KR102851278B1 - Turbine blade sealing assembly and gas turbine comprising it - Google Patents

Abstract

A turbine blade sealing assembly and a gas turbine including the same are disclosed, which seal a cooling passage for supplying cooling air to a turbine blade and prevent efficiency reduction due to gas friction.
The disclosed turbine blade sealing assembly comprises:
It includes a sealing member that seals one side of at least two or more adjacently formed platforms and one side of a turbine rotor disk on which a root member formed at the lower portion of each of the two or more platforms is mounted; a fixing pin that is inserted into one lower side of the turbine rotor disk to fix 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 coming off.

Description

Turbine blade sealing assembly and gas turbine comprising it {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 by utilizing the flow of compressible fluid such as steam or gas. Examples include steam turbines that use steam and gas turbines that use high-temperature combustion gas.

Among these, the gas turbine is largely composed of a compressor, a combustor, and a turbine. The compressor is equipped 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 compressed in the compressor and ignites it with a burner, thereby generating high-temperature, high-pressure combustion gas.

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

The rotor is rotatably supported at both ends by bearings. A plurality of disks are fixed to the rotor, and each blade is connected to the rotor. At the same time, a drive shaft for a generator or the like is connected to the end on the exhaust side.

Since these gas turbines do not have a reciprocating mechanism such as a piston in a four-stroke engine, there are no frictional parts such as pistons and cylinders, so they consume very little lubricating oil, and they have the advantage of greatly reducing the amplitude, which is a characteristic of reciprocating machines, and enabling high-speed operation.

Briefly, the operation of a gas turbine involves: compressed air from a compressor is mixed with fuel and combusted to produce high-temperature combustion gas, which is then injected into the turbine. As the injected combustion gas passes through the turbine vanes and blades, it generates rotational force, which in turn rotates the rotor.

Republic of Korea Patent Publication No. 10-2010-0064754 (Title: Cooling blade for gas turbine)

The present invention aims to provide a turbine blade sealing assembly capable of sealing a cooling passage for supplying cooling air to a turbine blade and preventing a decrease in efficiency due to gas friction, and a gas turbine including the same.

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

It includes a sealing member that seals one side of at least two or more adjacently formed platforms and one side of a turbine rotor disk on which a root member formed at the lower portion of each of the two or more platforms is mounted; a fixing pin that is inserted into one lower side of the turbine rotor disk to fix 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 coming off.

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

In a 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 a mounting rib.

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

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

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

In a 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 a concave edge of a stepped portion formed in a mounting groove, and a second chamfered surface formed on a convex edge of the stepped portion.

In a turbine blade sealing assembly according to an embodiment of the present invention, a fixed pin may include a pin body, a pin head formed on one side of the pin body and having an outer diameter larger than that of the pin body, a cut portion formed on a lower portion of a portion of the pin body and the pin head and to which a bending member is in close contact, a pin groove formed to be connected to the cut portion and formed to be stepped with respect to the pin head and to which the bending member is in close contact, and a screw hole formed longitudinally on a side surface of the pin head.

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

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

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

A turbine includes a compressor that sucks in outside air and compresses it; a combustor that mixes fuel with the compressed air from the compressor and combusts it; a turbine that rotates turbine blades by combustion gas discharged from the combustor; and a turbine blade sealing assembly that seals a platform of a turbine blade and at least one side of a turbine rotor disk on which the turbine blades are mounted to seal a cooling passage for supplying cooling air to the turbine blades. Here, the turbine blade sealing assembly includes a sealing member that seals one side of at least two or more adjacently formed platforms 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 that is inserted into one lower side of the turbine rotor disk to fix 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 coming off.

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

In a 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 a mounting rib.

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

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

In a gas turbine according to an embodiment of the present invention, the sealing member may include a first arc-shaped groove formed to prevent stress concentration at an inner edge between a step portion and a sealing body, and a first chamfered surface formed at the other edge of the step portion.

