KR102348487B1 - Turbine blade and gas turbine comprising the same - Google Patents

Abstract

The turbine blade of the present invention includes a flat platform portion, a root portion formed radially inwardly from the platform portion, an airfoil-type blade portion formed radially outward from the platform portion and having a pressure surface and a suction surface, and It includes a pair of weights inserted and mounted in a pair of mounting grooves formed on the pressure side and the suction side on the radial inner surface of the platform unit.

Description

Turbine blade and gas turbine comprising the same

The present invention relates to a turbine blade capable of balancing asymmetry of contact loads applied to both sides of a root portion by mounting a pair of weights on a platform portion of the turbine blade, and a gas turbine including the same.

A turbine is a mechanical device that uses the flow of a compressive fluid such as steam or gas to obtain rotational force by impulse or reaction force, and includes a steam turbine using steam and a gas turbine using high temperature combustion gas.

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

The combustor supplies fuel to the compressed air compressed by the compressor and ignites it with a burner to generate high-temperature and high-pressure combustion gas.

The turbine has a plurality of turbine vanes and turbine blades are alternately arranged in a turbine housing. In addition, the rotor is disposed so as to penetrate the compressor, the combustor, the turbine, and the central portion of the exhaust chamber.

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

Since these gas turbines do not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction part such as a piston-cylinder, so the consumption of lubricant is extremely low. There are advantages.

Briefly describing the operation of the gas turbine, the air compressed in the compressor is mixed with fuel and combusted to produce a high-temperature combustion gas, and the combustion gas thus produced is injected toward the turbine. As the injected combustion gas passes through the turbine vanes and turbine blades, a rotational force is generated, thereby rotating the rotor.

The turbine blade is made in the form of an airfoil including a suction surface and a pressure surface, a fir-shaped root portion is provided inside the platform portion, and is inserted and mounted in a coupling slot formed in the turbine rotor disk.

However, since the center of gravity of the airfoil of the turbine blade is not constant, the load applied to both sides of the root part during the manufacturing process or the operation process, that is, the contact force may be asymmetrically generated. The contact force of the asymmetric root part acts as a large load on the disk slot surface, and asymmetric deformation may occur.

Conventionally, the asymmetric load was solved by designing the airfoil of the turbine blade in a shape inclined at a predetermined angle. However, the balancing method by the design design change of the airfoil has a problem in that efficiency is bad because balancing must be solved in the design stage. In addition, unbalance occurring in the operation process rather than the manufacturing process of the turbine blade has a problem that cannot be solved.

Laid-Open Patent Publication No. 10-2001-0050226

An object of the present invention is to provide a turbine blade capable of easily balancing asymmetry of contact loads applied to both sides of a root portion by mounting a pair of weights on a platform portion of the turbine blade, and a gas turbine including the same.

The turbine blade of the present invention for achieving the above object is a flat platform portion, a root portion formed radially inwardly from the platform portion, an air formed radially outwardly from the platform portion and having a pressure surface and a suction surface It includes a blade part in the form of a foil, and a pair of weights inserted into a pair of mounting grooves formed on the pressure side and the suction side on the radial inner surface of the platform part and mounted.

A pair of weights may be selected from a plurality of weights having different weights to solve the asymmetry of the load applied to the pressure side and suction side contact surfaces of the root part, and weights having a predetermined weight may be mounted in each mounting groove. .

The plurality of weights may be made of materials having different densities.

The plurality of weights may have different sizes.

The weight may have a rectangular parallelepiped shape.

The weight may be welded or brazed to the mounting groove.

The weight may be detachably mounted in the mounting groove.

The mounting groove is formed to be larger than the weight, and the weight can be mounted by adjusting the position in the circumferential direction in the mounting groove.

A gas turbine according to the present invention includes a compressor for compressing air, a combustor mixing compressed air introduced from the compressor with fuel and combusting it, and a plurality of turbine blades rotating by the combusted gas to generate power Including a turbine, the turbine blade includes a flat platform portion, a root portion formed radially inwardly from the platform portion, and an airfoil-type blade portion formed radially outwardly from the platform portion and having a pressure surface and a suction surface. , and a pair of weights inserted and mounted in a pair of mounting grooves formed on the pressure side and the suction side on the radial inner surface of the platform unit.

