KR20240108753A - Turbine blade sealing assembly and gas turbine comprising it - Google Patents

Abstract

A turbine blade sealing assembly capable of sealing a cooling passage for supplying cooling air to a turbine blade and preventing efficiency reduction due to gas friction, and a gas turbine including the same are disclosed.
The disclosed turbine blade sealing assembly,
A sealing member sealing one side of at least two or more platforms formed adjacent to one side of a turbine rotor disk on which a root member formed in the lower portion of each of the two or more platforms is mounted; A fixing pin inserted into one lower side of the turbine rotor disk and fixing the sealing member to the turbine rotor disk; And, a bending member that is inserted together with the fixing pin to prevent the fixing pin from falling out.

Description

Turbine blade sealing assembly and gas turbine comprising the same {Turbine blade sealing assembly and gas turbine comprising it}

The present invention relates to a turbine blade sealing assembly and a gas turbine including the same.

A turbine is a mechanical device that obtains rotational power through impulse or reaction force using the flow of compressible fluid such as steam or gas. There are steam turbines using steam and gas turbines using high-temperature combustion gas.

Among these, the gas turbine largely consists of a compressor, combustor, and turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged within the compressor housing.

The combustor supplies fuel to the compressed air from the compressor and ignites it with a burner, thereby generating high-temperature, high-pressure combustion gas.

The turbine has a plurality of turbine vanes and turbine blades arranged alternately within the turbine casing. Additionally, the rotor is arranged to penetrate the center of the compressor, combustor, turbine, and exhaust chamber.

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

Since these gas turbines do not have a reciprocating mechanism such as the piston of a four-stroke engine, there is no mutual friction such as a piston-cylinder, so the consumption of lubricant is extremely low. The amplitude, which is a characteristic of a reciprocating machine, is greatly reduced, and high-speed movement is possible. There is an advantage.

To briefly explain the operation of a gas turbine, air compressed in a compressor is mixed with fuel and burned to produce high-temperature combustion gas, and the resulting combustion gas is injected toward the turbine. As the injected combustion gas passes through the turbine vanes and turbine blades, it generates rotational force, causing the rotor to rotate.

Republic of Korea Patent Publication No. 10-2010-0064754 (Name: Gas turbine cooling blade)

The purpose of the present invention is to provide a turbine blade sealing assembly that seals a cooling passage for supplying cooling air to a turbine blade and prevents efficiency reduction due to gas friction, and a gas turbine including the same.

The turbine blade sealing assembly according to an embodiment of the present invention,

A sealing member sealing one side of at least two or more platforms formed adjacent to one side of a turbine rotor disk on which a root member formed in the lower portion of each of the two or more platforms is mounted; A fixing pin inserted into one lower side of the turbine rotor disk and fixing the sealing member to the turbine rotor disk; And, a bending member that is inserted together with the fixing pin to prevent the fixing pin from falling out.

In the turbine blade sealing assembly according to an embodiment of the present invention, the turbine rotor disk includes a mounting groove formed on one axial side and into which the radial inner end of the sealing member is inserted, and a mounting rib extending radially on one axial side. may include.

In the turbine blade sealing assembly according to an embodiment of the present invention, the sealing member may include a pin groove formed at a radially inner end position corresponding to a through hole formed in the mounting rib.

In the turbine blade sealing assembly according to an embodiment of the present invention, the pin grooves may be formed in a number corresponding to the number of platforms.

In the turbine blade sealing assembly according to an embodiment of the present invention, the sealing member includes a sealing body, a step portion radially supported by a step formed in the mounting groove, and the thickness increases from the step portion to the radial inner end. It may include an inclined portion that becomes increasingly thinner.

In the turbine blade sealing assembly according to an embodiment of the present invention, the sealing member includes a first arc-shaped groove formed to prevent stress concentration at the inner edge between the step and the sealing body, and a first chamfer formed at the other edge of the step. May include sides.

In the turbine blade sealing assembly according to an embodiment of the present invention, the turbine rotor disk may include a second arc-shaped groove formed on the concave edge of the step formed in the mounting groove and a second chamfered surface formed on the convex edge of the step. .

In the turbine blade sealing assembly according to an embodiment of the present invention, the fixing pin includes a pin body, a pin head formed on one side of the pin body and having a larger outer diameter than the pin body, and a lower part of the pin body and a portion of the pin head. It may include a cutout part into which the bending member is in close contact, a pin groove connected to the cutout part and formed to be stepped on the pin head so that the bending member comes into close contact with it, and a screw hole formed in the longitudinal direction on the side of the pin head.

In the turbine blade sealing assembly according to an embodiment of the present invention, the fixing pins may be formed in a number corresponding to the number of platforms.

In the turbine blade sealing assembly according to an embodiment of the present invention, the bending member is formed by bending a rectangular plate, but includes a horizontal portion that can be bent by plastic deformation, a stepped portion connected to the horizontal portion in a stepwise manner, and a bending member at the stepped portion. It may include a vertical portion bent vertically and a bent portion formed by bending a portion of the horizontal portion and supporting the pin head of the fixing pin.