In a 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 a stepped portion formed in a mounting groove, and a second chamfered surface formed on a convex edge of the stepped portion.

In a gas turbine according to an embodiment of the present invention, a fixed pin may include a pin body, a pin head formed on one side of the pin body and having an outer diameter larger than that of the pin body, a cut portion formed on a lower portion of a portion of the pin body and the pin head and to which a bending member is in close contact, a pin groove formed to be connected to the cut portion and formed to be stepped with respect to the pin head and to which the bending member is in close contact, and a screw hole formed longitudinally on a side surface of the pin head.

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

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

Specific details of implementation examples according to various aspects of the present invention are included in the detailed description below.

According to an embodiment of the present invention, a cooling path for supplying cooling air to a turbine blade can be sealed, thereby preventing efficiency loss due to gas friction. Furthermore, the structural stability of the blade can be improved by minimizing the load applied to the blade root member, and stress concentration between the turbine rotor disk and the sealing member can be minimized.

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

The present invention is susceptible to various modifications and embodiments. Specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, but rather to encompass all modifications, equivalents, and alternatives falling within the spirit and technical scope of the present invention.

The terminology used herein is merely used to describe specific embodiments and is not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly indicates otherwise. In the present invention, it should be understood that the terms "comprise" or "have" are intended to specify the presence of a feature, number, step, operation, component, part, or combination thereof described in the specification, but do not exclude in advance the possibility of the presence or addition of one or more other features, 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. In the drawings, identical components are represented by identical reference numerals, wherever possible. Furthermore, 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 in the attached drawings are exaggerated, omitted, or schematically depicted.

FIG. 1 is a perspective view showing a gas turbine according to an embodiment of the present invention with a portion cut away, FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention, and FIG. 3 is a cross-sectional view showing a portion of the internal structure of a gas turbine according to an embodiment of the present invention.

As illustrated in FIG. 1, a gas turbine (1000) according to one embodiment of the present invention includes a compressor (1100), a combustor (1200), and a turbine (1300). The compressor (1100) has a plurality of blades (1110) that are radially installed. The compressor (1100) rotates the blades (1110), and air moves while being compressed by the rotation of the blades (1110). The size and installation angle of the blades (1110) may vary depending on the installation location. In one embodiment, the compressor (1100) is directly or indirectly connected to the turbine (1300), and may 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) arranged in an annular shape and a fuel nozzle module (1220).

As illustrated in FIG. 2, 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 side of the housing (1010) through which combustion gas passing through the turbine is discharged. In addition, a combustor (1200) is arranged in front of the diffuser (1400) to receive compressed air and combust it.

In terms of the direction of air flow, a compressor (1100) is positioned on the upstream side of the housing (1010), and a turbine (1300) is positioned on the downstream side. In addition, a torque tube (1500) is positioned between the compressor (1100) and the turbine (1300) as a torque transmission member that transmits the rotational torque generated in the turbine (1300) to the compressor (1100).

The compressor (1100) is provided with a plurality of (e.g., 14) compressor rotor disks (1120), and each of the compressor rotor disks (1120) is connected to the axial direction by a tie rod (1600) so as not to be spaced apart from each other.

Specifically, each compressor rotor disk (1120) is aligned axially with respect to one another with a tie rod (1600) forming a rotation axis passing through the center. Here, each adjacent compressor rotor disk (1120) is arranged so that the opposing surfaces are pressed by the tie rod (1600) so that relative rotation is impossible.

A plurality of blades (1110) are radially connected to the outer surface of the compressor rotor disc (1120). Each blade (1110) has a dovetail portion (1112) and is fastened to the compressor rotor disc (1120).

Between each rotor disk (1120), a vane (not shown) is positioned and fixed to the housing. Unlike the rotor disk, the vane is fixed so as not to rotate, and serves to align the flow of compressed air passing through the blades (1110) of the compressor rotor disk (1120) and guide the air to the blades (1110) of the rotor disk (1120) located on the downstream side.