A pair of weights may be selected from a plurality of weights having different weights to solve the asymmetry of the load applied to the pressure side and suction side contact surfaces of the root part, and weights having a predetermined weight may be mounted in each mounting groove. .

The plurality of weights may be made of materials having different densities.

The plurality of weights may have different sizes.

The weight may have a rectangular parallelepiped shape.

The weight may be welded or brazed to the mounting groove.

The weight may be detachably mounted in the mounting groove.

The mounting groove is formed to be larger than the weight, and the weight can be mounted by adjusting the position in the circumferential direction in the mounting groove.

According to the turbine blade of the present invention and the gas turbine including the same, by mounting a pair of weights on the platform portion of the turbine blade, it is possible to easily balance the asymmetry of the contact load applied to both sides of the root portion.

1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention.
2 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.
3 is an exploded perspective view showing a turbine rotor disk and a turbine blade;
4 is a cross-sectional view schematically showing a turbine blade according to a first embodiment of the present invention.
5 is an enlarged view illustrating a platform unit in the turbine blade of FIG. 4 .
6 is a partial perspective view illustrating the mounting of the weight in the mounting groove formed on the radial inner surface of the turbine blade platform part.
7 is a cross-sectional view schematically showing a turbine blade according to a second embodiment of the present invention.
8 is a cross-sectional view schematically showing a turbine blade according to a third embodiment of the present invention.

Since the present invention can apply various transformations and can have various 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, and should be understood to include all modifications, equivalents, and substitutes included in the spirit and 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. The singular expression includes the plural expression unless the context clearly dictates otherwise. In the present invention, terms such as 'comprising' or 'having' are intended to designate that the features, numbers, steps, operations, components, parts, or combinations thereof described in the specification exist, and one or more other features It should be understood that this does not preclude the existence or addition of numbers, steps, operations, components, parts, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this case, it should be noted that in the accompanying drawings, the same components are denoted by the same reference numerals as much as possible. In addition, 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 illustrated in the accompanying drawings.

1 is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention, 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 the turbine rotor disk of FIG. is an exploded perspective view showing

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 moves while the air is 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 , and may receive a portion of the power generated from the turbine 1300 and use it to rotate the blade 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 includes a housing 1010 , and a diffuser 1400 through which combustion gas passing through the turbine is discharged at the rear side of the housing 1010 . ) is provided. In addition, a combustor 1200 for receiving and burning compressed air in front of the diffuser 1400 is disposed.

Referring to the flow direction of the air, the compressor section 1100 is positioned on the upstream side of the housing 1010 , and the turbine section 1300 is disposed on the downstream side. And, between the compressor section 1100 and the turbine section 1300, the torque tube unit 1500 as a torque transmitting member for transmitting the rotational torque generated in the turbine section 1300 to the compressor section 1100 is disposed.

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

Specifically, each of the compressor rotor disks 1120 is aligned along the axial direction with the tie rods 1600 constituting the rotation shaft passing through the center. Here, each of the adjacent compressor rotor disks 1120 is arranged such that the opposite surfaces are compressed by the tie rods 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 positioned between each rotor disk 1120 . Unlike the rotor disk, the vane is fixed not to rotate, and serves to align the flow of compressed air passing through the blades of the rotor disk of the compressor and guide the air to the blades of the rotor disk located on the downstream side.

A fastening method of the dovetail part 1112 includes a tangential type and an axial type. This may be selected according to the required structure of a commercially available 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 fastener other than the above type, for example, a key or a fastener such as a bolt.

The tie rods 1600 are disposed to penetrate the central portions of the plurality of compressor rotor disks 1120 and the turbine rotor disks 1320 , and the tie rods 1600 may include one or a plurality of tie rods. One end of the tie rod 1600 is fastened in the compressor rotor disk located at the most upstream side, and the other end of the tie rod 1600 is fastened by a fixing nut 1450 .

Since the shape of the tie rod 1600 may have various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 2 . That is, as shown, one tie rod may have a shape penetrating the central portion of the rotor disk, or a plurality of tie rods may have a shape arranged in a circumferential shape, and a mixture thereof is also possible.

