Gas seal assembly structure of a turbine blade and a gas turbine

Abstract

The present invention relates to a turbine blade air seal assembly structure and a gas turbine. In particular, the turbine blade air seal assembly structure includes: a turbine blade including a blade portion, a platform portion, and a blade root portion; a turbine rotor disk on which the blade root portion of the turbine blade is mounted; an air seal plate mounted between the platform portion and one side portion of the turbine rotor disk to seal a cooling flow path formed inside the blade root portion and the platform portion; and a pin inserted through the turbine rotor disk to support the air seal plate and fix the air seal plate to the turbine rotor disk. The turbine rotor disk has a mounting groove into which a radial direction inner end portion of the air seal plate is inserted, and the air seal plate is provided with a shoulder portion supported by a step portion of the mounting groove in the radial direction.

Description

Technical Field

[0001] This invention discloses a gas seal assembly structure for a turbine blade and a gas turbine incorporating the same. Background Technology

[0002] A turbine is a mechanical device that uses the flow of compressible fluids such as steam or gas to obtain rotational force through impact or reaction force. It mainly includes steam turbines that use steam and gas turbines that use high-temperature gas.

[0003] A gas turbine mainly includes a compressor, a combustion chamber, and a turbine. The compressor is equipped with an air inlet for introducing air, and multiple compressor stationary blades and compressor blades are arranged in a cross pattern inside the compressor casing.

[0004] The combustion chamber supplies fuel to the compressed air compressed by the compressor and ignites it using a combustion device to generate high-temperature, high-pressure gas.

[0005] The turbine has multiple turbine blades and turbine blades arranged in a crisscross pattern within its casing. Furthermore, a rotor is positioned at the center of the compressor, combustion chamber, turbine, and exhaust chamber.

[0006] The rotor is supported by bearings at both ends and can rotate. Furthermore, multiple discs are fixed on the rotor to connect the individual blades, and a drive shaft for a generator or the like is also connected to the end on the exhaust chamber side.

[0007] Because this gas turbine lacks a reciprocating motion mechanism such as a piston in a four-stroke internal combustion engine, it does not have mutual friction parts such as piston-cylinder, and therefore consumes very little lubricating oil. This significantly reduces the amplitude of one of the characteristics of reciprocating motion, thus enabling high-speed motion.

[0008] The following is a brief explanation of the operation of a gas turbine. The compressed air and fuel are mixed and burned to produce high-temperature gas, which is then injected into the turbine side. As the injected gas passes through the turbine blades and turbine vanes, it generates rotational force, thereby driving the rotor to rotate.

[0009] The cooling airflow path that supplies cooling air from the turbine rotor disk to the turbine blades can be formed inside the blade root. In order to form and seal the cooling airflow path, air seal plates can be tightly attached to the blade root and the two axial sides of the rotor disk.

[0010] Existing technology uses bolts and other components to fasten the air seal plate to the root of the turbine blade. However, the bolt head protrudes from the air seal plate, and friction between it and the gas during high-speed rotation can lead to windage loss. Moreover, the weight of the bolt generates a significant centrifugal force after assembly at the blade root, which may contribute to increased stress at the blade root.

[0011] Existing technical documents

[0012] Patent documents

[0013] Patent Publication No. 10-2020-0020415 Summary of the Invention

[0014] Technical issues

[0015] The purpose of this invention is to provide a gas seal assembly structure for a turbine blade and a gas turbine including it. The lower end of the gas seal plate is fixed to the turbine rotor disk. The part of the fixing member protruding from the gas seal plate and the rotor disk is removed to reduce wind resistance loss caused by gas friction. The load applied to the blade root is greatly reduced, thereby improving the structural stability of the blade. The stress concentration between the turbine rotor disk and the gas seal plate can be greatly reduced, and it can be easily assembled.

[0016] Technical solutions to solve technical problems

[0017] An embodiment of the present invention, which achieves the aforementioned objective, includes a turbine blade gas seal assembly structure comprising: a turbine blade, including an airfoil portion, a plateau portion, and an air root portion; a turbine rotor disk on which the air root portion of the turbine blade is mounted; a gas seal plate installed between the plateau portion and a side portion of the turbine rotor disk to seal cooling flow paths formed inside the air root portion and the plateau portion; and a pin inserted through the turbine rotor disk to support the gas seal plate and fix it to the turbine rotor disk; the turbine rotor disk has a mounting groove into which the inner end of the gas seal plate is inserted in the radial direction, and the gas seal plate has a shoulder portion supported by the step portion of the mounting groove in the radial direction.

[0018] The turbine rotor disk may include: a mounting rib extending radially on one side in the axial direction to form a mounting groove between it and the turbine rotor disk; and a through hole formed through the mounting rib to allow a pin to be inserted.

[0019] The air seal plate may include a pin groove formed at the radially inner end of the through hole corresponding to the mounting rib.

[0020] The pin groove can be formed in a semi-circular shape.

[0021] The air seal plate can form an inclined surface by gradually decreasing in thickness towards the inner end of the shoulder in the radial direction.

[0022] The air seal plate may also include: an arc groove formed at the inner corner between the shoulder and the body plate to prevent stress concentration; and a chamfer formed at the other corner of the shoulder.

[0023] The turbine rotor disk may also include: an arcuate groove formed at a recessed corner of the mounting groove step; and a chamfered corner formed at a protruding corner of the mounting groove step.

[0024] In the turbine blade gas seal assembly structure of other embodiments of the present invention, the pin may include: a body portion having a cylindrical shape; and a head portion integrally formed on one side of the body portion in such a way that it has an outer diameter larger than that of the body portion.

[0025] In another embodiment of the present invention, the turbine blade gas seal assembly structure may further include a retainer, which, together with the pin, is inserted into the through hole of the mounting rib to fix the pin in order to prevent it from falling off.