The dovetail portion (1112) can be fastened in two types: a tangential type and an axial type. These can be selected based on the required structure of a commercially available gas turbine, and can have the commonly known dovetail or fir-tree shape. In some cases, the blade can be fastened to the rotor disk using fasteners other than the above types, such as a key or bolt.

A tie rod (1600) is arranged to penetrate the center of a 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 within a compressor rotor disk located on the uppermost side, and the other end of the tie rod (1600) is fastened by a fixing nut (1450).

The shape of the tie rod (1600) can be configured in various structures depending on the gas turbine, and is therefore not necessarily limited to the shape shown in Fig. 2. That is, as shown, a single tie rod may have a shape penetrating the center of the rotor disk, or a plurality of tie rods may have a shape arranged circumferentially, and a combination of these is also possible.

Although not shown, a vane that acts as a guide vane may be installed at the next position of the diffuser in the compressor of a gas turbine 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.

In the combustor (1200), the introduced compressed air is mixed with fuel and combusted to create high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is increased to the heat resistance limit that the combustor and turbine components can withstand through the isobaric combustion process.

The combustors that constitute the combustion system of a gas turbine can be arranged in a plurality within a housing formed in a cell shape, and are configured to include a burner including a fuel injection nozzle, a combustor liner that forms a combustion chamber, and a transition piece that serves as a connection between the combustor and the turbine.

Specifically, the liner provides a combustion space where fuel injected by the fuel nozzle is mixed with compressed air from the compressor and combusted. The liner may include a flame chamber, which provides a combustion space where the fuel mixed with air is combusted, and a flow sleeve that surrounds the flame chamber to form an annular space. Furthermore, a fuel nozzle is attached to the front end of the liner, and a spark plug is attached to the side wall.

Meanwhile, a transition piece is connected to the rear end of the liner to direct combustion gases combusted by the spark plug toward the turbine. To prevent damage caused by the high temperature of the combustion gases, the outer wall of this transition piece is cooled by compressed air supplied from the compressor.

To this end, the transition piece is provided with cooling holes to allow air to be injected into the interior, and the compressed air cools the main body inside through the holes and then flows to the liner side.

Cooling air that cools the aforementioned transition piece flows through the annular space of the liner, and compressed air from the outside of the flow sleeve can collide with the cooling air through cooling holes provided in the flow sleeve on 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 turbine's rotating blades, providing a reaction force to generate rotational torque. The rotational torque thus obtained is transmitted to the compressor via the torque tube (1500), and any power exceeding the power required to drive the compressor is used to drive a generator, etc.

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

The turbine vane (1330) is fixedly mounted within the turbine casing (1350) by means of 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 at a position facing the outer end of the turbine blade (1310) that rotates within the turbine casing (1350) so as 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. To form and seal the cooling passage, seal plates may be tightly coupled to the root member of the turbine blade and both axial surfaces of the rotor disk.

Conventionally, seal plates have been secured to the root member of turbine blades by bolts or the like. However, there is a problem in that the head of the bolt protrudes from the seal plate, resulting in windage loss due to friction with gas during high-speed rotation. Furthermore, the weight of the bolt assembled with the root member of the blade increases centrifugal force, 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 these problems.

FIG. 4 is a perspective view illustrating 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).

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

Unlike the compressor blades, the turbine blades (1310) come into direct contact with the high temperature and high pressure combustion gas. The temperature of the combustion gas is 1700 Because the temperature reaches a high temperature, a separate cooling means is required. To this end, a cooling path is provided to extract compressed air from some part of the compressor and supply it to the turbine blades (1310). The cooling path may extend outside the housing (external path), extend through the inside of the rotor disk (internal path), or use both external and internal paths.

And, a number of cooling holes (1311a) are formed on the surface of the airfoil (1311), and the cooling holes (1311a) are connected to a cooling path (not shown) formed inside the airfoil (1311) to supply cooling air to the surface of the airfoil (1311).