A gas turbine according to an embodiment of the present invention,

A compressor that takes in outside air and compresses it; A combustor that mixes fuel with air compressed in a compressor and combusts it; A turbine whose turbine blades rotate by combustion gas discharged from the combustor; And, a turbine blade sealing assembly that seals the platform of the turbine blade and at least one side of the turbine rotor disk on which the turbine blade is mounted to seal the cooling passage for supplying cooling air to the turbine blade. Here, the turbine blade sealing assembly includes a sealing member that seals one side of at least two or more platforms formed adjacent to one side of a turbine rotor disk on which a root member formed in the lower portion of each of the two or more platforms is mounted; A fixing pin inserted into one lower side of the turbine rotor disk and fixing the sealing member to the turbine rotor disk; And, a bending member that is inserted together with the fixing pin to prevent the fixing pin from falling out.

In the gas turbine according to an embodiment of the present invention, the turbine rotor disk includes a mounting groove formed on one axial side and into which the radial inner end of the sealing member is inserted, and a mounting rib extending radially on one axial side. can do.

In the gas turbine according to an embodiment of the present invention, the sealing member may include a pin groove formed at a radially inner end position corresponding to a through hole formed in the mounting rib.

In the gas turbine according to an embodiment of the present invention, the number of pin grooves may be formed in a number corresponding to the number of platforms.

In the gas turbine according to an embodiment of the present invention, the sealing member includes a sealing body, a step portion radially supported by a step formed in the mounting groove, and a thickness that gradually becomes thinner as it goes from the step portion to the radial inner end. It may include an inclined portion.

In the gas turbine according to an embodiment of the present invention, the sealing member has a first arc-shaped groove formed to prevent stress concentration at the inner edge between the stepped portion and the sealing body, and a first chamfered surface formed at the other edge of the stepped portion. It can be included.

In the gas turbine according to an embodiment of the present invention, the turbine rotor disk may include a second arc-shaped groove formed on a concave edge of the step portion formed in the mounting groove and a second chamfered surface formed on a convex edge of the step portion.

In the gas turbine according to an embodiment of the present invention, the fixing pin includes a pin body, a pin head formed on one side of the pin body and having a larger outer diameter than the pin body, and a lower part of the pin body and a portion of the pin head and bent. It may include a cutout portion to which the member is in close contact, a pin groove that is connected to the cutout portion and is formed to be stepped on the pin head so that the bending member is in close contact, and a screw hole formed in the longitudinal direction on a side of the pin head.

In the gas turbine according to an embodiment of the present invention, the fixing pins may be formed in a number corresponding to the number of platforms.

In the gas turbine according to an embodiment of the present invention, the bending member is formed by bending a rectangular plate, but includes a horizontal portion that can be bent by plastic deformation, a stepped portion connected to the horizontal portion at a step, and a vertical portion at the stepped portion. It may include a bent vertical portion and a bent portion that is formed by bending a portion of the horizontal portion and supports the pin head of the fixing pin.

Details of other implementations of various aspects of the present invention are included in the detailed description below.

According to an embodiment of the present invention, a cooling passage for supplying cooling air to a turbine blade is sealed and a decrease in efficiency due to gas friction can be prevented. In addition, the structural stability of the blade can be improved by minimizing the load applied to the root member of the blade, and stress concentration on the turbine rotor disk and sealing member can be minimized.

1 is a perspective view showing a partially cut away gas turbine according to an embodiment of the present invention.
Figure 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.
Figure 3 is a partial cross-sectional view showing the internal structure of a gas turbine according to an embodiment of the present invention.
Figure 4 is a perspective view showing a turbine blade and a turbine rotor disk in one embodiment of the present invention.
5A and 5B are partially cut-away perspective views showing a turbine blade sealing assembly according to an embodiment of the present invention.
Figure 6 is a side cross-sectional view showing a turbine blade sealing assembly according to an embodiment of the present invention.
Figure 7 is a side cross-sectional view showing a state in which the fixing pin and bending member in Figure 6 are removed.
8A and 8B are perspective views showing a sealing member.
Figure 9 is an enlarged cross-sectional view of the contact portion between the sealing member and the turbine rotor disk.
Figure 10 is a perspective view showing a fixing pin.
Figure 11 is a perspective view showing a bending member.
Figure 12 is a perspective view showing a modified example of a bending member.
13 to 15 are diagrams illustrating the assembly process of the turbine blade sealing assembly according to an embodiment of the present invention.

Since the present invention can be modified in various ways and can have various embodiments, specific embodiments will be exemplified and explained in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, and should be understood to include all transformations, equivalents, and substitutes included in the spirit and technical scope of the present invention.

The terms used in the present invention are only used to describe specific embodiments and are not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly dictates otherwise. In the present invention, terms such as 'include' or 'have' are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. At this time, in the attached drawings, identical components are indicated by identical symbols whenever possible. Additionally, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components are exaggerated, omitted, or schematically shown in the accompanying drawings.