Although not shown, in the compressor of the gas turbine, a vane serving as a guide vane may be installed at a position next to the diffuser in order to adjust the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the pressure of the fluid. and this is called a deswirler.

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

A plurality of combustors constituting the combustion system of the gas turbine may be arranged in a housing formed in a cell shape, and a burner including a fuel injection nozzle and the like, a combustor liner forming a combustion chamber, and a combustor And it is configured to include a transition piece (Transition Piece) that becomes the connection part of the turbine.

Specifically, the liner provides a combustion space in which the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and combusted. Such a 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 barrel and forms an annular space. In addition, the fuel nozzle is coupled to the front end of the liner, and the spark plug is coupled to the side wall.

On the other hand, a transition piece is connected to the rear end of the liner so that the combustion gas combusted by the spark plug can be sent to the turbine side. The transition piece is cooled by the compressed air supplied from the compressor so as to prevent damage caused by the high temperature of the combustion gas.

To this end, holes for cooling are provided in the transition piece to inject air into the transition piece, and compressed air flows to the liner side after cooling the body inside through the holes.

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

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor is supplied to the above-described turbine 1300 . The supplied high-temperature and high-pressure combustion gas expands and collides with the rotor blades of the turbine, giving a reaction force to generate rotational torque. The power is used to drive a generator, etc.

The turbine 1300 is basically similar to the structure of 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 radially disposed turbine blades 1340 . The turbine blade 1340 may also be coupled to the turbine rotor disk 1320 in a dovetail or the like manner. In addition, a turbine vane (not shown) fixed to the housing is provided between the blades 1340 of the turbine rotor disk 1320 to guide the flow direction of the combustion gas passing through the blades.

Referring to FIG. 3 , the turbine rotor disk 1320 has a substantially disk shape, and a plurality of coupling slots 1322 are formed on its outer periphery. The coupling slot 1322 is formed to have a curved surface in the shape of a fir-tree.

The turbine blade 1340 or 100 is fastened to the coupling slot 1322 . In FIG. 3 , the turbine blade 100 has a platform portion 110 in the form of a flat plate at an approximately central portion. The platform unit 110 serves to maintain a gap between the platform unit 110 and the side surface of the adjacent turbine blade in contact with each other.

A root portion 120 is formed on the bottom surface of the platform portion 110 . The root portion 120 is inserted in the coupling slot 1322 of the above-described rotor disk 1320 in the axial direction of the rotor disk 1320, and has an axial-type shape.

The root portion 120 has an approximately fir-shaped bent portion, which is formed to correspond to the shape of the bent portion formed in the coupling slot. Here, the coupling structure of the root does not necessarily have a fir tree shape, and may be formed to have a dovetail shape.

A blade unit 130 is formed on the upper surface of the platform unit 110 . The blade unit 130 is formed to have an airfoil optimized according to the specifications of the gas turbine, and has a leading edge disposed on the upstream side and a trailing edge disposed on the downstream side based on the flow direction of the combustion gas.

Here, unlike the blades of the compressor, the blades of the turbine come into direct contact with the high-temperature and high-pressure combustion gas. Since the temperature of the combustion gas is high enough to reach 1700°C, a cooling means is required. To this end, it has a cooling flow path for extracting compressed air from a part of the compressor and supplying it to the turbine-side blade.

The cooling passage may extend outside the housing (outer passage) or through the inside of the rotor disk (inner passage), and both external and inner passages may be used. In FIG. 3 , a plurality of film cooling holes 1344 are formed on the surface of the blade unit, and the film cooling holes 1344 communicate with a cooling passage (not shown) formed inside the blade unit 130 to supply cooling air to the blade. It serves to supply the surface of the part 130 .

On the other hand, the blade part 130 of the turbine is rotated by combustion gas inside the housing, and a gap exists between the end of the blade part 130 and the inner surface of the housing so that the blade part can rotate smoothly. However, since the combustion gas may leak through the gap as described above, a sealing means for blocking this is required.

