, wherein the block insertion groove is formed to be opened in a radially outward direction and a direction facing the blade.

4. The gas turbine of claim 2, wherein the pin insertion hole is formed in the disk body to communicate an interior and an exterior of the block insertion groove and is formed to extend in an axial direction.

5. The gas turbine of claim 2, wherein the blade includes: a blade body; and a platform part formed between the blade body and the root part.

6. The gas turbine of claim 5, wherein the block assembly groove is concavely formed in the platform part such that the block part is inserted thereinto, and is formed to be opened in a radially outward direction and a direction facing the block insertion groove.

7. The gas turbine of claim 6, wherein when the blade and the disk are assembled, the block assembly groove and the block insertion groove together form a fixing block groove, and the fixing block groove is formed in a shape corresponding to the block part such that the block part is inserted thereinto.

8. The gas turbine of claim 7, wherein the fixing block groove is divided into the block assembly groove located on one side and the block insertion groove located on an opposite side with respect to the circumferential direction, and an opening opened toward a radially outer side is formed, and wherein a portion of the block part is inserted into the block assembly groove, and the remaining portion of the block part is inserted into the block insertion groove.

9. The gas turbine of claim 7, wherein when the blade, the disk, and the fixing assembly are assembled, the pin part is assembled to be exposed to an exterior of the pin insertion hole, and the block part is assembled to be exposed to an exterior of the fixing block groove.

10. The gas turbine of claim 1, wherein the block part and the pin part are screw-coupled to each other.

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