Figure 1 is a perspective view showing a gas turbine according to an embodiment of the present invention partially cut away, Figure 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention, and Figure 3 is an implementation of the present invention. This is a partial cross-sectional view showing the internal structure of a gas turbine according to an example.

As shown in FIG. 1, a gas turbine 1000 according to an embodiment of the present invention includes a compressor 1100, a combustor 1200, and a turbine 1300. The compressor 1100 includes a plurality of blades 1110 installed radially. The compressor 1100 rotates the blade 1110, and the air moves while being compressed by the rotation of the blade 1110. The size and installation angle of the blade 1110 may vary depending on the installation location. In one embodiment, the compressor 1100 is directly or indirectly connected to the turbine 1300 to receive a portion of the power generated by the turbine 1300 and use it to rotate the blades 1110.

Air compressed in the compressor 1100 moves to the combustor 1200. The combustor 1200 includes a plurality of combustion chambers 1210 and a fuel nozzle module 1220 arranged in an annular shape.

As shown in FIG. 2, the gas turbine 1000 according to an embodiment of the present invention is provided with a housing 1010, and at the rear of the housing 1010 is a diffuser 1400 through which combustion gas passing through the turbine is discharged. ) is provided. Additionally, a combustor 1200 is disposed in front of the diffuser 1400 to receive compressed air and combust it.

If explained based on the direction of air flow, the compressor 1100 is located on the upstream side of the housing 1010, and the turbine 1300 is located on the downstream side. Additionally, a torque tube 1500 is disposed between the compressor 1100 and the turbine 1300 as a torque transmission member that transmits the rotational torque generated by the turbine 1300 to the compressor 1100.

The compressor 1100 is provided with a plurality of compressor rotor disks 1120 (for example, 14 pieces), and each of the compressor rotor disks 1120 is fastened by a tie rod 1600 so as not to be spaced apart in the axial direction. .

Specifically, each compressor rotor disk 1120 is aligned with each other along the axial direction with the tie rod 1600 constituting the rotation axis passing through approximately the center. Here, the opposing surfaces of each neighboring compressor rotor disk 1120 are compressed by the tie rod 1600, so that relative rotation is impossible.

A plurality of blades 1110 are radially coupled to the outer peripheral surface of the compressor rotor disk 1120. Each blade 1110 has a dovetail portion 1112 and is fastened to the compressor rotor disk 1120.

A vane (not shown) fixed to the housing is located between each rotor disk 1120. Unlike the rotor disk, the vanes are fixed so as not to rotate, and align the flow of compressed air passing through the blades 1110 of the compressor rotor disk 1120 to the blades 1110 of the rotor disk 1120 located on the downstream side. It plays a role in guiding the air.

The fastening method of the dovetail portion 1112 includes a tangential type and an axial type. It can be selected depending on the required structure of a commercial gas turbine, and may have a commonly known dovetail or fir-tree shape. In some cases, the blade may be fastened to the rotor disk using a fastening device other than the above type, for example, a fastener such as a key or bolt.

The tie rod 1600 is arranged to penetrate the centers of the plurality of compressor rotor disks 1120 and turbine rotor disks 1320, and the tie rod 1600 may be composed of one or more tie rods. One end of the tie rod 1600 is fastened to the compressor rotor disk located on the most upstream side, and the other end of the tie rod 1600 is fastened by a fixing nut 1450.

The shape of the tie rod 1600 may have various structures depending on the gas turbine, so it is not necessarily limited to the shape shown in FIG. 2. That is, as shown, one tie rod may have a shape that penetrates the central part of the rotor disk, or a plurality of tie rods may have a shape arranged circumferentially, and a combination of these may be possible.

Although not shown, in the compressor of a gas turbine, vanes that serve as guide blades may be installed at the next position of the diffuser to adjust the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the pressure of the fluid. This is called a deswirler.

The combustor 1200 mixes and combusts the incoming compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas. The isobaric combustion process increases the temperature of the combustion gas to the heat resistance limit that the combustor and turbine parts can withstand. .

The combustors that make up the combustion system of a gas turbine may be arranged in large numbers in a housing formed in the form of a cell, including a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a combustor. It is composed of a transition piece that becomes the connection between the turbine and the turbine.

Specifically, the liner provides a combustion space where the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and burned. This liner may include a flame passage that provides a combustion space in which fuel mixed with air is combusted, and a flow sleeve that surrounds the flame passage and forms an annular space. Additionally, a fuel nozzle is coupled to the front end of the liner, and a spark plug is coupled to the side wall.

Meanwhile, at the rear end of the liner, a transition piece is connected to send combustion gas burned by the spark plug to the turbine side. The outer wall of this transition piece is cooled by compressed air supplied from the compressor to prevent damage due to the high temperature of combustion gas.

For this purpose, holes for cooling are provided in the transition piece to allow air to be sprayed inside, and the compressed air cools the body inside through the holes and then flows to the liner side.

Cooling air that cools the transition piece described above flows in the annular space of the liner, and compressed air from the outside of the flow sleeve may be provided as cooling air through cooling holes provided in the flow sleeve and collide with the outer wall of the liner.