[0026] The air seal plate may also include: an arc groove formed at the inner corner between the shoulder and the body plate to prevent stress concentration; and a chamfer formed at the other corner of the shoulder.

[0027] The turbine rotor disk may also include: an arcuate groove formed at a recessed corner of the mounting groove step; and a chamfered corner formed at a protruding corner of the mounting groove step.

[0028] The pin may include: a body portion having a cylindrical shape; a head portion integrally formed on one side of the body portion having an outer diameter larger than that of the body portion; and a cutting portion formed on the lower part of the body portion and the head portion to allow the retainer to fit snugly.

[0029] The pin may also include a groove that continues from the cut portion and is formed at the head in a stepped manner to allow the retainer to fit snugly.

[0030] The through hole of the turbine rotor disk can be provided on one side with a head receiving hole formed with an inner diameter larger than the through hole to receive the head of the pin.

[0031] The fastener is formed by bending a rectangular sheet and may include: a horizontal part, which is plastically deformed and bent; a step part, which is connected in a step manner at the horizontal part; and a vertical part, which is bent vertically at the step part.

[0032] The retainer is inserted into the through hole of the mounting rib. After the pin is inserted, the head of the pin can be supported by the folded part formed by bending a part of the horizontal part.

[0033] The bent part can be placed inside the head receiving hole after being bent.

[0034] An embodiment of the gas turbine of the present invention includes: a compressor for drawing in and compressing external air; a combustion chamber for mixing fuel with the air compressed by the compressor and for combustion; and a turbine for rotating by means of the gas discharged from the combustion chamber; the turbine includes: turbine blades comprising an airfoil portion, a plateau portion, and a blade root portion; a turbine rotor disk on which the blade root portions of the turbine blades are mounted; an air seal plate installed between the plateau portion and a side portion of the turbine rotor disk to seal cooling flow paths formed inside the blade root portion and the plateau portion; and a pin inserted through the turbine rotor disk to support the air seal plate and fix it to the turbine rotor disk; the turbine rotor disk has a mounting groove for inserting the inner end of the air seal plate in the radial direction, and the air seal plate has a shoulder portion supported by a step portion of the mounting groove in the radial direction.

[0035] The turbine rotor disk includes: a mounting rib extending radially on one side in the axial direction to form a mounting groove between it and the turbine rotor disk; a through hole formed through the mounting rib and allowing a pin to be inserted; and an air seal plate including a pin groove formed at the radially inner end of the through hole corresponding to the mounting rib.

[0036] The air seal plate may also include: an arc-shaped groove formed at the inner corner between the shoulder and the body plate to prevent stress concentration; and a chamfer formed at the other corner of the shoulder. The turbine rotor disc may also include: an arc-shaped groove formed at the recessed corner of the mounting groove step; and a chamfer formed at the protruding corner of the mounting groove step.

[0037] Beneficial effects

[0038] According to the aforementioned turbine blade gas seal assembly structure and gas turbine including it, the lower end of the gas seal plate is fixed to the turbine rotor disk, the part of the fixing member protruding from the gas seal plate and the rotor disk is removed to reduce wind resistance loss caused by gas friction, the load applied to the blade root is greatly reduced to improve the structural stability of the blade, the stress concentration between the turbine rotor disk and the gas seal plate is greatly reduced, and it can be easily assembled. Attached Figure Description

[0039] Figure 1 This is a partial sectional perspective view of a gas turbine according to an embodiment of the present invention.

[0040] Figure 2 This is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.

[0041] Figure 3 It is shown Figure 2 An exploded perspective view of the turbine rotor disk.

[0042] Figure 4 This is a partial cross-sectional perspective view showing the gas seal assembly structure of a turbine blade according to an embodiment of the present invention.

[0043] Figures 5A to 5C These are partial cross-sectional views illustrating the gas seal assembly structure of the turbine blade according to the first embodiment of the present invention. Figure 5A ), showing a three-dimensional view of the latch ( Figure 5B ) and a perspective view showing the turbine rotor disk ( Figure 5C ).

[0044] Figure 6 It is Figure 5A A magnified partial sectional view of the area around the shoulder of the central axis.

[0045] Figures 7A to 7B These are cross-sectional views illustrating the gas seal assembly structure of the turbine blade according to the second embodiment of the present invention. Figure 7A ) and from Figure 7A A cross-sectional view showing the assembly structure after removing the pins. Figure 7B ).

[0046] Figure 8 This is a cross-sectional view showing the gas seal assembly structure of a turbine blade according to a third embodiment of the present invention.

[0047] Figure 9 It was omitted. Figure 8 A partial sectional view of the pin and retainer in the gas seal assembly structure.

[0048] Figure 10 This is a three-dimensional view showing the latch.

[0049] Figure 11 This is a perspective view showing the fixation device.

[0050] Figures 12 to 14 The process of assembling the air seal plate to the turbine rotor disk using pins and retainers is shown. Detailed Implementation

[0051] This invention can be modified and implemented in various ways. Specific embodiments are illustrated below and described in detail in the description of the invention. However, this is not intended to limit the invention to a specific implementation. All variations, equivalents, and even substitutions included within the scope of the concept and technology of this invention should be interpreted as belonging to this invention.

[0052] The terminology used in this invention is for illustrative purposes only and is not intended to limit the invention. Unless clearly distinguishable in the context of the sentence, singular expressions also include plural expressions. Terms such as "comprising" or "having" in this invention merely specify the presence of features, numbers, steps, actions, constituent elements, parts, or combinations thereof described in the specification, and should not be construed as precluding the presence or additional possibilities of one or more other features, numbers, steps, actions, constituent elements, parts, or combinations thereof.