A platform (1312) is arranged at the bottom of the airfoil (1311). The platform (1312) may be formed in a roughly rectangular plate shape. A cooling path through which cooling air can flow is formed inside the airfoil (1311), and the cooling air can be introduced into the cooling path (1314, see FIG. 5) through the platform (1312).

The root member (1313) is positioned radially inwardly of the platform (1312). The radially inwardly of the platform (1312) may be the lower portion of the platform (1312). The root member (1313) is formed so that its width narrows radially inwardly. Dovetails are formed on both circumferential sides of the root member (1313). The dovetails may have a cross-section shaped like a fir tree and may be formed in multiple pieces.

The turbine rotor disk (1320) has a roughly circular shape, and a plurality of coupling slots (1321) are formed on its outer periphery. The coupling slots (1321) are formed to have a curved surface in the shape of a fir tree. The turbine blade (1310) can be fastened to the coupling slots (1321).

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

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

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

The cross-section of the mounting groove (1325) may be formed to have a roughly rectangular shape. A through hole (1322) into which a fixing pin (2200) is inserted may be formed in the axial direction of the mounting rib (1321). The through hole (1322) may include a head receiving portion (1322a) into which a pin head (2220) described later is received.

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 or more adjacently formed platforms (1312). In this regard, FIG. 5a illustrates that one sealing member (2100) is formed to seal one side of one platform (1312), and FIG. 5b illustrates that one sealing member (2100) is formed to seal one side of two platforms (1312). FIG. 5b illustrates that when one sealing member (2100_2) seals one side of at least two or more platforms (1312), the number of sealing members (2100) can be reduced, thereby simplifying the assembly process.

A screw hole (2111) may be formed in the center of one side of the sealing member (2100). The screw hole (2111) may be formed to a depth of approximately half the thickness of the sealing member (2100) without penetrating the sealing member (2100). Since screw threads are formed on the inner circumferential surface of the screw hole (2111), when assembling the sealing member (2100), the sealing member (2100) can be easily moved to an accurate position by fastening a screw to the screw hole (2111). The sealing member (2100) will be described later with reference to FIGS. 8 and 9.

The fixed pin (2200) is inserted into one side of the lower portion of the turbine rotor disk (1320) to fix the sealing member (2100) to the turbine rotor disk (1320). The fixed pin (2200) is inserted into a through hole (1322) formed in the turbine rotor disk (1320) to radially support the sealing member (2100), thereby fixing the sealing member to the turbine rotor disk (1320). The number of fixed pins (2200) may correspond to the number of platforms (1312). One fixed pin (2200) may support one sealing member (2100), or multiple fixed pins (2200) may support one sealing member (2100).

For example, when one sealing member (2100) seals one side of one platform (1312) as in Fig. 5a, one fixing pin (2200) may be provided, and when one sealing member (2100) seals one side of two platforms (1312) as in Fig. 5b, 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 coming out of the through hole (1322). The bending member (2300) will be described later with reference to FIG. 11.

FIG. 8a and FIG. 8b are perspective views illustrating a sealing member (2100), and FIG. 9 is an enlarged cross-sectional view illustrating 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 semicircle at a widthwise central position at the radially 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 number of pin grooves (2140) may correspond to the number of platforms (1312). One pin groove (2140) may be formed in one sealing member (2100), or multiple 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 in FIG. 5a, one pin groove (2140) can be formed, and when one sealing member (2100) seals one side of two platforms (1312) as in FIG. 5b, two pin grooves (2140) can be formed.

The sealing member (2100) may have 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 step 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 a vertical surface at a predetermined height. According to the 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) may further include a first arc-shaped groove (2121) formed to prevent stress concentration at an inner edge between the step portion (2120) and the sealing body (2110), and a first chamfered surface (2122) formed at the other edge of the step portion (2120).