Meanwhile, high-temperature, high-pressure combustion gas from the combustor is supplied to the turbine 1300. As the supplied high-temperature, high-pressure combustion gas expands, it collides with the rotor blades of the turbine, giving a recoil force to generate rotational torque. The rotational torque thus obtained is transmitted to the compressor through the torque tube 1500, providing the power necessary to drive the compressor. The excess power is used to drive generators, etc.

The turbine 1300 is basically similar to the structure of a compressor. That is, the turbine 1300 is also provided with a plurality of turbine rotor disks 1320 similar to the compressor rotor disk of a compressor. Accordingly, the turbine rotor disk 1320 also includes a plurality of turbine blades 1310 arranged radially. The turbine blade 1310 may also be coupled to the turbine rotor disk 1320 in a dovetail or other manner. In addition, a turbine vane 1330 fixed to the turbine casing 1350 is provided between the turbine blades 1310 to guide the flow direction of combustion gas passing through the turbine blade 1310.

The turbine vane 1330 is fixedly mounted within the turbine casing 1350 by a turbine vane platform 1340 coupled to the inner and outer ends of the turbine vane 1330. On the other hand, a ring segment 1360 is mounted inside the turbine casing 1350 at a position facing the outer end of the rotating turbine blade 1310 to form a predetermined gap with the outer end of the turbine blade 1310.

Meanwhile, a cooling passage 1314 (see FIG. 5) for supplying cooling air to the turbine blade 1310 may be formed inside the root member of the turbine blade. In order to form and seal the cooling passage, seal plates may be tightly coupled to the root member of the turbine blade and both axial sides of the rotor disk.

Conventionally, the seal plate was fixed to the root member of the turbine blade by fastening bolts, etc. However, there is a problem in that the head of the bolt protrudes from the seal plate and a windage loss occurs due to friction with gas during high-speed rotation. Additionally, centrifugal force increases due to the weight of the bolt assembled with the root member of the blade, which may cause increased stress on the root member of the blade. Accordingly, the present invention discloses a turbine blade sealing assembly (2000) to solve this problem.

Figure 4 is a perspective view showing a turbine blade and a turbine rotor disk in one embodiment of the present invention.

Referring to FIG. 4, the turbine blade 1310 includes an airfoil 1311, a platform 1312, and a root member 1313.

The airfoil 1311 is formed on the upper surface of the platform 1312. The airfoil 1311 is formed to have an airfoil optimized according to the specifications of the gas turbine, and has a leading edge (LE) disposed on the upstream side and a trailing edge (TE) disposed on the downstream side based on the flow direction of the combustion gas. is provided.

에 이르는 고온이기 때문에 별도의 냉각 수단을 필요로 한다. 이를 위해서, 압축기의 일부 개소에서 압축된 공기를 추기하여 터빈 블레이드(1310)로 공급하는 냉각 유로를 구비한다. 냉각 유로는 하우징 외부에서 연장되거나(외부 유로), 로터 디스크의 내부를 관통하여 연장될 수 있고(내부 유로), 외부 및 내부 유로를 모두 사용할 수도 있다.Unlike the compressor blades, the turbine blades 1310 are in direct contact with high-temperature and high-pressure combustion gas. The temperature of combustion gas is 1700

Because the temperature is high, a separate cooling means is required. For this purpose, a cooling passage is provided to extract compressed air from some portion of the compressor and supply it to the turbine blade 1310. The cooling passage may extend outside the housing (external passage), may extend through the inside of the rotor disk (internal passage), or both external and internal passages may be used.

In addition, a plurality of cooling holes 1311a are formed on the surface of the airfoil 1311, and the cooling holes 1311a communicate with a cooling passage (not shown) formed inside the airfoil 1311 to supply cooling air to the air. It is supplied to the surface of the foil (1311).

A platform 1312 is disposed below the airfoil 1311. The platform 1312 may be formed in a substantially square plate shape. A cooling passage through which cooling air can flow is formed inside the airfoil 1311, and the cooling air may flow into the cooling passage 1314 (see FIG. 5) through the platform 1312.

The root member 1313 is disposed radially inside the platform 1312. The radial interior of platform 1312 may be the lower portion of platform 1312 . The root member 1313 is formed to be narrow in width in the radial direction. Dovetails are formed on both sides of the root member 1313 in the circumferential direction. The dovetail has a fir-tree shape in cross section and can be formed in plural pieces.

The turbine rotor disk 1320 has a substantially disk shape, and a plurality of coupling slots 1321 are formed on its outer periphery. The coupling slot 1321 is formed to have a curved surface in the shape of a fir-tree. The turbine blade 1310 may be fastened to the coupling slot 1321.

FIGS. 5A and 5B are partially cut-away perspective views showing a turbine blade sealing assembly according to an embodiment of the present invention, FIG. 6 is a side cross-sectional view showing a turbine blade sealing assembly according to an embodiment of the present invention, and FIG. 7 is a side cross-sectional view showing the state in which the fixing pin and bending member in FIG. 6 are removed.