4 is a cross-sectional view schematically showing a turbine blade according to a first embodiment of the present invention, FIG. 5 is an enlarged view showing a platform part in the turbine blade of FIG. 4, and FIG. 6 is a turbine blade formed on the radial inner surface of the platform part It is a partial perspective view showing the mounting of the weight in the mounting groove.

The turbine blade 100 according to the first embodiment of the present invention includes a flat platform portion 110 , a root portion 120 formed radially inwardly from the platform portion, and radially outwardly formed from the platform portion, and the pressure As long as it is inserted and mounted into the airfoil-shaped blade part 130 having a surface 131 and a suction surface 132, and a pair of mounting grooves 140 formed on the pressure side and the suction side on the radial inner surface of the platform part It includes a pair of weights 150 .

As described above, the platform unit 110 may be formed in the form of a flat plate as a whole at a central portion of the turbine blade 100 in a radial direction. The platform unit 110 may have the platform unit 110 and the side surface of the neighboring turbine blades in contact with each other in the circumferential direction to maintain a gap between the blades.

The root portion 120 is inserted in the axial direction of the rotor disk 1320 into the coupling slot 1322 formed to have a substantially fir-shaped bent portion of the above-described rotor disk 1320, in the form of an axial-type. have The root portion 120 may have a substantially fir-shaped bent portion corresponding to the coupling slot 1322 of the rotor disk 1320 .

The blade unit 130 is formed in the form of an airfoil on the upper surface of the platform unit 110 , that is, on the radial outer surface. The blade unit 130 is formed to have an airfoil optimized according to the specifications of the gas turbine, and has a leading edge disposed on the upstream side and a trailing edge disposed on the downstream side based on the flow direction of the combustion gas. The side between the leading edge and the trailing edge may have a concave pressure surface 131 and a convex suction surface 132 .

The pair of mounting grooves 140 may be formed on the pressure side and the suction side of the root part 120 on the radial inner surface of the platform part 110 .

The pair of weights 150 may be inserted into the pair of mounting grooves 140 to be mounted. After the weight 150 is inserted into the mounting groove 140, its surface is formed to coincide with the radial inner surface of the platform unit 110, so that when the root unit 120 is inserted into the coupling slot 1322, the rotor disk ( It is supported by the outer peripheral surface of the 1320, it is possible to prevent the weight 150 from being separated.

A pair of weights 150 is selected from a plurality of weights having different weights in order to solve the asymmetry of the load applied to the pressure side and suction side contact surfaces of the root part 120, and a predetermined weight is placed in each mounting groove. A weight 150 with may be mounted.

For example, it is possible to prepare a plurality of weights 150 that increase step by step by 10g. When the center of gravity of the turbine blade 100 is located at the center in the circumferential direction, the two weights 150 may be mounted with the same weight.

When the center of gravity of the turbine blade 100 is located at a point skewed to one side from the center in the circumferential direction, the two weights 150 are mounted with different weights, thereby balancing the center of gravity of the turbine blade 100 in the circumferential direction. can do. As will be described later, whether the circumferential symmetry according to the center of gravity of the turbine blade 100 may be balanced by adjusting the contact load acting on the side of the root part 120 to be symmetrical.

As shown in FIG. 4 , the root portion 120 may have a shape having three mountains and three valleys on a substantially circumferential side surface. Contrary to this, the number of mountains and valleys may be formed differently from 2 to 6.

A contact load is applied to each mount by the coupling slot 1322 of the rotor disk 1320 on the pressure side and the suction side. The contact force received by each acid on the pressure side is F _P1 , F _P2 , and F _P3 , respectively, and the contact force received by each acid on the suction side is F _S1 , F _S2 , F _S3 . In addition, the mass of the weight 150 mounted on the pressure side may be _{referred to as M PS} , and the mass of the weight 150 mounted on the suction side may be referred to _{as M SS .}

When the contact force on the suction side (F _S1 , F _S2 , F _S3 ) is larger than the contact force on the pressure side (F _P1 , F _P2 , F _{P3 ), the mass (MPS} ) of the weight 150 on the pressure side is By mounting a weight larger than the mass 150 mass ( _MSS ), the contact force on both sides can be made the same.