[0053] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings. In these drawings, the same reference numerals are used as much as possible to indicate the same constituent elements. Furthermore, descriptions of well-known structures or functions that may obscure the spirit of the invention will be omitted. For the same reason, some constituent elements may be exaggerated, schematically illustrated, or omitted in the drawings.

[0054] Figure 1 This is a partial sectional perspective view of a gas turbine according to an embodiment of the present invention. Figure 2 This is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention. Figure 3 It is shown Figure 2 An exploded perspective view of the turbine rotor disk.

[0055] like Figure 1 As shown, a gas turbine 1000 according to one embodiment of the present invention includes a compressor 1100, a combustion chamber 1200, and a turbine 1300. The compressor 1100 has a plurality of blades 1110 arranged radially. The compressor 1100 drives the blades 1110 to rotate, and the rotation of the blades 1110 causes air to be compressed and moved. The size and installation angle of the blades 1110 can vary depending on the installation position. In one embodiment of the present invention, the compressor 1100 is directly or indirectly connected to the turbine 1300, receives a portion of the power generated on the turbine 1300, and can use it for the rotation of the blades 1110.

[0056] The compressed air from the compressor 1100 moves toward the combustion chamber 1200. The combustion chamber 1200 includes a plurality of combustion chambers 1210 arranged in a ring and a fuel nozzle module 1220.

[0057] like Figure 2 As shown, a gas turbine 1000 according to one embodiment of the present invention has a housing 1010, and a diffuser 1400 is provided at the rear of the housing 1010 to discharge the gas that has passed through the turbine. Moreover, a combustion chamber 1200 is arranged at the front of the diffuser 1400 to receive compressed air and burn it.

[0058] Based on the direction of air flow, the compressor section 1100 is located upstream of the casing 1010, while the turbine section 1300 is located downstream. Furthermore, a torque tube unit 1500 is disposed between the compressor section 1100 and the turbine section 1300. This torque tube unit 1500 acts as a torque transmission component, transmitting the rotational torque generated in the turbine section 1300 to the compressor section 1100.

[0059] The compressor section 1100 is provided with a plurality of (e.g., 14) compressor rotor discs 1120, each compressor rotor disc 1120 being fastened in the axial direction without isolation by means of a tie rod 1600.

[0060] Specifically, each compressor rotor disc 1120 is aligned with each other along the axial direction with a tie rod 1600, which forms the axis of rotation, passing through its approximate central portion. Here, adjacent compressor rotor discs 1120 are configured to prevent relative rotation because their opposing surfaces are pressed together by the tie rod 1600.

[0061] The outer circumferential surface of the compressor rotor disk 1120 is radially connected with multiple blades 1110. Each blade 1110 is provided with a dovetail portion 1112 and is fastened to the compressor rotor disk 1120.

[0062] Each rotor disk 1120 is provided with stationary blades (not shown) fixed to the housing. Unlike the rotor disks, the stationary blades are fixed and do not rotate. They guide the flow of compressed air through the blades of the compressor rotor disk to the blades of the downstream rotor disk after regulating the airflow.

[0063] The dovetail portion 1112 can be fastened in either a tangential or axial manner. The method can be selected based on the required structure of the commercial gas turbine, and it can have a well-known dovetail or fir-tree shape. Alternatively, other fastening devices such as keys or bolts can be used to fasten the blades to the rotor disk, depending on the situation.

[0064] The tie rod 1600 is disposed through the center of the plurality of compressor rotor disks 1120 and turbine rotor disk 1320. The tie rod 1600 can be composed of one tie rod or multiple tie rods. One end of the tie rod 1600 is fastened to the compressor rotor disk located at the upstream end, and the other end of the tie rod 1600 is fastened by a fixing nut 1450.

[0065] The form of the tie rod 1600 can be configured in various ways depending on the gas turbine, and therefore is not limited to a specific type. Figure 2 The revealed form can be a single tie rod running through the center of the rotor disk, as shown in the figure, or it can be multiple tie rods arranged on the circumference, or a combination of both.

[0066] Although not illustrated, gas turbine compressors can install stationary blades, which act as guide vanes, at a position downstream of the diffuser to align the flow angle of the fluid entering the combustion chamber after the fluid pressure is increased with the design flow angle. These blades are called deswirlers.

[0067] The combustion chamber 1200 mixes and burns the incoming compressed air and fuel to generate high-energy, high-temperature, and high-pressure gas. Through the isobaric combustion process, the gas temperature is raised to the heat resistance limit that the combustion chamber and turbine components can withstand.

[0068] Multiple combustion chambers constituting the combustion system of a gas turbine can be arranged inside a shell-shaped casing. Each combustion chamber includes a burner equipped with fuel injection nozzles, a combustion chamber flame tube forming the combustion chamber, and a transition section serving as the connection between the combustion chamber and the turbine.

[0069] Specifically, the flame tube provides a combustion space where fuel injected by the fuel nozzle and compressed air from the compressor mix and burn. The flame tube may include: a tube body providing the combustion space for the combustion of the air-fuel mixture; and a flow guide bushing that encloses the tube body to form an annular space. Furthermore, the front end of the flame tube is connected to a fuel nozzle, and the sidewalls are connected to spark plugs.

[0070] On the other hand, the rear end of the flame tube is connected to a transition section to transfer the combustion gases, which are burned by the spark plug, to the turbine side. The outer wall of this transition section is cooled by compressed air from the compressor to prevent damage from the high temperature of the combustion gases.

[0071] For this purpose, the transition section is provided with cooling holes to inject air into the interior. The compressed air cools the body located inside the interior through the holes and then flows towards the flame tube side.

[0072] The cooling air that has cooled the aforementioned transition section flows in the annular space of the flame tube. Outside the guide bushing, compressed air is supplied as cooling air through the cooling holes provided in the guide bushing and can collide with the outer wall of the flame tube.

