KR102405750B1 - rotor and turbo-machine comprising the same - Google Patents

Abstract

The present invention, a disk having a disk slot; a blade inserted into the disk slot and including a root member for forming a cooling cavity between an inner portion of the disk slot with respect to the radial direction of the disk, and an air foil disposed on the radially outer side of the root member; and a rotor coupled to the disk and installed on the radially inner side of the root member and including a lifting part for pressing the root member outward, and a turbomachine including the same.

Description

Rotor and turbo-machine comprising the same

The present invention relates to a rotor and a turbomachine including the same, and more particularly, to a rotor generating power for power generation and a turbomachine including the same.

A turbomachine refers to a device that generates power for power generation through a fluid (particularly, gas) passing through the turbomachine. Therefore, the turbomachine is usually installed and used together with the generator. The turbomachine may include a gas turbine, a steam turbine, a wind power turbine, and the like. A gas turbine is a device for generating combustion gas by mixing compressed air and natural gas, and generating power for power generation using the generated combustion gas. A steam turbine is a device that generates power for power generation using steam generated by heating water. A wind turbine is a device that converts wind power into power for power generation.

Looking at a gas turbine among turbomachines, the gas turbine includes a compressor, a combustor, and a turbine. In the compressor, a plurality of compressor vanes and compressor blades are alternately arranged in a compressor casing. And the compressor sucks in the outside air through the compressor inlet scroll strut. The sucked air is compressed by the compressor vanes and the compressor blades while passing through the inside of the compressor. The combustor receives compressed air compressed from the compressor and mixes it with fuel. In addition, the combustor ignites fuel mixed with compressed air with an igniter to generate high-temperature and high-pressure combustion gas. The combustion gas thus generated is supplied to the turbine. In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a turbine casing. And the turbine receives the combustion gas generated in the combustor and passes it inside. The combustion gas passing through the inside of the turbine rotates the turbine blades, and the combustion gas completely passing through the inside of the turbine is discharged to the outside through the turbine diffuser.

Looking at a steam turbine among turbomachines, the steam turbine includes an evaporator and a turbine. The evaporator generates steam by heating water supplied from the outside. In the turbine, a plurality of turbine vanes and turbine blades are alternately disposed in a turbine casing, similarly to a turbine in a gas turbine. However, the turbine in the steam turbine passes the steam generated in the evaporator, not the combustion gas, to the inside, thereby rotating the turbine blades.

More specifically, the turbine includes a turbine disk and turbine blades. The turbine disk is formed in the shape of a disk, and a plurality of turbine disk slots are formed on an outer circumferential surface of the turbine disk in the circumferential direction. The turbine blade is installed in the turbine disk slot, and includes a root member, a platform, and an airfoil. The root member is inserted into the turbine disk slot. The platform is coupled to the radially outer side of the root member. The airfoil is coupled to the radially outer side of the platform and is rotated by a flowing gas (combustion gas or steam). The turbine disk slot may have an inner wall formed in a curved shape (eg, a Fir-tree shape), and the root member may also have a curved outer surface corresponding to the inner wall shape of the turbine disk slot.

On the other hand, a gap is formed between the root member and the turbine disk slot. This gap is intended to improve the assembly of the root member and the turbine disk, and also takes into account thermal expansion of each component during operation of the turbomachine.

During the operation of the turbomachine, the blades come into close contact with the disk by centrifugal force, so there is no movement between the disk and the blade. A gap is created between the disks, resulting in relative movement between the blades and the disks. Therefore, in order to prevent relative movement between the blade and the disk, the turbomachine is provided with a separate adhesion structure for attaching the blade to the disk. As the adhesion structure, a wedge structure and a root spring mounted between the blade and the disk are used, but the adhesion structure such as the wedge structure and the root spring blocks the cooling air inflow space.

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Registered Patent No. 10-2042505 Turbine rotor and steam turbine including the same (2019. 11. 08 Announcement)

The present invention is to solve the above problems, and to provide a rotor capable of securing an inflow space for cooling air to a disk while keeping a blade and a disk in close contact with each other during operation of the turbomachine and a turbomachine including the same .

The present invention, a disk having a disk slot; a blade inserted into the disk slot and including a root member for forming a cooling cavity between an inner portion of the disk slot with respect to the radial direction of the disk, and an air foil disposed on the radially outer side of the root member; And it is coupled to the disk, it provides a rotor comprising a lifting portion installed on the radially inner side of the root member to press the root member outward.

In addition, the present invention, a stator for guiding the fluid passing therein; and a rotor installed inside the stator and rotated by the fluid passing into the stator, wherein the rotor includes a disk having a disk slot formed therein, and being inserted into the disk slot in a radial direction of the disk. A root member for forming a cooling cavity between an inner portion of the disk slot as a reference, a blade including an airfoil disposed radially outside of the root member, coupled to the disk, the radius of the root member It provides a turbomachine including a lifting part installed inside the direction to press the root member outward.

The lifting unit may be disposed between the cooling cavity and the inner end of the root member.

The disk may have a first seating groove formed on a surface opposite to the disk of an adjacent stage, and the lifting unit may be installed in the first seating groove.

The first seating groove is disposed between the cooling cavity and the inner end of the root member with respect to the radial direction of the disk, and may be formed in a shape extending in the circumferential direction of the disk.

At the inner end of the root member, a second seating groove is formed on a surface opposite to the disk of an adjacent stage and connected to the first seating groove, and the lifting part includes the first seating groove and the second seating groove. 2 It can be installed in the seating groove.

A radially outer portion of the inner wall of the second seating groove protrudes more inward than a radially outer portion of the inner wall of the first seating groove, and the lifting unit includes a first lifting member installed in the first seating groove and , a second lifting installed in the first and second seating grooves, adjacent to the first lifting member, and radially outwardly pressing the inner wall of the second seating groove as installed in the second seating groove member may be included.

The first lifting member may have a first protrusion protruding toward the second lifting member, and the second lifting member may have a second protrusion protruding toward the first lifting member and contacting the first protrusion.

The second protrusion may be disposed between the first protrusion and an inner wall of the first seating groove.

The disk may further include a penetrating member having a through hole formed therein, and the lifting unit being coupled to the first lifting member and inserted into the through hole.

The penetrating member may be coupled to the radially outer side of the first lifting member, and may be formed in a hollow shape.

According to the rotor and turbomachine including the same according to the present invention, the disk slot formed in the disk is divided into a curved cavity and a cooling cavity existing below the curved cavity, and the root member of the blade is inserted into the curved cavity, and lifting By pressing the root member of the blade radially outwardly between the curved cavity and the cooling cavity, the root member of the blade and the disk can be brought into close contact with each other during operation of the turbomachine, and at the same time, from the outside through the cooling cavity to the inside of the disk Cooling air can be introduced.
In addition, in the present invention, even if the rotor rotates at a high speed and a temperature rise due to a high-temperature fluid and thermal expansion occur accordingly, there is an allowance space between the first lifting member and the second lifting member in consideration of thermal expansion, so damage due to thermal expansion occurs. has the effect of not doing it.
In addition, in the present invention, since the plurality of penetrating members fixed to the disk are connected to the first lifting member and the second lifting member, they are not easily damaged by vibration.

1 is a view showing a gas turbine among turbomachines.
2 is a perspective view of a turbine rotor according to an embodiment of the present invention.
3 is an enlarged view of FIG. 2 .
Fig. 4 is a perspective view of the disk of Fig. 2;
5 is a view showing a state in which the root member of the blade is inserted into the disk slot of the disk of FIG.
6 is a perspective view of a lifting unit according to an embodiment of the present invention.

Although the present invention has been described with reference to the embodiment shown in the drawings, which is merely exemplary, it will be understood by those skilled in the art that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true technical protection scope of the present invention should be determined by the technical spirit of the appended claims.

Hereinafter, a rotor according to the present invention and a turbomachine including the same will be described with reference to the drawings. At this time, the description will be made assuming that the turbomachine according to the present invention is a gas turbine, but this is only an example, and it will be understood that the turbomachine according to the present invention may correspond to a steam turbine rather than a gas turbine.

Referring to FIG. 1 , a gas turbine 10 according to an embodiment of the present invention includes a compressor 11 , a combustor 12 , and a turbine 13 . Based on the flow direction of the gas (compressed air or combustion gas), the compressor 11 is disposed on the upstream side of the gas turbine 10 and the turbine 13 is disposed on the downstream side. And the combustor 12 is disposed between the compressor 11 and the turbine 13 .

The compressor 11 accommodates the compressor vane and the compressor rotor inside the compressor casing, and the turbine 13 accommodates the turbine vane 16 and the turbine rotor 100 inside the turbine casing 15 . The compressor vanes and the compressor rotor are arranged in multi-stage along the flow direction of the compressed air, and the turbine vane 16 and the turbine rotor 100 are also arranged in multiple stages along the flow direction of the combustion gas. At this time, in the compressor 11, the internal space decreases from the front-stage to the rear-stage side so that the sucked air can be compressed. It is designed in such a way that the inner space increases from the front end to the rear end.

On the other hand, between the compressor rotor located at the rearmost end of the compressor 11 and the turbine rotor 100 located at the most forward end of the turbine 13 , the rotational torque generated by the turbine 13 is transferred to the compressor 11 . A torque tube as a torque transmitting member for transmitting to the The torque tube may be composed of a plurality of torque tube disks consisting of a total of three stages as shown in FIG. 1, but this is only one of several embodiments of the present invention, and the torque tube has four or more stages or It may be composed of a plurality of torque tube disks consisting of two or less stages.

The compressor rotor includes a compressor disk and a compressor blade. A plurality (eg, 14 sheets) of compressor disks are provided inside the compressor casing, and each of the compressor disks is fastened by a tie rod so as not to be spaced apart from each other in the axial direction. More specifically, the respective compressor disks are aligned along the axial direction with each other with a central portion pierced by the tie rod. And, each of the compressor disks adjacent to each other are arranged so that the opposing surfaces are compressed by the tie rods so that they cannot rotate relative to each other.

A plurality of compressor blades are radially coupled to an outer circumferential surface of the compressor disk. In addition, between the compressor blades, a plurality of compressor vanes that are annularly installed on the inner circumferential surface of the compressor casing based on the same stage are respectively disposed. Unlike the compressor disk, the compressor vane maintains a fixed state so as not to rotate, aligns the flow of compressed air passing through the compressor blade, and guides the compressed air to the compressor blade located on the downstream side. In this case, in order to distinguish the compressor casing and the compressor vane from the compressor rotor, a generic name of a compressor stator may be defined.

The tie rod is disposed to pass through the center of the plurality of compressor disks and a turbine disk to be described later, one end is fastened in the compressor disk located at the most front end side of the compressor, and the other end is fastened by a fixing nut. do.

Since the shape of the tie rod may have various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 1 . That is, as shown, one tie rod may have a shape passing through the central portions of the compressor disk and the turbine 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, a deswirler serving as a guide blade may be installed in the compressor of the 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.

The combustor 12 mixes and combusts the introduced compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas, and the temperature of the combustion gas up to the heat resistance limit that the combustor and turbine parts can withstand through an isostatic combustion process. will be raised

A plurality of combustors constituting the combustion system of the gas turbine 10 may be arranged in a combustor casing formed in a cell shape, and a nozzle for injecting fuel, a liner forming a combustion chamber, and a combustor It includes a transition piece that becomes a 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 is formed with a combustion chamber providing a combustion space in which fuel mixed with air is combusted, and a liner annular passage forming an annular space while surrounding the combustion chamber. In addition, a nozzle for injecting fuel is coupled to the front end of the liner, and an igniter is coupled to the sidewall.

In the liner annular flow path, the compressed air introduced through a plurality of holes provided in the outer wall of the liner flows, and the compressed air that has cooled the transition piece, which will be described later, also flows through it. As the compressed air flows along the outer wall of the liner, it is possible to prevent the liner from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

At the rear end of the liner, a transition piece is connected so that the combustion gas combusted by the spark plug can be sent to the turbine side. Like the liner, the transition piece has a transition piece annular flow path surrounding the inner space of the transition piece, and the outer wall is formed by compressed air flowing along the transition piece annular flow path to prevent damage due to the high temperature of the combustion gas. The sub is cooled.

On the other hand, the high-temperature, high-pressure combustion gas from the combustor 12 is supplied to the turbine 13 described above. The high-temperature and high-pressure combustion gas supplied to the turbine 13 expands while passing through the inside of the turbine 13 , and accordingly, an impulse and reaction force are applied to the turbine blade 120 to be described later to generate rotational torque. The rotational torque thus obtained is transmitted to the compressor through the above-described torque tube, and a portion exceeding the power required to drive the compressor is used to drive a generator or the like.

The turbine 13 is basically similar to the structure of the compressor 11 . That is, the turbine 13 is also provided with a plurality of turbine rotors 100 similar to the compressor rotor of the compressor 11 . Accordingly, the turbine rotor 100 also includes a turbine disk 110 and a plurality of turbine blades 120 radially disposed therefrom. Also between the turbine blades 120, a plurality of turbine vanes 16 are provided in an annular shape to the turbine casing 15 when the same stage is used as a reference, and the turbine vanes 16 are the turbine blades 120. ) guides the flow direction of the combustion gas passing through it. In this case, the turbine casing 15 and the turbine vane 16 may also be defined as a generic name of the turbine stator 14 in order to distinguish them from the turbine rotor 10 .

2 and 3, the turbine disk 110 has a plurality of turbine disk slots 111 are formed on its outer peripheral surface. 2 shows only a portion of the turbine disk 110, in fact, the turbine disk 110 may be formed in a disk shape. The turbine blade 120 is installed on the radially outer side of the turbine disk 110 , and the root member 121 inserted into the turbine disk slot 111 and the root member 121 are coupled to the radially outer side of the root member 121 . It includes a platform (Platform; 123) and an airfoil (124) which is coupled to the radially outer side of the platform (123) and rotates by combustion gas.

The platform 123 fixes the airfoil 124 to the root member 121 . In addition, the platform 123 serves to maintain a gap between the adjacent platform 123 and the turbine blades 120 in contact with each other. In this case, although the platform 123 is formed in a planar shape in this embodiment, the shape of the platform 123 may be formed in various shapes.

A root member 121 fastened to the disk slot 111 is provided on a bottom surface of the platform 123 . The root member 121 is formed to correspond to the shape of the curved surface formed in the disk slot 111, which may be selected according to the required structure of the commercially available gas turbine 10, and may have a dovetail or fir tree shape (Fir). -tree).

The fastening method of the root member 121 is a tangential type that is inserted into the turbine disk slot 111 along a tangential direction of the outer circumferential surface of the turbine disk 110, and as shown in FIG. There is an axial type inserted in the turbine disk slot 111 along the axial direction of the turbine disk. In some cases, the turbine blade 120 may be fastened to the turbine disk 110 using a fastener other than the above type, for example, a key or a bolt.

An airfoil 124 is provided on the upper surface of the platform 123 . The airfoil 124 is formed to have an airfoil optimized according to the specifications of the gas turbine 10, a leading edge disposed on the upstream side based on the flow direction of the combustion gas, and a trail disposed on the downstream side It has a trailing edge.

Here, unlike the compressor blade, the turbine blade 120 is in direct contact with the combustion gas of high temperature and high pressure. Since the temperature of the combustion gas is high enough to reach 1700° C., a cooling means is required. To this end, the gas turbine 10 has a extraction flow path for extracting compressed air from a portion of the compressor and supplying it to the turbine blade 120 .

The bleed flow path may extend outside the casing (external flow path) or extend through the inside of the compressor disk (internal flow path), and both the external and internal flow paths may be used. A plurality of film cooling holes (not shown) may be formed on the surface of the airfoil 124 , and the film cooling holes are cooling passages (not shown) formed inside the airfoil 124 . It communicates with and serves to supply compressed air to the surface of the airfoil.

Hereinafter, for convenience of description, reference numeral C denotes a circumferential direction of the turbine disk 110 , reference numeral R denotes a radial direction of the turbine disk 110 , and reference numeral X denotes the turbine disk 110 . is the direction of the axis that is the center of rotation of Here, reference numeral X also denotes the longitudinal direction of the tie rod shown in FIG. 1 .

2 to 5 , the turbine disk slot 111 includes a curved cavity 112 and a cooling cavity 113 . The curved cavity 112 is a portion fastened to the root member 121 of the turbine blade 120 and has an inner wall of a dovetail or fir-tree shape. The cooling cavity 113 is disposed inside the radial direction R of the curved cavity 112 , and cooling air (such as compressed air extracted from the compressor 11 ) is introduced.

The turbine disk 110, the first seating groove 114 is formed on a surface opposite to the turbine disk 110 existing in the adjacent stage (Stage). The first seating groove 114 extends along the circumferential direction C from the turbine disk slot 111 between the curved cavity 112 and the cooling cavity 113 in the radial direction R. formed in the shape In this case, the first seating groove 114 may be provided as a pair with the turbine disk slot 111 interposed therebetween.

The turbine disk 110 has a through hole 115 formed therethrough. The through hole 115 is disposed outside the first seating groove 114 in the radial direction (R). And the through hole 115 is penetrated into the inside of the turbine disk 110 along the axial direction (X). In this case, the through hole 115 may be formed in a shape inclined outward in the radial direction R toward the inside of the turbine disk 110 .

2, 3 and 5 , the root member 121 is inserted into the curved cavity 112 of the turbine disk slot 111 . In addition, a supply hole 125 through which cooling air is introduced is formed at the inner end of the root member 121 in the radial direction (R). The cooling cavity 113 is present between the radially (R) inner end of the root member 121 and the radially (R) inner portion of the turbine disk slot 111 . Cooling air introduced into the turbine disk 111 through will make it Meanwhile, referring to FIG. 5 , at the inner end of the root member 121 , a second seating groove 122 is formed on a surface opposite to the turbine disk 110 of an adjacent stage. When the root member 121 is inserted into the curved cavity 112 , the second seating groove 122 remains connected to the first seating groove 114 .

2 to 6 , the turbine rotor 100 further includes a lifting unit 130 . The lifting unit 130 is coupled to the turbine disk 110, is installed inside the radial direction (R) of the root member 121 to press the root member 121 outward in the radial direction (R) . More specifically, the lifting part 130 is disposed between the curved cavity 112 and the cooling cavity 113 . And the lifting part 130 is formed in a shape extending along the circumferential direction (C), and is seated in the first seating groove 114 and the second seating groove 122 .

Referring to FIG. 6 , the lifting unit 130 includes a first lifting member 131 , a second lifting member 133 , and a penetrating member 135 .

The first lifting member 131 is seated in the first seating groove 114, and the second lifting member 133 is seated in the first seating groove 114 and the second seating groove 122, It is disposed adjacent to the first lifting member (131). And the second lifting member 133 presses the root member 121 outward in the radial direction R, so that the root member 121 and the inner wall of the curved cavity 112 are in closer contact with each other. to keep

More specifically, referring to FIG. 5 , the radial (R) outer portion of the inner wall of the second seating groove 122 is greater than the radial (R) outer portion of the inner wall of the first seating groove 114 . , may be formed in a shape more protruding inward. In this case, when the lifting part 130 is seated in the first and second seating grooves 122 and 122 , the second lifting member 133 of the lifting part 130 moves to the second While being coupled to the seating groove 122 by an interference fit method, the radial direction (R) outer portion of the inner wall of the second seating groove 122 is pressed to the outside. Accordingly, the lifting unit 130 presses the root member 121 outward in the radial direction, so that the root member 121 can maintain a more intimate contact with the inner wall of the curved cavity 112 . have. Meanwhile, as shown in FIGS. 2, 3 and 6 , the first lifting member 131 is provided as a pair and is disposed adjacent to the second lifting member 133 in the circumferential direction (C). can be

The first lifting member 131 has a first protrusion 132 protruding toward the second lifting member 133 , and the second lifting member 133 moves toward the first lifting member 131 . Two protrusions 134 are formed to protrude. The first protrusion 132 and the second protrusion 134 are disposed to contact each other. And the second protrusion 134 is disposed between the first protrusion 132 and the inner wall of the first seating groove 114 . That is, the first protrusion 132 is disposed in a state of pressing the second protrusion 134 toward the turbine disk 110 .

The through member 135 is coupled to the first lifting member 131 and is inserted into the through hole 115 . More specifically, the penetrating member 135 is formed in a cylindrical shape, and may be coupled to the outer side in the radial direction R of the first lifting member 131 . And correspondingly, the radially (R) outer portion of the first lifting member 131 may be concave as shown in FIG. 6 . In this case, the penetrating member 135 may be formed in a hollow shape. Therefore, in a state in which the penetrating member 135 is inserted into the through hole 115 , a separate fastening member (not shown; for example, a bolt) is inserted into the penetrating member 135 , so that the first lifting A member 131 may be fixed to the turbine disk 110 . And in this case, as the first protrusion 132 presses the second protrusion 134 toward the turbine disk 110 , the second lifting member 133 is attached to the inner wall of the second seating groove 122 . clings to

According to the present invention as described above, the disk slot 111 formed in the turbine disk 110 is divided into a curved cavity 112 and a cooling cavity 113 existing below the curved cavity 112, and the turbine blade 120 ) of the root member 121 is inserted into the curved cavity 112, and a lifting part 130 is inserted between the curved cavity 112 and the cooling cavity 113, the root member 121 of the turbine blade 120. By pressing radially outward, the root member 121 of the turbine blade 120 and the turbine disk 110 can be brought into close contact with each other during operation of the turbomachine 10 and at the same time, the turbine from the outside through the cooling cavity 113 Cooling air may be introduced into the disk 110 .

10: turbo machine (gas turbine) 13: turbine
100: turbine rotor 110: turbine disk
112: curved cavity 113: cooling cavity
114: first seating groove 120: turbine blade
122: second seating groove 130: lifting part
131: first lifting member 132: first projection
133: second lifting member 134: second projection
135: penetrating member

Claims (20)

a disk having a disk slot formed thereon;
a blade inserted into the disk slot and including a root member for forming a cooling cavity between an inner portion of the disk slot with respect to the radial direction of the disk, and an air foil disposed on the radially outer side of the root member; and
It is coupled to the disk and is installed on the radially inner side of the root member and includes a lifting part for pressing the root member to the outside,
The lifting unit,
a second lifting member for pressing the root member outward in the radial direction (R) to maintain a state in which the root member and the inner wall of the curved cavity are in close contact;
A pair of first lifting members respectively disposed on both ends of the second lifting member,
The first lifting member and the second lifting member are formed in a shape extending along the circumferential direction (C) of the turbine disk. The method according to claim 1,
The lifting unit is a rotor disposed between the cooling cavity and the inner end of the root member. The method according to claim 1,
The disk has a first seating groove formed on a surface opposite to the disk of an adjacent stage,
The lifting part is a rotor installed in the first seating groove. 4. The method according to claim 3,
The first seating groove is disposed between the cooling cavity and the inner end of the root member with respect to the radial direction of the disk, and is formed in a shape extending in the circumferential direction of the disk. 4. The method according to claim 3,
At the inner end of the root member, a second seating groove is formed on a surface opposite to the disk of an adjacent stage and connected to the first seating groove,
The lifting part is a rotor installed in the first seating groove and the second seating groove. 6. The method of claim 5,
A radially outer portion of the inner wall of the second seating groove protrudes more inward than a radially outer portion of the inner wall of the first seating groove,
The first lifting member,
installed in the first seating groove,
The second lifting member,
A rotor installed in the first and second seating grooves, adjacent to the first lifting member, and installed in the second seating groove to press the inner wall of the second seating groove radially outward. 7. The method of claim 6,
The first lifting member, a first projection is formed to protrude toward the second lifting member,
The second lifting member is a rotor having a second protrusion protruding toward the first lifting member and contacting the first protrusion. 8. The method of claim 7,
The second protrusion is disposed between the first protrusion and an inner wall of the first seating groove. 7. The method of claim 6,
The disk is formed with a through hole,
The lifting unit,
The rotor coupled to the first lifting member and further comprising a penetrating member inserted into the through hole. 10. The method of claim 9,
The penetrating member is coupled to the radially outer side of the first lifting member, and is formed in a hollow shape. a stator for guiding the fluid passing therein; and
A rotor installed inside the stator and rotated by the fluid passing into the stator; including,
The rotor is
a disk having a disk slot formed therein;
A blade comprising: a root member inserted into the disk slot and forming a cooling cavity between an inner portion of the disk slot with respect to the radial direction of the disk; and an air foil disposed on the radially outer side of the root member; ,
It is coupled to the disk and is installed on the radially inner side of the root member and includes a lifting part for pressing the root member to the outside,
The lifting unit,
a second lifting member for pressing the root member outward in the radial direction (R) to maintain a state in which the root member and the inner wall of the curved cavity are in close contact;
A pair of first lifting members respectively disposed on both ends of the second lifting member,
The first lifting member and the second lifting member are formed in a shape extending along the circumferential direction (C) of the turbine disk. 12. The method of claim 11,
The lifting unit is a turbomachine that is disposed between the cooling cavity and the inner end of the root member. 12. The method of claim 11,
The disk has a first seating groove formed on a surface opposite to the disk of an adjacent stage,
The lifting part is a turbo machine installed in the first seating groove. 14. The method of claim 13,
The first seating groove is disposed between the cooling cavity and the inner end of the root member with respect to the radial direction of the disk, and is formed in a shape extending along the circumferential direction of the disk. 14. The method of claim 13,
At the inner end of the root member, a second seating groove is formed on a surface opposite to the disk of an adjacent stage and connected to the first seating groove,
The lifting part is a turbo machine installed in the first seating groove and the second seating groove. 16. The method of claim 15,
A radially outer portion of the inner wall of the second seating groove protrudes more inward than a radially outer portion of the inner wall of the first seating groove,
The first lifting member,
installed in the first seating groove,
The second lifting member,
A turbo machine installed in the first and second seating grooves, adjacent to the first lifting member, and radially outwardly pressing the inner wall of the second seating groove as it is installed in the second seating groove. 17. The method of claim 16,
The first lifting member, a first projection is formed to protrude toward the second lifting member,
The second lifting member is a turbomachine in which a second protrusion protrudes toward the first lifting member and comes into contact with the first protrusion. 18. The method of claim 17,
The second protrusion is disposed between the first protrusion and the inner wall of the first seating groove. 17. The method of claim 16,
The disk is formed with a through hole,
The lifting unit,
The turbomachine further comprising a penetrating member coupled to the first lifting member and inserted into the through hole. 20. The method of claim 19,
The penetrating member is coupled to the radially outer side of the first lifting member, and is formed in a hollow shape.

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