Conversely, when the contact force on the pressure side (F _P1 , F _P2 , F _P3 ) is greater than the contact force on the suction side (F _S1 , F _S2 , F _{S3 ), the mass (MSS} ) of the weight 150 on the suction side is the pressure by mounting is larger than the weight 150, the mass (M _PS) of the same side can make the contact pressure of the two sides.

A plurality of weights 150 mounted for balancing may be made of materials having different densities. That is, even though they have the same size and shape, materials having different densities may constitute the weight 150 having different weights.

In addition, a plurality of weights 150 mounted for balancing may be prepared in different sizes in stages. That is, if made of the same material but different in size, weights 150 having different weights may be configured.

As shown in FIG. 6 , the weight 150 may be formed to have a substantially rectangular parallelepiped shape. The mounting groove 140 of the platform unit 110 may also be formed in a rectangular parallelepiped groove shape corresponding to the shape of the weight 150 . At least four sides of the rectangular parallelepiped are chamfered or formed to be rounded, thereby reducing the concentration of stress on the edge of the mounting groove 140 compared to the right-angled edge.

If the weight 150 and the mounting groove 140 are formed in a rectangular parallelepiped shape, it is easy to manufacture, and it is easy to form various sizes by changing the length or thickness of the long side or the short side.

The weight 150 may be coupled to the mounting groove 140 by welding or brazing. Brazing is a technology for joining by heating the base material below the solidus temperature, melting only the brazing alloy with a melting point of 450°C or higher, and then penetrating and diffusing between the two base materials to be joined using the wetting phenomenon and capillary phenomenon. In welding, since both the base material and the joint are heated to a melting temperature or higher to perform fusion bonding, thermal deformation such as distortion or bulging due to thermal stress may occur. In contrast, brazing has little deformation or residual stress of the base material and is easy to work, so that the weight 150 can be joined to the mounting groove 140 with better quality than welding.

7 is a cross-sectional view schematically showing a turbine blade according to a second embodiment of the present invention.

As shown in FIG. 7 , the weight 150 may be detachably mounted to the mounting groove 140 . To this end, the weight 150 may be mounted by being fastened to the mounting groove 140 by a screw 160 . To this end, at least one screw fastening hole is formed through the weight 150 , and a fastening groove may also be formed in the platform unit 110 . It is preferable that the head of the screw 160 is completely embedded in the fastening hole of the weight 150, or a screw of a headless type is used. Thus, it is possible to prevent the screw 160 from protruding from the surface of the weight 150 to interfere with the rotor disk 1320 .

Even when the gas turbine is operated after balancing by mounting the weight 150 in the mounting groove 140, it is deformed or worn under the load by the high-temperature and high-pressure combustion gas during operation so that the turbine blade 100 becomes asymmetric in the circumferential direction. There may be cases. If the weight 150 is detachable from the mounting groove 140 , the weight 150 mounted in the mounting groove 140 may be replaced with a different weight for balancing again.

8 is a cross-sectional view schematically showing a turbine blade according to a third embodiment of the present invention.

In the case of the third embodiment, the mounting groove 140 is formed to be larger than the weight 150 , and the weight 150 may be mounted by adjusting the position in the circumferential direction in the mounting groove 140 .

In Figure 8 (a), the pressure side weight (150P) is mounted so as to be in close contact with the left end in the mounting groove (140), the suction side weight (150S) is mounted so as to be in close contact with the left end in the mounting groove (140) have. This arrangement is for balancing the contact forces on both sides so that when the contact forces on the suction side (F _S1 , F _S2 , F _S3 ) are greater than the contact forces on the pressure side (F _P1 , F _P2 , F _{P3 ), the contact forces on both sides are the same.}

In Figure 8 (b), the pressure side weight (150P) is mounted to be in close contact with the right end in the mounting groove (140), the suction side weight (150S) is mounted so as to be in close contact with the right end in the mounting groove (140) have. This arrangement is for balancing so that the contact forces on both sides are equal when the contact forces F _P1 , F _P2 , F _P3 on the pressure side are greater than the contact forces on the suction side ( F _S1 , F _S2 , F _{S3 ).}

According to the difference between the pressure side contact force (F _P1 , F _P2 , F _P3 ) and the suction side contact force (F _S1 , F _S2 , F _S3 ), the weights 150P, 150S are located at the left end of the mounting groove 140 and It can be mounted to be placed at any point between the right ends. Accordingly, it is possible to easily balance the asymmetry of the contact load of the turbine blades by adjusting only the mounting positions of the weights on both sides.