Referring to FIGS. 5A to 7 , the turbine blade sealing assembly 2000 according to an embodiment of the present invention includes a sealing member 2100, a fixing pin 2200, and a bending member 2300.

The turbine rotor disk 1320 has a mounting groove 1325 formed on at least one axial side and into which the radial inner end of the sealing member 2100 is inserted, and a mounting rib 1321 extending radially on one axial side. Includes. The mounting groove 1325 may be formed between the mounting rib 1321 and the side surface of the turbine rotor disk 1320.

The cross section of the mounting groove 1325 may be formed in a substantially rectangular shape. The mounting rib 1321 may be formed in the axial direction of a through hole 1322 into which the fixing pin 2200 is inserted. The through hole 1322 may include a head receiving portion 1322a in which a pin head 2220, which will be described later, is accommodated.

The sealing member 2100 seals at least one side of the platform 1312 and the turbine rotor disk 1320. The sealing member 2100 is generally formed in a plate shape and is mounted on one or both sides of the platform 1312 and the turbine rotor disk 1320 to seal the cooling passage 1314.

One sealing member 2100 can seal one side of at least two platforms 1312 formed adjacent to each other. In this regard, Figure 5a illustrates that one sealing member 2100 is formed to seal one side of one platform 1312, and Figure 5b illustrates one sealing member 2100 of two platforms 1312. It is exemplified that it is formed to seal one side. Figure 5b shows that when one sealing member 2100_2 seals one side of at least two platforms 1312, the assembly process can be simplified by reducing the number of sealing members 2100.

A screw hole 2111 may be formed in the central portion of one side of the sealing member 2100. The screw hole 2111 may not penetrate the sealing member 2100 and may be formed to a depth of approximately half the thickness. Since a screw thread is formed on the inner peripheral surface of the screw hole 2111, the sealing member 2100 can be easily moved to an accurate position by fastening a screw to the screw hole 2111 when assembling the sealing member 2100. The sealing member 2100 will be described later with reference to FIGS. 8 and 9.

The fixing pin 2200 is inserted into one lower side of the turbine rotor disk 1320 to secure the sealing member 2100 to the turbine rotor disk 1320. The fixing pin 2200 can be inserted into the through hole 1322 formed in the turbine rotor disk 1320 and fixed to the turbine rotor disk 1320 by supporting the sealing member 2100 in the radial direction. The number of fixing pins 2200 may correspond to the number of platforms 1312. One fixing pin 2200 may support one sealing member 2100, or a plurality of fixing pins 2200 may support one sealing member 2100.

For example, when one sealing member 2100 seals one side of one platform 1312 as shown in Figure 5a, one fixing pin 2200 may be provided, and as shown in Figure 5b, one sealing member ( When 2100 seals one side of the two platforms 1312, two fixing pins 2200 may be provided. The fixing pin 2200 will be described later with reference to FIG. 10.

The bending member 2300 is inserted into the through hole 1322 of the turbine rotor disk 1320 together with the fixing pin 2200 to prevent the fixing pin 2200 from falling out of the through hole 1322. The bending member 2300 will be described later with reference to FIG. 11 .

FIGS. 8A and 8B are perspective views showing the sealing member 2100, and FIG. 9 is an enlarged cross-sectional view showing a contact portion between the sealing member 2100 and the turbine rotor disk 1320.

Referring to FIGS. 8A and 8B , the sealing member 2100 may include a pin groove 2140 formed at a radially inner end position corresponding to the through hole 1322 of the mounting rib 1321. The pin groove 2140 may be formed in a semicircular shape at the central portion in the width direction at the radial inner end of the sealing member 2100. Approximately half the thickness of the fixing pin 2200 may be inserted into the pin groove 2140 to support the sealing member 2100.

The pin grooves 2140 may be formed in a number corresponding to the number of platforms 1312. One pin groove 2140 may be formed in one sealing member 2100, or a plurality of pin grooves 2140 may be formed in one sealing member 2100.

For example, when one sealing member 2100 seals one side of one platform 1312 as shown in Figure 5a, the pin groove 2140 may be formed as one, and as shown in Figure 5b, one sealing member ( When 2100 seals one side of the two platforms 1312, two pin grooves 2140 may be formed.

The sealing member 2100 may include an inclined portion 2130 whose thickness gradually becomes thinner as it goes from the step portion 2120 to the radially inner end. The lower end of the inclined portion 2130 may be formed to have a thickness smaller than the thickness of the sealing body 2110 formed on the stepped portion 2120 of the sealing member 2100. The inclined portion 2130 may not start directly from the step portion 2120, but may be connected at the bottom of the vertical surface at a predetermined height. According to this structure of the sealing member 2100, when the lower part of the sealing member 2100 is tilted and inserted into the mounting groove 1325, it can be easily inserted without interference.

The sealing member 2100 includes a first arc-shaped groove 2121 formed at the inner edge between the stepped portion 2120 and the sealing body 2110 to prevent stress concentration, and a first groove formed at the other edge of the stepped portion 2120. It may further include a chamfer surface (2122).