The first arc-shaped groove (2121) can be formed in the form of a groove having 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 edge where two planes meet vertically, it is possible to prevent stress from being concentrated at that area.

The first chamfered surface (2122) may be formed at an angle of 40 to 50 degrees at the outer edge where the upper surface of the step portion (2120) and the inclined portion (2130) meet. The first chamfered surface (2122) prevents stress from being concentrated at the edge 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) may further include a second arc-shaped groove (1323a) formed on a concave edge of a step portion (1323) formed in a mounting groove (1325), and a second chamfered surface (1323b) formed on a convex edge of the step portion (1323).

The second arc-shaped groove (1323a) may be formed in the form of a groove having a predetermined radius of curvature at the inner edge where the vertical plane and the horizontal plane of the step portion (1323) meet in the mounting groove (1325) of the turbine rotor disk (1320). That is, by forming the second arc-shaped groove (1323a) at the inner edge where the two planes meet vertically, it is possible to prevent stress from being concentrated at that area. In addition, the first chamfered surface (2122) of the sealing member (2100) is positioned in front of the second arc-shaped groove (1323a), so that interference when the sealing member (2100) is tilted and inserted into the mounting groove (1325) by the second arc-shaped groove (1323a) can be minimized.

The second chamfered surface (1323b) can be formed at an angle of 40 to 50 degrees to the convex corner 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 since the first arc-shaped groove (2121) of the sealing member (2100) is positioned in front of the second chamfered surface (1323b), interference between them during disassembly and assembly can also be minimized.

Figure 10 is a perspective view showing a fixed pin (2200).

Referring to Fig. 10, the fixed pin (2200) may be formed in an overall cylindrical shape, and a chamfer may be formed at one edge. Specifically, the fixed 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 an outer diameter larger than that of the pin body (2210). The pin body (2210) and the pin head (2220) can be formed in a stepwise manner as one piece.

A cut portion (2240) may be formed on the entire pin body (2210) and the lower portion of a portion of the pin head (2220), into which a bending member (2300) is fitted. The cut portion (2240) may have a flat cut surface, and a step surface perpendicular to the cut surface may be formed on the lower portion of the middle portion of the pin head (2220). In addition, the cut portion (2240) may have a chamfer formed on the end portion of the pin body (2210).

The pin groove (2230) is formed to be connected to the cut portion (2240) and is formed to be stepped on the pin head (2220) so that the bending member (2300) can be in close contact with it. The pin groove (2230) is formed to be shallower than the cut portion (2240) and is formed to be stepped from the cut portion (2240). The cut portion (2240) continues flatly to the circumference of the fixed pin (2200) in the width direction, but the pin groove (2230) has a width smaller than the outer diameter of the pin head (2220) and is formed to be stepped from the circumference of the pin head (2220) to the bottom of the pin groove (2230).

The screw hole (2250) may be formed longitudinally on the side of the pin head (2220). The screw hole (2250) may be formed eccentrically opposite to the pin groove (2230) rather than at the center of the pin head (2220). The depth of the screw hole (2250) may be formed greater than the length of the pin head (2220). Since the screw hole (2250) has threads formed on the inner circumference, when disassembling the fixing pin (2200), the fixing pin (2200) can be easily separated from the through hole (1322) by fastening a bolt to the screw hole (2250) and pulling the bolt.

Fig. 11 is a perspective view illustrating a bending member (2300), and Fig. 12 is a perspective view illustrating a modified example of the bending member.

Referring to FIG. 11, a bending member (2300) is formed by bending a rectangular plate, and may include a horizontal portion (2310) that can be bent by plastic deformation, a stepped portion (2320) that is connected to the horizontal portion in a stepwise manner, and a vertical portion (2330) that is bent vertically from the stepped portion.

The bending member (2300) can be formed by bending a rectangular metal plate having a predetermined width, length, and thickness. The bending member (2300) may be formed of a material that can easily be bent by plastic deformation throughout the plate, or may be formed of a material that can be bent by plastic deformation only in the horizontal portion (2310) where 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 and placed in the pin groove (2230) of the fixed pin (2200).