[0073] On the other hand, the high-temperature, high-pressure gas from the combustion chamber is supplied to the aforementioned turbine 1300. The supplied high-temperature, high-pressure gas expands and collides with the turbine's rotor blades, generating a reaction force that produces a rotational torque. This rotational torque is then transmitted to the compressor via the aforementioned torque tube. Any power exceeding the power required to drive the compressor is used to drive the generator, etc.

[0074] The turbine 1300 is basically similar in structure to a compressor. That is, the turbine 1300 also has multiple turbine rotor disks 1320 similar to those of a compressor rotor disk. Therefore, each turbine rotor disk 1320 also includes multiple turbine blades 1340 arranged radially, and the turbine blades 1340 can be joined to the turbine rotor disk 1320 in a dovetail-like manner. Simultaneously, turbine flat blades 1330 fixed to the housing are also provided between the blades 1340 of the turbine rotor disk 1320 to guide the flow direction of the combustion gas passing through the blades.

[0075] Please see Figure 3 The turbine rotor disk 1320 is roughly in the shape of a disk, and a plurality of mating grooves 1322 are formed on its outer periphery. The mating grooves 1322 are formed with a fir-tree-shaped zigzag surface.

[0076] Turbine blade 1340 is fastened to the mating groove 1322. Figure 3 The turbine blade 1340 may have a plate-shaped platform portion 1341 in approximately the central part. The platform portion 1341 and the platform portion 1341 of the turbine blade function to maintain the spacing between the blades because their sides are in contact with each other.

[0077] The bottom surface of the platform portion 1341 is formed with a blade root portion 1342. The blade root portion 1342 has an axial-type shape that is inserted into the mating groove 1322 of the rotor disk 1320 along the axial direction of the rotor disk 1320.

[0078] The leaf root 1342 has a bend that roughly resembles a fir tree shape, formed in a manner corresponding to the bend formed in the joint groove. Here, the joint structure of the leaf root does not necessarily have to take the shape of a fir tree; it can also be formed in a swallowtail shape.

[0079] The upper surface of the platform portion 1341 is provided with a blade portion 1343. The blade portion 1343 is formed with an airfoil optimized according to the specifications of a gas turbine, and has a leading edge disposed on the upstream side and a trailing edge disposed on the downstream side based on the direction of gas flow.

[0080] Here, unlike the compressor blades, the turbine blades are in direct contact with the high-temperature, high-pressure combustion gas. Since the temperature of the combustion gas reaches as high as 1700°C, cooling is required. Therefore, a cooling flow path is provided to supply compressed air to the turbine blades after it is drawn from a portion of the compressor.

[0081] The cooling flow path can extend outside the housing (external flow path) or extend through the interior of the rotor disk (internal flow path), or both external and internal flow paths can be used. Figure 3 The surface of the blade portion has a plurality of thin film cooling holes 1344, which are connected to a cooling flow path (not shown) formed inside the blade portion 1343 to supply cooling air to the surface of the blade portion 1343.

[0082] On the other hand, the turbine blades 1343 rotate inside the housing using combustion gases, and a gap exists between the tip of the blades 1343 and the inner surface of the housing to allow the blades to rotate smoothly. However, as mentioned earlier, combustion gases can leak through this gap, so a sealing means is required to prevent leakage.

[0083] Both turbine blades and stator blades are airfoil-shaped, consisting of a leading edge, trailing edge, suction surface, and pressure surface. The interior of both stator blades and turbine blades contains a complex labyrinthine structure that forms the cooling system. The cooling circuit within the stator blade and the blade itself receives cooling fluid (e.g., air) from the turbine engine's compressor, allowing the fluid to pass through the ends of the stator blade and the blade itself, which are attached to the stator blade and blade holder. The cooling circuit typically includes multiple flow paths designed to maintain a relatively uniform temperature across all surfaces of the turbine blade and the blade itself. At least a portion of the fluid passing through these cooling circuits is discharged through openings in the leading edge, trailing edge, suction surface, and pressure surface of the stator blade.

[0084] Figure 4 This is a partial cross-sectional perspective view showing the gas seal assembly structure of a turbine blade according to an embodiment of the present invention. Figures 5A to 5C These are partial cross-sectional views illustrating the gas seal assembly structure of the turbine blade according to the first embodiment of the present invention. Figure 5A ), showing a three-dimensional view of the latch ( Figure 5B ) and a perspective view showing the turbine rotor disk ( Figure 5C ), Figure 6 It is Figure 5C A magnified partial sectional view of the area around the shoulder of the central axis.

[0085] An embodiment of the turbine blade gas seal assembly structure of the present invention includes: a turbine blade 100, comprising an airfoil portion 110, a platform portion 120, and an air root portion 130; a turbine rotor disk 200, on which the air root portion of the turbine blade is mounted; an air seal plate 300, installed between the platform portion and one side portion of the turbine rotor disk, sealing the cooling flow path 150 formed inside the air root portion and the platform portion; and a pin 400, inserted through the turbine rotor disk to support the air seal plate and fix it to the turbine rotor disk.

[0086] like Figure 3 and Figure 4As shown, the blade portion 110 of the turbine blade 100 is composed of a leading edge, a trailing edge, a convex suction surface on one side, and a concave pressure surface on the other side, as previously described.

[0087] A platform portion 120, roughly in the shape of a flat plate, can be integrally formed inside the blade portion 110 in the radial direction. The circumferential width of the platform portion 120 can be greater than the thickness of the blade portion 110.

[0088] The leaf base 130 can extend radially inward towards the platform portion 120 and be integrally formed. The leaf base 130 can be formed with a roughly fir-tree-like zigzag surface. Figure 3 As shown, the leaf roots 130 and 1342 can be inserted into the mating groove 1322 of the turbine rotor discs 1320 and 200, which have a corresponding zigzag surface in the shape of a fir tree, for installation.

[0089] The turbine rotor disk 200 is generally circular in shape, with a through hole in the center for the tie rod 1600 to pass through, and multiple engagement slots 1322 arranged at certain intervals on its outer circumference. The blade root 130 of the turbine blade 100 can be inserted into each engagement slot 1322 for installation.

[0090] exist Figure 4 In one embodiment, the blade root 130 of the turbine blade 100 can be inserted into the mating groove of the turbine rotor disk 200 in the circumferential direction for installation. That is, Figure 3 The turbine blades are mounted to the turbine rotor disk in an axial flow configuration, but Figure 4 The turbine blades can be tangentially mounted to the turbine rotor disc.

[0091] A cooling flow path 150 for supplying cooling air to the turbine blade 100 can be formed inside the blade root 130 and the platform section 120. An air seal plate 300 is installed between the platform section 120 and one side of the turbine rotor disk 200 and can seal the cooling flow path 150.

[0092] like Figures 5A to 5C As shown, the pin 400 is inserted into the through hole formed in the turbine rotor disk 200 and supports the air seal plate 300 in the radial direction to fix it to the turbine rotor disk 200.

[0093] The turbine rotor disk 200 may be provided with a mounting groove 250 into which the inner radial end of the gas seal plate 300 is inserted. It may include a mounting rib 210, which extends radially on one axial side of the turbine rotor disk 200 and forms the mounting groove 250 between itself and the turbine rotor disk 200. Figure 5A As shown, the cross-section of the mounting groove 250 can be roughly rectangular.

[0094] like Figure 5AAs shown, a through hole 220 for inserting a pin 400 is formed through the mounting rib 210 in the axial direction. The through hole 220 can be a circular hole formed in the thickness direction of the mounting rib 210.

[0095] like Figure 5B As shown, the pin 400 can be formed in a cylindrical shape, and a chamfered part can be formed at one end of the corner.

[0096] like Figure 5C As shown, the air seal plate 300 may include a pin groove 350 formed at the radially inner end of the through hole 220 corresponding to the mounting rib 210. The pin groove 350 may be formed in a semi-circular shape at the center of the width direction at the radially inner end of the air seal plate 300. Therefore, approximately half the thickness of the pin 400 is inserted into the pin groove 350 to support the air seal plate 300.

[0097] The air seal plate 300 can form an inclined surface 330 by gradually decreasing in thickness towards the inner end of the shoulder 320 in the radial direction. Figure 5C Based on this, the thickness of the lower end of the inclined surface 330 can be made smaller than the thickness of the body plate 310 above the shoulder portion 320 of the air seal plate 300. The inclined surface 330 can be connected to the lower end of a vertical surface with a preset height instead of starting immediately at the shoulder portion 320. According to the structure of this air seal plate 300, when the lower part of the air seal plate 300 is inclined and inserted into the mounting groove 250, it can be easily inserted without interference.

[0098] like Figure 5C and Figure 6 As shown, the air seal plate 300 may also include an arc-shaped groove 321 formed at the inner corner between the shoulder portion 320 and the body plate 310 to prevent stress concentration, and a chamfered portion 323 formed at the other corner of the shoulder portion 320.

[0099] The arc-shaped groove 321 can be formed in the inner corner between the upper surface of the shoulder 320 and the side surface of the body plate 310 with a groove shape having a preset radius of curvature. That is, by forming the arc-shaped groove 321 at the inner corner where the two planes meet perpendicularly, stress concentration at that part can be prevented.

[0100] The chamfer 323 is formed at an angle of 40 to 50 degrees at the outer corner where the shoulder 320 meets the inclined surface 330. This chamfer 323 can prevent stress concentration at its corner and also reduce the possibility of damage to the air seal plate 300 from collision with other parts when assembling or disassembling it.

[0101] like Figure 6 As shown, the turbine rotor disk 200 may also include an arcuate groove 261 formed in the recessed corner of the mounting groove 250 step portion 260 and a chamfered portion 263 formed in the protruding corner of the mounting groove step portion 260.

[0102] by Figure 6 Based on this, the arc-shaped groove 261 is formed in the mounting groove 250 of the turbine rotor disk 200 at the inner corner where the vertical plane meets the horizontal plane of the step portion 260, with a preset radius of curvature. That is, by forming the arc-shaped groove 261 at the inner corner where the two planes meet perpendicularly, stress concentration at that location can be prevented. Furthermore, the chamfered portion 323 of the air seal plate 300 is located in front of the arc-shaped groove 261, and interference is minimized when the air seal plate 300 is tilted and inserted into the mounting groove 250 by means of the arc-shaped groove 261.

[0103] The chamfer 263 can be formed at an angle of 40 to 50 degrees at the protruding corner of the mounting groove step 260. With this chamfer 263, stress concentration at this part can be prevented, and since the arc groove 321 of the air seal plate 300 is located in front of the chamfer 263, mutual interference can be minimized during assembly and disassembly.

[0104] Figures 7A to 7B These are cross-sectional views illustrating the gas seal assembly structure of the turbine blade according to the second embodiment of the present invention. Figure 7A ) and from Figure 7A The cross-sectional view shown after removing the pins from the assembled structure ( Figure 7B ).

[0105] like Figure 7A As shown, in the turbine blade gas seal assembly structure of the second embodiment of the present invention, the pin 400 includes a body portion 410 having a cylindrical shape and a head 420 integrally formed on one side of the body portion in such a way that it has an outer diameter larger than that of the body portion.

[0106] That is, compared to the first embodiment, in the gas seal assembly structure of the second embodiment, the pin 400 includes not only a cylindrical body portion 410, but also a head 420. The head 420 can be formed in a cylindrical shape with an outer diameter larger than that of the body portion 410.

[0107] like Figure 7B As shown, the through hole 220 into which the pin 400 is inserted can also be further formed with a head receiving hole 230 corresponding to the shape of the pin 400, which receives the head 420. The inner diameter of the head receiving hole 230 can be formed slightly larger than the outer diameter of the head 420 of the pin 400. Moreover, the length of the head receiving hole 230 in the longitudinal direction can be formed slightly larger than the length of the head 420 of the pin 400 to prevent the pin 400 from protruding outside the through hole 220 of the mounting rib 210. Furthermore, the inner side of the head receiving hole 230 in the longitudinal direction is formed with a step, so that the insertion length is limited when the pin 400 is inserted, and the pin 400 can be installed in the correct position.

[0108] Figure 8 This is a cross-sectional view showing the gas seal assembly structure of a turbine blade according to a third embodiment of the present invention. Figure 9 It was omitted. Figure 8 A partial sectional view of the pin and retainer in the gas seal assembly structure. Figure 10 This is a three-dimensional view showing the latch. Figure 11 This is a perspective view showing the fixation device.

[0109] Compared to the second embodiment, the turbine blade gas seal assembly structure of the third embodiment also includes a retainer 500, which, together with the pin 400, is inserted into the through hole 220 of the mounting rib 210 to fix the pin 400 and prevent it from falling off.

[0110] As in the aforementioned embodiments, the turbine rotor disk 200 may include mounting ribs 210, through holes 220, and mounting grooves 250. Furthermore, the shape of the air seal plate 300 can also be the same as in the aforementioned embodiments.

[0111] like Figure 9 As shown, the air seal plate 300 may include a pin groove 350 formed at the radially inner end of the through hole 220 corresponding to the mounting rib 210.

[0112] Please see Figure 6 As mentioned above, the air seal plate 300 may further include an arcuate groove 321 formed at the inner corner between the shoulder portion 320 and the body plate 310 to prevent stress concentration, and a chamfered portion 323 formed at the other corner of the shoulder portion 320. The turbine rotor disk 200 may further include an arcuate groove 261 formed at the concave corner of the mounting groove 250 step portion 260 and a chamfered portion 263 formed at the convex corner of the mounting groove step portion 260.

[0113] The pin 400 is inserted into the through hole 220 formed in the turbine rotor disk 200 and supports the air seal plate 300, thereby fixing the air seal plate 300 to the turbine rotor disk 200.

[0114] The pin 400 is simply inserted into the through hole 220 of the mounting rib 210 formed in the turbine rotor disk 200, and the retainer 500 is installed in the through hole 220 of the turbine rotor disk 200 so that the pin 400 is fixed without detaching.

[0115] like Figure 10 As shown, the pin 400 may include: a body portion 410 having a cylindrical shape; a head 420 integrally formed on one side of the body portion having an outer diameter larger than that of the body portion; and a cutting portion 440 formed on the lower part of the body portion and the head portion and allowing the retainer 500 to fit snugly against it.

[0116] The body part 410 has a cylindrical shape, and the head 420 has a cylindrical shape with an outer diameter larger than that of the body part 410. The body part 410 and the head 420 can be integrally formed with a step difference.

[0117] A cutting portion 440 may be formed on the lower part of the entire body portion 410 and a portion of the head portion 420 to allow the retainer 500 to fit snugly. The cutting surface of the cutting portion 440 is formed in a planar shape, and a step surface perpendicular to the cutting surface may be formed on the lower middle part of the head portion 420. Furthermore, the cutting portion 440 may have a chamfer formed on the end side of the body portion 410.

[0118] The pin 400 may also include a groove 430, which continues from the cut portion 440 and is formed in a stepped manner at the head 420 to allow the retainer 500 to fit snugly. The groove 430 is shallower than the cut portion 440 and can be formed in a stepped manner from the cut portion 440. The cut portion 440 extends in a planar manner to the circumferential surface of the pin 400 in the width direction, but the groove 430 has a width smaller than the outer diameter of the head 420, so that a stepped manner can be formed from the circumferential surface of the head 420 to the bottom of the groove 430.

[0119] Furthermore, the pin 400 may have a screw hole 450 formed along its length on one side of the head 420. The screw hole 450 may not be formed in the center of the head 420, but rather slightly off-center to the opposite side of the slot 430. The length of the screw hole 450 may be greater than the length of the head 420. The screw hole 450 has threads formed on its inner circumferential surface, so when removing the pin 400, the pin 400 can be easily removed from the through hole 220 by engaging the bolt into the screw hole 450 and pulling the bolt.

[0120] like Figure 9 As shown, the through hole 220 of the turbine rotor disk 200 can include a head receiving hole 230 on one side, which is formed with an inner diameter larger than the through hole to receive the head 420 of the pin 400.

[0121] The diameter of the head receiving hole 230 is larger than that of the through hole 220, and it is formed in a stepped manner from the through hole 220 so that the head 420 of the pin 400 can be received in the correct position. The length of the head receiving hole 230 is larger than that of the head 420, so that the bent portion 550, as described later, can be fully received within the head receiving hole 230.

[0122] like Figure 11 As shown, the fastener 500 is formed by bending a rectangular plate and may include: a horizontal portion 510, which can be plastically deformed and bent; a step portion 520, which is connected in a step manner in the horizontal portion; and a vertical portion 530, which is bent vertically in the step portion.

[0123] The fastener 500 can bend a rectangular metal sheet with a preset width, length, and thickness to form the shape. The fastener 500 can be used to form a material structure that can be easily bent by plastic deformation of the entire sheet, or it can be used to form a material structure by simply inserting the fastener 500 into the horizontal part 510 after bending.

[0124] Horizontal section 510 is a slender rectangular plate, such as Figure 11 As shown, the unbent portion of the horizontal part 510 is configured to be inserted into the slot 430 of the pin 400.

[0125] The step section 520 is formed by bending upwards and then bending horizontally again from one end of the horizontal section 510. For example... Figure 8 As shown, the step portion 520 can be installed between the cutting portion 440 of the pin 400 and the through hole 220.

[0126] The vertical portion 530 can be formed by bending downwards from one end of the step portion 520. The vertical portion 530 can be formed with a length that is more than twice the step height of the step portion 520. The vertical portion 530 is close to the inner side of the mounting rib 210 so that the retainer 500 can be fixed to the outside without coming off.

[0127] like Figure 8 As shown, the retainer 500 is inserted into the through hole 220 of the mounting rib 210. After the pin 400 is inserted, the head 420 of the pin 400 can be supported by the folded portion 550 formed by bending a part of the horizontal portion 510.

[0128] At this time, the bent portion 550 is positioned inside the head receiving hole 230 after bending, thus preventing the head 420 of the retainer 500 and the pin 400 from protruding from the outer side of the through hole 220 of the mounting rib 210.

[0129] On the other hand, such as Figure 8 As shown, a screw hole 312 can be formed in the center of one side of the air seal plate 300. The screw hole 312 does not penetrate the air seal plate 300 and is formed with a length approximately equivalent to half the thickness. The inner circumferential surface of the screw hole 312 is threaded. Therefore, when assembling the air seal plate 300, tightening the bolts into the screw hole 312 allows the air seal plate 300 to be easily moved to the correct position.

[0130] Figures 12 to 14 The process of assembling the air seal plate to the turbine rotor disk using pins and retainers is shown.

[0131] The following description, in conjunction with the accompanying drawings, illustrates the gas seal assembly method for turbine blades.

[0132] First, such as Figure 4 As shown, the blade root 130 of the turbine blade 100 is inserted into the slot of the turbine rotor disk 200 for installation.

[0133] Next, as Figure 9 As shown, the air seal plate 300 is installed between the platform portion 120 of the turbine blade 100 and the mounting rib 210 of the turbine rotor disk 200. At this time, the inner end of the air seal plate 300 in the radial direction can be inserted into the mounting groove 250.

[0134] Next, as Figure 12 As shown, the fastener 500 is installed by inserting it into the through hole 220 formed in the mounting rib 210. At this time, the horizontal part 510 of the fastener 500 is not bent, and it can be installed by inserting the step part 520 and the vertical part 530 into the through hole 220.

[0135] Then, as Figure 12 and Figure 13 As shown, the pin 400 is installed by inserting it into the through hole 220 of the mounting rib 210 and the pin groove 350 formed in the air seal plate 300. At this time, the pin 400 can be inserted in such a way that the step portion between the body portion 410 and the head 420 is tightly against the step portion between the through hole and the head receiving hole 230 and is supported. Furthermore, the pin 400 can be installed by inserting it in such a way that the step portion 520 and the horizontal portion 510 of the retainer 500 contact the cutting portion 440 and the groove portion 430 of the pin 400.

[0136] Next, as Figure 13 As shown, the portion of the retainer 500 that protrudes outside the mounting rib 210 is bent to support the pin 400. That is, the bent portion 550 formed by vertically bending the protruding end of the horizontal portion 510 of the retainer 500 is pressed against the head 420 of the pin 400 to support the pin 400.

[0137] like Figure 14 As shown, the bent portion 550, formed by bending a portion of the horizontal portion 510, can be disposed inside the through hole 220 of the turbine rotor disk 200. That is, the pin 400 or the retainer 500 will not protrude from the outer surface of the mounting rib 210, thus preventing flow loss due to protruding parts and gas friction.

[0138] The foregoing has described one embodiment of the present invention. However, those skilled in the art to which this invention pertains may modify and alter the present invention in various ways, such as by adding, altering, deleting, or adding constituent elements, without departing from the spirit of the invention as set forth in the claims. All such modifications and alterations should be interpreted as falling within the scope of the claims of this invention.

[0139] List of reference numerals

[0140] 1000: Gas turbine; 1010: Casing

[0141] 1100: Compressor; 1110: Compressor blades

[0142] 1112: Dovetail section; 1120: Compressor rotor disc

[0143] 1200: Combustion chamber; 1210: Combustion cavity

[0144] 1220: Fuel Nozzle Module

[0145] 1300: Turbine; 1320: Turbine rotor disc

[0146] 1330: Transparent blade 1340: Transparent blade

[0147] 1400: Diffuser 1450: Fixing nut

[0148] 1500: Torque tube unit; 1600: Tie rod

[0149] 100: Turbine blade; 110: Leaf shape.