The first arc-shaped groove 2121 may be formed in the form of a groove with a predetermined radius of curvature at the inner edge between the upper surface of the step portion 2120 and the side surface of the sealing body 2110. That is, by forming the first arc-shaped groove 2121 at the inner corner where two planes meet vertically, it is possible to prevent stress from concentrating at that area.

The first chamfered surface 2122 may be formed at an angle of 40 to 50 degrees at an outer corner where the upper surface of the step portion 2120 and the inclined portion 2130 meet. The first chamfered surface 2122 prevents stress from concentrating on the corner portion and reduces damage caused by collision with other parts when assembling or disassembling the sealing member 2100.

Referring to FIG. 9, the turbine rotor disk 1320 also has a second arc-shaped groove 1323a formed on the concave edge of the step portion 1323 formed in the mounting groove 1325, and a second arc-shaped groove 1323a formed on the convex edge of the step portion 1323. 2 It may further include a chamfer surface (1323b).

The second arc-shaped groove 1323a may be formed in the form of a groove with a predetermined radius of curvature at the inner edge where the vertical surface of the mounting groove 1325 of the turbine rotor disk 1320 meets the horizontal surface of the step portion 1323. That is, by forming the second arc-shaped groove 1323a at the inner corner where two planes meet vertically, it is possible to prevent stress from concentrating at that area. In addition, the first chamfered surface 2122 of the sealing member 2100 is located in front of the second arc-shaped groove 1323a, and the sealing member 2100 is tilted by the second arc-shaped groove 1323a to fit into the mounting groove 1325. Interference during insertion can also be minimized.

The second chamfered surface 1323b may be formed at an angle of 40 to 50 degrees at the convex edge of the step portion 1323 of the mounting groove. Not only can the second chamfered surface 1323b prevent stress from being concentrated in that area, but the first arc-shaped groove 2121 of the sealing member 2100 is located in front of the second chamfered surface 1323b. Interference with each other during disassembly and assembly can also be minimized.

Figure 10 is a perspective view showing the fixing pin 2200.

Referring to FIG. 10, the fixing pin 2200 may be formed overall in a cylindrical shape, and a chamfer may be formed at one end edge. Specifically, the fixing pin 2200 may include a pin body 2210, a pin head 2220, a pin groove 2230, a cutout 2240, and a screw hole 2250.

The pin body 2210 is formed in a cylindrical shape, and the pin head 2220 is formed in a cylindrical shape with a larger outer diameter than the pin body 2210, and the pin body 2210 and the pin head 2220 are integrally stepped. can be formed.

A cutout portion 2240 into which the bending member 2300 is in close contact may be formed in the entire pin body 2210 and a lower part of the pin head 2220. The cut surface of the cut portion 2240 may be formed in a flat shape, and a stepped surface perpendicular to the cut surface may be formed in the lower middle of the pin head 2220. Additionally, the cutout portion 2240 may be formed with a chamfer at the end of the pin body 2210.

The pin groove 2230 is connected to the cutout portion 2240 and is formed to be stepped on the pin head 2220 to allow the bending member 2300 to come into close contact with it. The pin groove 2230 may be shallower than the cut portion 2240 and may be formed to be stepped from the cut portion 2240. The cut portion 2240 extends in a plane direction to the circumferential surface of the fixing pin 2200 in its width direction, but the pin groove 2230 has a width smaller than the outer diameter of the pin head 2220, so that the pin groove 2230 has a width smaller than the outer diameter of the pin head 2220. It may be formed to be stepped from the main surface to the bottom of the pin groove 2230.

The screw hole 2250 may be formed in the longitudinal direction on the side of the pin head 2220. The screw hole 2250 may be formed eccentrically toward the opposite side of the pin groove 2230 rather than at the center of the pin head 2220. The depth of the screw hole 2250 may be greater than the length of the pin head 2220. The screw hole 2250 has a thread formed on its inner peripheral surface, so when disassembling the fixing pin 2200, a bolt is fastened to the screw hole 2250 and the bolt is pulled to insert the fixing pin 2200 into the through hole 1322. It can be easily separated from.

FIG. 11 is a perspective view showing the bending member 2300, and FIG. 12 is a perspective view showing a modified example of the bending member.

Referring to FIG. 11, the bending member 2300 is formed by bending a rectangular plate, and includes a horizontal portion 2310 that can be bent by plastic deformation, a stepped portion 2320 connected to the horizontal portion at a step, and a stepped portion It may include a vertical portion 2330 bent vertically.

The bending member 2300 can be formed by bending a rectangular metal plate with a predetermined width, length, and thickness. The bending member 2300 may be made of a material that is easily bent by plastically deforming the entire plate, or may be made of a material that is bent by plastically deforming only the portion of the horizontal portion 2310 that is bent after the bending member 2300 is inserted.

The horizontal portion 2310 is a rectangular plate, and the non-bent portion of the horizontal portion 2310 can be inserted into the pin groove 2230 of the fixing pin 2200 and placed.