On the other hand, even when the weight 150 is fastened to the mounting groove 140 by the screw 160 , the mounting position of the weight 150 may be moved. For example, if the fastening hole of the weight 150 is formed in the form of a long long hole in the circumferential direction, the position of the weight 150 may be moved to be fastened with the screw 160 .

As described above, one embodiment of the present invention has been described, but those of ordinary skill in the art can add, change, delete or add components within the scope that does not depart from the spirit of the present invention described in the claims. Various modifications and changes of the present invention will be possible by this, and this will also be included within the scope of the present invention.

1000: gas turbine 1010: housing
1100: compressor 1110: compressor blade
1112: dovetail part 1120: compressor rotor disk unit
1130: compressor cooling air supply flow path 1200: combustor
1300: turbine 1320: turbine rotor disk
1330: turbine vanes 1340: turbine blades
1400: diffuser 1450: fixing nut
1500: torque tube unit 1600: tie rod
100: turbine blade 110: platform unit
120: root portion 130: blade portion
131: pressure side 132: suction side
135: film cooling hole 140: mounting groove
150: weight 160: screw

Claims (16)

a flat platform unit;
a root portion formed radially inwardly from the platform portion;
an airfoil-shaped blade portion formed radially outward from the platform portion and having a pressure surface and a suction surface; and
and a pair of weights inserted and mounted in a pair of mounting grooves formed on the pressure side and the suction side on the radial inner surface of the platform part,
The pair of weights is selected from a plurality of weights having different weights in order to solve the asymmetry of the load applied to the pressure side and the suction side contact surface of the root part, and a weight having a predetermined weight is mounted in each mounting groove Turbine blades, characterized in that. delete According to claim 1,
The plurality of weights are turbine blades, characterized in that made of materials having different densities. According to claim 1,
Turbine blade, characterized in that the plurality of weights have different sizes. According to claim 1,
The weight is a turbine blade, characterized in that having a rectangular parallelepiped shape. According to claim 1,
The weight is a turbine blade, characterized in that welded or brazed to the mounting groove. According to claim 1,
The weight is a turbine blade, characterized in that detachably mounted in the mounting groove. 8. The method according to any one of claims 1, 3 to 7,
The mounting groove is formed to be larger than the weight, and the weight is mounted by adjusting a position in the circumferential direction in the mounting groove. a compressor for compressing air;
a combustor for mixing and burning the compressed air introduced from the compressor with fuel; and
A turbine comprising a plurality of turbine blades to generate power by rotating by the combustor gas,
The turbine blade is
a flat platform unit;
a root portion formed radially inwardly from the platform portion;
an airfoil-shaped blade portion formed radially outward from the platform portion and having a pressure surface and a suction surface; and
and a pair of weights inserted and mounted in a pair of mounting grooves formed on the pressure side and the suction side on the radial inner surface of the platform part,
The pair of weights is selected from a plurality of weights having different weights in order to solve the asymmetry of the load applied to the pressure side and the suction side contact surface of the root part, and a weight having a predetermined weight is mounted in each mounting groove Gas turbine, characterized in that. delete 10. The method of claim 9,
The plurality of weights is a gas turbine, characterized in that made of a material having a different density. 10. The method of claim 9,
A gas turbine, characterized in that the plurality of weights have different sizes. 10. The method of claim 9,
The weight is a gas turbine, characterized in that having a rectangular parallelepiped shape. 10. The method of claim 9,
The weight is a gas turbine, characterized in that welded or brazed to the mounting groove. 10. The method of claim 9,
The gas turbine, characterized in that the weight is detachably mounted in the mounting groove. 16. The method according to any one of claims 9, 11 to 15,
The mounting groove is formed to be larger than the weight, and the weight is mounted by adjusting a position in the circumferential direction in the mounting groove.

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