The step portion (2320) may be formed by bending upward from one end of the horizontal portion (2310) and then bending horizontally again. Referring to Fig. 6, the step portion (2320) may be positioned 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 from one end of the step portion (2320). The vertical portion (2330) may be formed to be at least twice as long as the step height of the step portion (2320). The vertical portion (2330) may be in close contact with the inner surface of the mounting rib (1321) to fix the bending member (2300) so that it does not fall out.

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

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

Next, an assembly process of a turbine blade sealing assembly according to an embodiment of the present invention will be described with reference to FIGS. 13 to 15. FIGS. 13 to 15 are drawings illustrating an assembly process of a 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 into the slot (1321) of the turbine rotor disk (1320) and mounted.

Next, as illustrated in FIG. 7, a 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) can be inserted into the mounting groove (1325).

Next, as illustrated in Fig. 13, the bending member (2300) is inserted into the through hole (1322) formed in the mounting rib (1321) and mounted. 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 so as to be seated in the through hole (1322).

Next, as illustrated in FIGS. 13 and 14, the fixing pin (2200) is inserted into the through hole (1322) of the mounting rib (1321) and the pin groove (2140) formed in the sealing member (2100) to be mounted. At this time, the fixed pin (2200) may be inserted so that the step between the pin body (2210) and the pin head (2220) is in close contact with and supported by the step between the through hole (1322) and the head receiving portion (1322a). In addition, the fixed pin (2200) may be mounted so that the step (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 fixed pin (2200).

Next, as illustrated in FIG. 14, the portion protruding outward from the mounting rib (1321) of the bending member (2300) is bent to support the fixing pin (2200). That is, the bending portion (2350) formed by vertically bending the protruding end of the horizontal portion (2310) of the bending member (2300) can be brought into close contact with the pin head (2220) of the fixing pin (2200) to support the fixing pin (2200).

As illustrated in Fig. 15, a bent portion (2350) formed by bending a portion of a horizontal portion (2310) can be placed inside a through hole (1322) of a 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 friction between the protrusion and the gas.

Above, one embodiment of the present invention has been described, but a person having ordinary skill in the art will be able to modify and change the present invention in various ways by adding, changing, deleting or adding components, etc., within the scope that does not depart from the spirit of the present invention described in the claims, and this will also be considered to be included within the scope of the 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: Single jaw
2130: Slope 2140: Pin groove
2200: Fixed pin
2210: Pin body 2220: Pin head
2230: Pin groove 2240: Cutout
2250: Screw hole
2300: Bending member
2310: Horizontal section 2320: Step section
2330: Vertical section 2340: Insertion projection
2350: Bend section

Claims (20)