The stepped portion 2320 may be formed by bending upward at one end of the horizontal portion 2310 and then bending horizontally again. Referring to FIG. 6, the step portion 2320 may be located between the cut portion 2240 of the fixing pin 2200 and the through hole 1322.

The vertical portion 2330 may be formed by bending downward at one end of the stepped portion 2320. The vertical portion 2330 may be formed to be more than twice as long as the step height of the step portion 2320. The vertical portion 2330 can be in close contact with the inner surface of the mounting rib 1321 to prevent the bending member 2300 from falling out.

Referring to FIG. 6, the bending member 2300 is inserted into the through hole 1322 of the mounting rib 1321, and after inserting the fixing pin 2200, a portion of the horizontal portion 2310 is bent upward. The pin head 2220 of the fixing pin 2200 can be fixed and supported by the formed bent portion 2350. At this time, the bent portion 2350 is bent and then disposed inside the head receiving portion 1322a, so that the bending member 2300 and the pin head 2220 of the fixing pin 2200 are connected to the through hole 1322 of the mounting rib 1321. ) It may not protrude from the outer surface.

Referring to FIG. 12 , the bending member 2300 may further include an insertion protrusion 2340 formed on the upper surface of the bent portion 2350. The insertion protrusion 2340 may be inserted into the screw hole 2250 of the fixing pin 2200 when the bent portion 2350 is bent. However, since a screw thread is not formed on the insertion protrusion 2340, it is not fastened to the screw hole 2250.

Next, the assembly process of the turbine blade sealing assembly according to an embodiment of the present invention will be described with reference to FIGS. 13 to 15. 13 to 15 are diagrams illustrating the assembly process of the turbine blade sealing assembly according to an embodiment of the present invention.

First, as shown in FIG. 4, the root member 1313 of the turbine blade 1310 is inserted and mounted into the slot 1321 of the turbine rotor disk 1320.

Next, as shown in FIG. 7, the sealing member 2100 is mounted between the platform 1312 of the turbine blade 1310 and the mounting rib 1321 of the turbine rotor disk 1320. At this time, the radially inner end of the sealing member 2100 may be inserted into the mounting groove 1325.

Next, as shown in FIG. 13, the bending member 2300 is inserted and mounted into the through hole 1322 formed in the mounting rib 1321. At this time, the horizontal portion 2310 of the bending member 2300 is not bent, and the step portion 2320 and the vertical portion 2330 can be inserted and mounted to be seated in the through hole 1322.

Next, as shown in FIGS. 13 and 14, the fixing pin 2200 is inserted and mounted into the through hole 1322 of the mounting rib 1321 and the pin groove 2140 formed in the sealing member 2100. At this time, the step portion between the pin body 2210 and the pin head 2220 of the fixing pin 2200 may be inserted so as to be supported in close contact with the step portion between the through hole 1322 and the head receiving portion 1322a. In addition, the fixing pin 2200 can be inserted and mounted so that the step portion 2320 and the horizontal portion 2310 of the bending member 2300 are in contact with the cut portion 2240 and the pin groove 2230 of the fixing pin 2200. You can.

Next, as shown in FIG. 14, the portion of the bending member 2300 that protrudes outside the mounting rib 1321 is bent to support the fixing pin 2200. That is, the bent portion 2350 formed by vertically bending the protruding end of the horizontal portion 2310 of the bending member 2300 is brought into close contact with the pin head 2220 of the fixing pin 2200 to support the fixing pin 2200. can do.

As shown in FIG. 15, the bent portion 2350 formed by bending a portion of the horizontal portion 2310 may be disposed inside the through hole 1322 of the turbine rotor disk 1320. That is, since the fixing pin 2200 or the bending member 2300 does not protrude from the outer surface of the mounting rib 1321, it is possible to prevent flow loss from occurring due to the protrusion rubbing against gas.

Above, an embodiment of the present invention has been described, but those skilled in the art can add, change, delete or add components without departing from the spirit of the present invention as set forth in the patent claims. The present invention may be modified and changed in various ways, and this will also be included within the scope of rights of the present invention.

1000: gas turbine
1100: Compressor
1200: Combustor
1300: Turbine
1310: turbine blade
1320: Turbine rotor disk
2000: Turbine blade sealing assembly
2100: Sealing member
2110: Sealing body 2120: Stepped portion
2130: inclined portion 2140: pin groove
2200: fixing pin
2210: pin body 2220: pin head
2230: pin groove 2240: cutout
2250: screw hole
2300: bending member
2310: horizontal part 2320: step part
2330: Vertical portion 2340: Insertion protrusion
2350: bending part

Claims (20)

a sealing member sealing one side of at least two or more platforms formed adjacent to one side of a turbine rotor disk on which a root member formed at a lower portion of each of the two or more platforms is mounted;
a fixing pin inserted into a lower side of the turbine rotor disk and fixing the sealing member to the turbine rotor disk; and,
A turbine blade sealing assembly comprising a bending member that is inserted together with the fixing pin to prevent the fixing pin from being removed.
The method according to claim 1, wherein the turbine rotor disk,
a mounting groove formed on one axial side into which the radial inner end of the sealing member is inserted;
Mounting rib extending radially from one axial side
Including a turbine blade sealing assembly.
The method of claim 2, wherein the sealing member,
A turbine blade sealing assembly comprising a pin groove formed at a radially inner end position corresponding to a through hole formed in the mounting rib.
In claim 3,
The turbine blade sealing assembly, wherein the pin grooves are formed in a number corresponding to the number of the platforms.
The method of claim 2, wherein the sealing member,
a sealing body,
a stepped portion supported in the radial direction on a stepped portion formed in the mounting groove;
An inclined portion whose thickness gradually becomes thinner as it moves from the step to the radial inner end.
Including a turbine blade sealing assembly.
The method of claim 5, wherein the sealing member,
a first arc-shaped groove formed to prevent stress concentration at an inner edge between the step portion and the sealing body;
A first chamfer surface formed on the other edge of the step portion
Including a turbine blade sealing assembly.
The method of claim 6, wherein the turbine rotor disk,
a second arc-shaped groove formed in a concave corner of the step formed in the mounting groove;
A second chamfer surface formed on the convex edge of the step portion
Including a turbine blade sealing assembly.
The method of claim 2, wherein the fixing pin is,
pin body,
a pin head formed on one side of the pin body and having an outer diameter larger than the pin body;
a cutout portion formed at a lower portion of the pin body and a portion of the pin head and into which the bending member is in close contact;
a pin groove connected to the cut portion and formed to be stepped on the pin head so that the bending member is in close contact;
Screw hole formed in the longitudinal direction on the side of the pin head
Including a turbine blade sealing assembly.
The method of claim 8, wherein the fixing pin is,
A turbine blade sealing assembly formed in a number corresponding to the number of platforms.
The method of claim 8, wherein the bending member,
A horizontal portion that is formed by bending a rectangular plate and can be bent by plastic deformation,
A stepped portion connected to the horizontal portion in a stepped manner,
A vertical portion bent vertically at the step portion,
A bent portion formed by bending a portion of the horizontal portion and supporting the pin head of the fixing pin.
Including a turbine blade sealing assembly.
A compressor that takes in outside air and compresses it;
a combustor that mixes fuel with air compressed by the compressor and combusts it;
A turbine whose turbine blades rotate by combustion gas discharged from the combustor; and,
a turbine blade sealing assembly that seals a platform of the turbine blade and at least one side of a turbine rotor disk on which the turbine blade is mounted to seal a cooling passage for supplying cooling air to the turbine blade;
Includes, the turbine blade sealing assembly,
a sealing member sealing one side of at least two or more platforms formed adjacent to each other and one side of a turbine rotor disk on which a root member formed at a lower portion of each of the two or more platforms is mounted;
a fixing pin inserted into a lower side of the turbine rotor disk and fixing the sealing member to the turbine rotor disk; and,
A gas turbine including; a bending member that is inserted together with the fixing pin to prevent the fixing pin from falling out.
The method of claim 11, wherein the turbine rotor disk,
a mounting groove formed on one axial side into which the radial inner end of the sealing member is inserted;
Mounting rib extending radially from one axial side
Including gas turbines.
The method of claim 12, wherein the sealing member,
A gas turbine comprising a pin groove formed at a radially inner end position corresponding to a through hole formed in the mounting rib.
In claim 13,
The gas turbine is formed in a number corresponding to the number of the platforms.
The method of claim 12, wherein the sealing member,
a sealing body,
a stepped portion supported in the radial direction on a stepped portion formed in the mounting groove;
An inclined portion whose thickness gradually becomes thinner as it moves from the step to the radial inner end.
Including gas turbines.
The method of claim 15, wherein the sealing member,
a first arc-shaped groove formed to prevent stress concentration at an inner edge between the step portion and the sealing body;
A first chamfer surface formed on the other edge of the step portion
Including gas turbines.
The method of claim 16, wherein the turbine rotor disk,
a second arc-shaped groove formed in a concave corner of the step formed in the mounting groove;
A second chamfer surface formed on the convex edge of the step portion
Including gas turbines.
The method of claim 12, wherein the fixing pin is,
pin body,
a pin head formed on one side of the pin body and having an outer diameter larger than the pin body;
a cutout portion formed at a lower portion of the pin body and a portion of the pin head and into which the bending member is in close contact;
a pin groove connected to the cut portion and formed to be stepped on the pin head so that the bending member is in close contact;
Screw hole formed in the longitudinal direction on the side of the pin head
Including gas turbines.
The method of claim 18, wherein the fixing pin is,
A gas turbine formed by a number corresponding to the number of platforms.
The method of claim 18, wherein the bending member,
A horizontal portion that is formed by bending a rectangular plate and can be bent by plastic deformation,
A stepped portion connected to the horizontal portion in a stepped manner,
A vertical portion bent vertically at the step portion,
A bent portion formed by bending a portion of the horizontal portion and supporting the pin head of the fixing pin.
Including gas turbines.

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