[0150] 120: Platform Department; 130: Leaf Root Department

[0151] 150: Cooling flow path

[0152] 200: Turbine rotor disc; 210: Mounting ribs

[0153] 220: Through hole; 230: Head receiving hole

[0154] 250: Mounting slot; 260: Step section

[0155] 261: Curved groove; 263: Chamfered section

[0156] 300: Air sealing plate 310: Body plate

[0157] 312: Screw hole

[0158] 320: Shoulder portion of shaft 321: Arc groove

[0159] 323: Chamfered part; 330: Sloping surface

[0160] 350: Pin groove

[0161] 400: Pin 410: Body

[0162] 420: Head 430: Groove

[0163] 440: Cutting section; 450: Screw hole

[0164] 500: Fixture 10: Horizontal section

[0165] 520: step part 530: vertical part

[0166] 550: Bent section

Claims

1. A gas seal assembly structure for a turbine blade, characterized in that, include: A turbine blade consists of a leaf-shaped part, a plateau part, and a leaf base; A turbine rotor disk on which the root of the turbine blades is mounted; An air seal plate, installed between the platform section and one side of the turbine rotor disk, seals the cooling flow path formed at the blade root and inside the platform section; and, A pin is inserted through the turbine rotor disk to support the air seal plate and secure it to the turbine rotor disk; The turbine rotor disc has a mounting groove into which the inner end of the gas seal plate is inserted in the radial direction. The air seal plate is provided with a shoulder portion that is supported by the step portion of the mounting groove in the radial direction. An inclined surface is formed at the shoulder portion, the inclined surface being formed such that its thickness decreases towards the inner end in the radial direction, and the lower end has a thickness smaller than that of the body plate above the shoulder portion. It also includes a chamfered portion, formed on the other side corner of the shoulder portion, and formed at an angle of 40 to 50 degrees on the outer corner of the shoulder portion where it meets the inclined surface.

2. The gas seal assembly structure for the turbine blade according to claim 1, characterized in that, The turbine rotor disk includes: The mounting rib extends radially on one side of the axial direction and forms the mounting groove between it and the turbine rotor disk; A through hole is formed through the mounting rib and allows the pin to be inserted.

3. The gas seal assembly structure for turbine blades according to claim 2, characterized in that... The air seal plate includes a pin groove formed at the radially inner end position of the through hole corresponding to the mounting rib.

4. The gas seal assembly structure for the turbine blade according to claim 3, characterized in that, The pin groove is formed in a semi-circular shape.

5. The gas seal assembly structure for a turbine blade according to claim 2, characterized in that, The air seal plate also includes: An arc-shaped groove is formed at the inner corner between the shoulder and the body plate to prevent stress concentration.

6. The gas seal assembly structure for a turbine blade according to claim 5, characterized in that, The turbine rotor disk includes: An arc-shaped groove is formed at the concave corner of the mounting groove step portion; A chamfered portion is formed at the protruding corner of the mounting groove step portion.

7. The gas seal assembly structure for a turbine blade according to claim 1, characterized in that, The pin includes: The main body has a cylindrical shape; The head is integrally formed on one side of the body portion in a manner that has an outer diameter greater than that of the body portion.

8. The gas seal assembly structure for the turbine blade according to claim 3, characterized in that, It also includes a retainer, which, together with the pin, is inserted into the through hole of the mounting rib to secure the pin and prevent it from falling off.

9. The gas seal assembly structure for a turbine blade according to claim 8, characterized in that, The pin includes: The main body has a cylindrical shape; The head is integrally formed on one side of the body portion in a manner that has an outer diameter greater than that of the body portion; A cutting section is formed at the lower part of the body and the head to allow the retainer to fit snugly.

10. The gas seal assembly structure for a turbine blade according to claim 9, characterized in that, The pin also includes a groove that extends from the cut portion and is formed at the head in a stepped manner to allow the retainer to fit snugly.

11. The gas seal assembly structure for a turbine blade according to claim 10, characterized in that, The turbine rotor disk has a through hole on one side, which is formed with an inner diameter larger than the through hole to receive the head of the pin.

12. The gas seal assembly structure for a turbine blade according to claim 11, characterized in that, The fastener is formed by bending a rectangular sheet of material, and includes: The horizontal section is susceptible to plastic deformation and bending. The step section is connected in a step-like manner to the horizontal section; The vertical section bends vertically at the step difference.

13. The gas seal assembly structure for a turbine blade according to claim 12, characterized in that, The retainer is inserted into the through hole of the mounting rib, and after the pin is inserted, the head of the pin is supported by the folded portion formed by bending a part of the horizontal portion.

14. The gas seal assembly structure for a turbine blade according to claim 13, characterized in that, The folded portion is folded and then disposed inside the head receiving hole.

15. A gas turbine, characterized in that, include: An air compressor compresses outside air after it is drawn in. The combustion chamber, in which the air compressed by the compressor is mixed with fuel and combusted; and, The turbine rotates by the combustion gases emitted from the combustion chamber; The turbine includes: A turbine blade consists of a leaf-shaped part, a plateau part, and a leaf base; A turbine rotor disk on which the root of the turbine blades is mounted; An air seal plate, installed between the platform section and one side of the turbine rotor disk, seals the cooling flow path formed at the blade root and inside the platform section; and, A pin is inserted through the turbine rotor disk to support the air seal plate and secure it to the turbine rotor disk; The turbine rotor disc has a mounting groove into which the inner end of the gas seal plate is inserted in the radial direction. The air seal plate is provided with a shoulder portion that is supported by the step portion of the mounting groove in the radial direction. An inclined surface is formed at the shoulder portion, the inclined surface being formed such that its thickness decreases towards the inner end in the radial direction, and the lower end has a thickness smaller than that of the body plate above the shoulder portion. It also includes a chamfered portion, formed on the other side corner of the shoulder portion, and formed at an angle of 40 to 50 degrees on the outer corner of the shoulder portion where it meets the inclined surface.

16. The gas turbine according to claim 15, characterized in that, The turbine rotor disk includes: a mounting rib extending radially on one side in the axial direction to form the mounting groove between it and the turbine rotor disk; and a through hole formed through the mounting rib to allow the pin to be inserted. The air seal plate includes a pin groove formed at the radially inner end position of the through hole corresponding to the mounting rib.

17. The gas turbine according to claim 16, characterized in that, The air seal plate also includes an arc-shaped groove, which is formed at the inner corner between the shoulder and the body plate to prevent stress concentration. The turbine rotor disk further includes: an arc-shaped groove formed at the concave corner of the mounting groove step portion; and a chamfered portion formed at the convex corner of the mounting groove step portion.

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