A sealing member that seals one side of at least two adjacently formed platforms and one side of a turbine rotor disk on which a root member formed at the bottom of each of the two or more platforms is mounted;
A fixing pin inserted into the lower side of the turbine rotor disk to fix the sealing member to the turbine rotor disk; and
A bending member inserted together with the above fixed pin to prevent the above fixed pin from coming off;
The turbine rotor disk is formed on one axial side and includes a mounting groove into which a radially inner end of the sealing member is inserted and a mounting rib extending radially from one axial side,
The sealing member is supported radially by a horizontal surface of a step portion formed in the mounting groove and a step portion formed horizontally, and includes a sloped portion whose thickness gradually becomes thinner as it goes from the end of the step portion to the radially inner end, and whose lower end is formed to have a thickness smaller than the thickness of the sealing body formed on the step portion.
A turbine blade sealing assembly characterized by:
delete In claim 1, 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 above mounting rib.
In claim 3,
A turbine blade sealing assembly, wherein the above pin grooves are formed in a number corresponding to the number of the above platforms.
delete In claim 1, the sealing member,
A first arc-shaped groove formed to prevent stress concentration at the inner edge between the above-mentioned step portion and the sealing body,
A first chamfered surface formed on the other side edge of the above-mentioned short-cut portion
A turbine blade sealing assembly comprising:
In claim 6, the turbine rotor disk,
A second arc-shaped groove formed on the concave corner of the step formed in the above mounting groove,
A second chamfered surface formed on the convex corner of the above-mentioned step portion
A turbine blade sealing assembly comprising:
In claim 1, the fixed pin,
With a fin body,
A pin head formed on one side of the pin body and having an outer diameter larger than the pin body,
A cut portion formed on the lower part of the pin body and a part of the pin head, to which the bending member is in close contact;
A pin groove formed to be connected to the above-mentioned cut portion and formed to be stepped on the pin head so that the bending member is in close contact with it,
A screw hole formed longitudinally on the side of the above pin head
A turbine blade sealing assembly comprising:
In claim 8, the fixed pin,
A turbine blade sealing assembly formed in a number corresponding to the number of the above platforms.
In claim 8, the bending member,
A horizontal portion formed by bending a rectangular plate and capable of being bent by plastic deformation,
A step portion connected stepwise from the above horizontal portion,
A vertical portion vertically bent in the above step portion,
A bent portion formed by bending a portion of the above horizontal portion and supporting the pin head of the above fixed pin
A turbine blade sealing assembly comprising:
A compressor that sucks in outside air and compresses it;
A combustor that mixes fuel with the compressed air from 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;
, and the turbine blade sealing assembly comprises:
A sealing member that seals one side of at least two adjacently formed platforms and one side of a turbine rotor disk on which a root member formed at the bottom of each of the two or more platforms is mounted;
A fixing pin inserted into the lower side of the turbine rotor disk to fix the sealing member to the turbine rotor disk; and
A bending member inserted together with the above fixed pin to prevent the above fixed pin from coming off;
The turbine rotor disk is formed on one axial side and includes a mounting groove into which a radially inner end of the sealing member is inserted and a mounting rib extending radially from one axial side,
The sealing member is supported radially by a horizontal surface of a step portion formed in the mounting groove and a step portion formed horizontally, and includes a sloped portion whose thickness gradually becomes thinner as it goes from the end of the step portion to the radially inner end, and whose lower end is formed to have a thickness smaller than the thickness of the sealing body formed on the step portion.
A gas turbine characterized by:
delete In claim 11, 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 above mounting rib.
In claim 13,
A gas turbine, wherein the above pin grooves are formed in a number corresponding to the number of the above platforms.
delete In claim 11, the sealing member,
A first arc-shaped groove formed to prevent stress concentration at the inner edge between the above-mentioned step portion and the sealing body,
A first chamfered surface formed on the other side edge of the above-mentioned short-cut portion
A gas turbine, including:
In claim 16, the turbine rotor disk,
A second arc-shaped groove formed on the concave corner of the step formed in the above mounting groove,
A second chamfered surface formed on the convex corner of the above-mentioned step portion
A gas turbine, including:
In claim 11, the fixed pin,
With a fin body,
A pin head formed on one side of the pin body and having an outer diameter larger than the pin body,
A cut portion formed on the lower part of the pin body and a part of the pin head, to which the bending member is in close contact;
A pin groove formed to be connected to the above-mentioned cut portion and formed to be stepped on the pin head so that the bending member is in close contact with it,
A screw hole formed longitudinally on the side of the above pin head
A gas turbine, including:
In claim 18, the fixed pin,
A gas turbine formed in a number corresponding to the number of the above platforms.
In claim 18, the bending member is,
A horizontal portion formed by bending a rectangular plate and capable of being bent by plastic deformation,
A step portion connected stepwise from the above horizontal portion,
A vertical portion vertically bent in the above step portion,
A bent portion formed by bending a portion of the above horizontal portion and supporting the pin head of the above fixed pin
A gas turbine, including: