KR102141998B1 - Blade shroud, turbine and gas turbine comprising the same - Google Patents

Abstract

The present invention is to provide a blade shroud with improved cooling performance by improving the cooling structure formed inside the shroud, a turbine and a gas turbine using the same, in the blade shroud formed on the blade tip of the gas turbine, the cooling air flows A shroud body in which a cooling flow path is formed; And an impingement plate formed in the cooling passage and spraying cooling air supplied through the cooling passage to the inner wall of the shroud body, and a blade shroud, a turbine, and a gas turbine using the same.

Description

Blade shroud, turbine and gas turbine comprising the same}

The present invention relates to a blade shroud, a turbine and a gas turbine including the same, and more particularly, to a blade shroud, a turbine and a gas turbine including the blade shroud formed on the tip of the blade rotating by the combustion gas supplied from the combustor will be.

Generally, a gas turbine is composed of a compressor, a combustor, and a turbine. In the compressor, a plurality of compressor vanes and compressor blades are alternately arranged in the compressor casing. And the compressor draws in the outside air through the compressor inlet scroll strut. The air sucked in this way is compressed by the compressor vane and the compressor blade while passing through the interior of the compressor.

The combustor receives compressed air compressed by 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 generated combustion gas is supplied to the turbine.

In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in the turbine casing. And the turbine receives the combustion gas generated by the combustor and passes it through. The combustion gas passing through the inside of the turbine rotates the turbine blade, and the combustion gas completely passing through the inside of the turbine is discharged to the outside through the turbine diffuser.

The gas turbine further includes a tie rod. The tie rod is installed such that the compressor blade is coupled to the outer circumferential surface of the compressor disk and the turbine blade is coupled to the outer circumferential surface of the turbine disk. Accordingly, the tie rod allows the compressor disk and the turbine disk to be fixed to each other inside the gas turbine.

Since such a gas turbine does not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction portion such as a piston-cylinder and consumption of lubricant is extremely low. Therefore, the gas turbine has an advantage in that amplitude, which is a characteristic of a reciprocating machine, is greatly reduced, and high-speed motion is possible, thereby generating high-capacity power.

As a technology related to the turbine blade of such a gas turbine, Korean Registered Utility Model No. 20-0174662 discloses a gas turbine.

The turbine blade included in the conventional gas turbine includes an air foil through which combustion gas passes, a root member inserted into the turbine disk to fix the air foil to the disk, and installed between the air foil and the root member, and the air foil It includes a platform on which it rests. The airfoil includes a main body portion and a tip part extending from a pressure side side and a suction side side to the turbine casing side.

A blade shroud is formed at the tip of the turbine blade toward the turbine casing. The blade shroud is made of a shape surrounding the blade tip to prevent the gas from leaking out of the blade tip. The shroud encloses the tip of the turbine blade to prevent gas leakage, thereby increasing efficiency and to make the turbine blade thin and lightweight.

In recent years, although the temperature of the 3rd and 4th stage blades is increasing as the efficiency of the gas turbine becomes important, there is a problem that the cooling efficiency is not high because the shroud portions of a plurality of blades are not cooled or have a simple cooling structure.

The present invention was created to solve the above problems, and has an object to provide a blade shroud, a turbine, and a gas turbine using the same, which has improved cooling performance by improving the cooling structure formed inside the shroud.

Blade shroud according to an aspect of the present invention, in the blade shroud formed on the blade tip of the gas turbine, a shroud body in which a cooling flow path through which cooling air flows is formed; And an impingement plate formed on the cooling passage and spraying cooling air supplied through the cooling passage to the inner wall of the shroud body.

Preferably, the cooling flow path includes a first cooling flow path formed parallel to the tip portion of the blade, and a second cooling flow path formed to bend and extend from the first cooling flow path toward the tip portion of the blade, and the first cooling flow path. The impingement plate is disposed between and the second cooling passage.

More preferably, the cooling air guide is further disposed on the downstream side of the first cooling flow path to guide the cooling air supplied through the first cooling flow path to the second cooling flow path. It may be formed of a plate having a curved surface formed on the inner wall of the shroud body.

In addition, a first cooling hole for supplying a portion of the cooling air supplied from the first cooling channel to the outside of the shroud body is formed in the shroud body downstream of the first cooling channel, and the cooling air supplied to the second cooling channel is provided. A second cooling hole to supply the outside of the shroud body may be formed on the blade tip side of the second cooling passage.

In addition, an insertion hole is formed in the shroud body on one side of the impingement plate, and further includes a fixing part formed in the insertion hole to prevent the impingement plate from coming off, and the fixing part is formed through a welding process. Can be.

On the other hand, the present invention, the tie rod penetrates through the center, generates a power for generating electricity through the combustion gas supplied from the combustor, and in the turbine cooled by compressed air supplied from the compressor, the casing, A stator installed on the inner circumferential surface of the casing and including vanes arranged in a multi-stage along the flow direction of combustion gas; A disk installed between the casing and the tie rod, and a blade installed on an outer circumferential surface of the disk and disposed between the vane and the vane to rotate by combustion gas; And a rotor including a blade shroud formed at a tip of the blade, wherein the blade shroud is formed with a shroud body in which a cooling flow path through which cooling air flows is formed; And an impingement plate formed in the cooling passage and spraying cooling air supplied through the cooling passage to the inner wall of the shroud body.

Preferably, one end is in communication with the cooling flow path and a blade cooling flow path formed inside the blade is formed to supply cooling air to the cooling flow path through the blade cooling flow path, wherein the cooling flow path is a tip portion of the blade. And a second cooling flow path formed parallel to and a second cooling flow path extending from the first cooling flow path toward the tip of the blade, and between the first cooling flow path and the second cooling flow path. The plate may be arranged.

And, it is disposed on the downstream side of the first cooling flow path further includes a cooling air guide that guides the cooling air supplied through the first cooling flow path to the second cooling flow path, wherein the cooling air guide comprises the shroud body. It may be a plate of a curved surface formed on the inner wall.

In addition, a first cooling hole for supplying a portion of the cooling air supplied from the first cooling flow path to the outside of the shroud body is formed in the shroud body downstream of the first cooling flow path, and the cooling air supplied to the second cooling flow path A second cooling hole to supply the outside of the shroud body may be formed on the blade tip side of the second cooling passage.

In addition, an insertion hole is formed in the shroud body on one side of the impingement plate, and may further include a fixing part formed in the insertion hole to prevent separation of the impingement plate.

On the other hand, the present invention, the compressor for sucking air to compress; A combustor that combusts the compressed air supplied from the compressor with fuel; A turbine that generates power for generating electricity by passing the combustion gas supplied from the combustor therein, and is cooled by compressed air supplied from the compressor; And a tie rod penetrating through the center of the compressor and the turbine, wherein the turbine comprises a casing and vanes installed on the inner circumferential surface of the casing and arranged in multi-stage along the flow direction of the combustion gas. A stator, a disk installed between the casing and a tie rod, and a blade shroud provided on an outer circumferential surface of the disk and disposed between the vane and the vane to rotate by combustion gas and a tip of the blade It includes a rotor, and the blade shroud is a shroud body in which a cooling flow path through which cooling air flows is formed; And an impingement plate formed in the cooling passage and spraying cooling air supplied through the cooling passage to the inner wall of the shroud body.

In addition, the cooling flow path includes a first cooling flow path formed parallel to the tip portion of the blade, and a second cooling flow path extending from the first cooling flow path toward the tip portion of the blade, and the first cooling flow path. The impingement plate is disposed between the second cooling flow paths, and is disposed on the downstream side of the first cooling flow path to guide cooling air supplied through the first cooling flow path to the second cooling flow path. It may further include, it may be a plate of a curved surface formed on the inner wall of the shroud body.

And, a first cooling hole for supplying a portion of the cooling air supplied from the first cooling flow path to the outside of the shroud body is formed in the shroud body downstream of the first cooling flow path, and the cooling air supplied to the second cooling flow path A second cooling hole to supply the outside of the shroud body may be formed on the blade tip side of the second cooling passage.

According to the blade shroud according to the present invention, a turbine and a gas turbine including the same, the cooling efficiency of the blade shroud can be improved by providing an impingement plate in the cooling passage formed inside the blade shroud.

1 is a cross-sectional view showing a schematic structure of a gas turbine to which an embodiment of the present invention is applied.
FIG. 2 is an exploded perspective view showing the turbine rotor in FIG. 1.
FIG. 3 is a cross-sectional view of part “A” of FIG. 2.
4 is an end cross-sectional view of a blade shroud according to another embodiment of the present invention.
5 is an end cross-sectional view of a blade shroud according to another embodiment of the present invention.

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

Hereinafter, embodiments of the blade airfoil, turbine, and gas turbine including the same will be described with reference to the drawings.

Referring to Figure 1, the gas turbine 1 according to the present invention includes a compressor 2, a combustor 3 and a turbine 10. Based on the flow direction of the gas (compressed air or combustion gas), the compressor 2 is disposed on the upstream side of the gas turbine 1 and the turbine 10 is disposed on the downstream side. And the combustor 3 is arranged between the compressor 1 and the turbine 10.

The compressor 2 accommodates the compressor vane and the compressor rotor inside the compressor casing, and the turbine 10 accommodates the turbine vane 13 and the turbine rotor 100 inside the turbine casing 12. The compressor vane and the compressor rotor are arranged in a multi-stage along the flow direction of compressed air, and the turbine vane 13 and the turbine rotor 100 are also arranged in multiple stages along the flow direction of the combustion gas. At this time, the compressor 2, the inner space decreases toward the rear-stage side from the front-stage so that the intake air can be compressed, and on the contrary, the turbine 10 expands the combustion gas supplied from the combustor. It is designed in such a way that the internal space becomes larger as it goes from the front end to the rear end.

On the other hand, between the compressor rotor located at the rear end side of the compressor and the turbine rotor located at the front end side of the turbine, a torque tube as a torque transmission member for transmitting rotational torque generated by the turbine to the compressor is disposed. The torque tube may be composed of a plurality of torque tube discs consisting of a total of three stages, as shown in Figure 1, but this is only one of several embodiments of the present invention, the torque tube is four or more stages or It may be composed of a plurality of torque tube discs consisting of two or less stages.

The compressor rotor includes a compressor disk and a compressor blade. A plurality of (for example, 14) compressor discs are provided inside the compressor casing, and each of the compressor discs is fastened so as not to be spaced apart in the axial direction by a tie rod 4. More specifically, each of the compressor discs is aligned along the axial direction of each other with the central portion penetrated by the tie rod 4. In addition, each adjacent compressor disk is arranged such that the opposing faces are compressed by the tie rods 4 so that they cannot rotate relative to each other.

A plurality of compressor blades are radially coupled to the outer circumferential surface of the compressor disk. Further, between the compressor blades, a plurality of compressor vanes, which are provided in an annular shape on the inner circumferential surface of the compressor casing, respectively, are arranged on the basis of the same stage. Unlike the compressor disc, the compressor vane maintains a fixed state so as not to rotate, and serves to guide compressed air to a compressor blade positioned downstream by aligning the flow of compressed air passing through the compressor blade. At this time, the compressor casing and the compressor vane corresponding to the fixed body may be defined with a comprehensive name of a compressor stator in order to distinguish them from the compressor rotor corresponding to the rotating body.

The tie rod is disposed to penetrate the center of the plurality of compressor discs and a turbine disc, which will be described later, and one end is fastened in the compressor disc located at the foremost end of the compressor, and the other end is fastened by a fixing nut. do.

Since the shape of the tie rod may be formed in 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 that passes through the central portion of the compressor disc and the turbine disc, or may have a shape in which a plurality of tie rods are arranged in a circumferential shape, and mixing of these is possible.

Although not shown, the compressor of the gas turbine may be equipped with a desworler that serves as a guide to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor 3 to the design flow angle. .

In the combustor (3), the compressed air introduced is mixed and burned with fuel to produce high-temperature, high-pressure combustion gas with high energy. Combustion gas up to the heat-resistant limit that the combustor (3) and turbine components can withstand through isostatic combustion. It will increase the temperature.

Combustors constituting the combustion system of the gas turbine may be arranged in a plurality in a combustor casing formed in a cell shape, a nozzle for injecting fuel, a liner forming a combustion chamber, and a transition for connecting the combustor to the turbine Includes a piece (Transition piece).

Specifically, the liner provides a combustion space in which fuel injected by the fuel nozzle is mixed with compressed air of the compressor and burned. The liner includes a combustion chamber that provides a combustion space in which fuel mixed with air is combusted, and a liner annular flow path that forms 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, compressed air introduced through a plurality of holes provided on the outer wall of the liner flows, and compressed air that cools a transition piece to be described later also flows through it. As such, the compressed air flows along the outer wall portion of the liner, thereby preventing 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 burned by the spark plug can be sent to the turbine side. Like the liner, the transition piece is formed with a transition piece annular flow path surrounding the inner space of the transition piece, and an outer wall by compressed air flowing along the transition piece annular flow path to prevent damage due to high temperature of combustion gas. The part is cooled.

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor is supplied to the above-described turbine. The high-temperature and high-pressure combustion gas supplied to the turbine expands while passing through the inside of the turbine, and accordingly, impulses and reaction forces are applied to the turbine blades, which will be described later, to generate rotation torque. The rotation torque thus obtained is transmitted to the compressor through the above-described torque tube, and the portion exceeding the power required to drive the compressor is used to drive the generator.

The turbine 10 is basically similar to the structure of the compressor 2. That is, the turbine 10 is also provided with a plurality of turbine rotors 100 similar to the compressor rotor of the compressor 2. Therefore, the turbine rotor 100 also includes a turbine disk 110 and a plurality of turbine blades 1000 radially disposed therefrom. Between the turbine blades 1000, a plurality of turbine vanes 13 are provided which are annularly installed in the turbine casing 12, based on the same stage, and the turbine vanes 13 are turbine blades 1000 ) To guide the flow direction of the combustion gas passing through. At this time, the turbine casing 12 and the turbine vane 13 corresponding to the stationary body may also be defined by the generic name of the turbine stator 11 in order to distinguish them from the turbine rotor 100 corresponding to the rotating body. have.

Referring to FIG. 2, the turbine disk 110 has a disk shape and a plurality of turbine disk slots are formed on its outer circumferential surface. Turbine blade 1000 is installed on the radially outer side of the turbine disk 110, the root member 1200 inserted into the turbine disk slot, and the platform coupled to the radially outer side of the root member 1200 ( 1300; Platform, and an airfoil 1100; Airfoil coupled to the radially outer side of the platform 1300 to rotate by the combustion gas.

The platform 1300 is disposed at a central portion of the turbine blade 1000 to fix the airfoil 1100 to the root member 1200. In addition, the platform 1300 serves to maintain a gap between the turbine blades 1000 by adjoining the platform 1300 and its side surfaces. In this case, although the platform 1300 is illustrated in FIG. 2 as having a flat shape, this is only an embodiment of the present invention, and the shape of the platform 1300 may be variously formed.

A root member 1200 fastened to the disk slot is provided on the bottom surface of the platform 1300. The root member 1200 is formed to correspond to the shape of a curved surface formed in the disk slot, which can be selected according to the required structure of a commercial gas turbine, and commonly known dovetail or fir-tree (Fir-tree) Can have

The fastening method of the root member includes a tangential type inserted in the turbine disk slot along the tangential direction of the outer circumferential surface of the turbine disk, and an axial inserted in the turbine disk slot along the axial direction of the turbine disk. There are axial types. In some cases, the turbine blade may be fastened to the turbine disk using a fastener other than the above type, for example, a key or a bolt.

The airfoil 100 is provided on the upper surface of the platform 1300. The airfoil 1100 is formed to have an optimized airfoil according to the specifications of the gas turbine, and 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 ( Trailing edge).

Here, unlike the compressor blade, the turbine blade is in 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, the compressed air is extracted at a part of the compressor to have a bleeding flow path for supplying it to the turbine blade.

The extraction flow path may extend from the outside of the casing (outside flow path), extend through the interior of the compressor disc (inside flow path), or may use both the outer and inner flow paths. In FIG. 2, a plurality of film cooling holes are formed on the surface of the airfoil, and the film cooling holes are in communication with a blade cooling flow path (not shown) formed inside the airfoil to compress air. It serves to supply to the surface of the airfoil.

A blade shroud 1400 is formed at a tip 1100a; a tip of the turbine blade.

Referring to FIG. 3, the blade shroud 1400 includes a shroud body 1410 and an impingement plate 1420.

The shroud body 1410 is formed on the blade tip of the gas turbine, and a cooling passage 1430 through which cooling air flows is formed.

The cooling passage 1430 is formed in communication with the blade cooling passage formed inside the air foil 1100 of the blade.

The cooling passage 1430 of the shroud body 1410 is formed with a first cooling passage 1431 and a second cooling passage 1432. The first cooling passage 1431 is formed in communication with the blade cooling passage and is formed in a position close to the outer end (upper end of FIG. 3) of the blade shroud 1400 in parallel with the tip of the blade. The second cooling passage 1432 is formed to be bent from the end of the first cooling passage 1431 to the tip side (lower side of FIG. 3) of the blade. Accordingly, the cooling air supplied to the first cooling channel 1431 is supplied to the second cooling channel 1432 to cool the lower portion of the shroud body 1410.

The cooling passage 1430 is formed with an impingement plate 1420 that injects cooling air supplied from the first cooling passage 1431 toward the second cooling passage 1432.

The impingement plate 1420 is formed between the first cooling flow path 1431 and the second cooling flow path 1432, and the cooling air supplied from the first cooling flow path 1431 is the second cooling flow path. The shroud body 1410 is cooled by spraying the inner wall 1410a of the shroud body 1410 forming the (1432). The impingement plate 1420 is formed in a plate-shaped plate with a plurality of injection holes flowing through the cooling air.

The injection hole is formed in a shape that gradually decreases in diameter as it goes from the first cooling flow path 1431 to the second cooling flow path 1432, so that the cooling air can be sprayed at a faster speed toward the inner wall of the second cooling flow path. To make.

In order to mount the impingement plate 1420, an insertion hole 1413 is formed on a side surface of the shroud body 1410. The insertion hole 1413 may be processed into a slot shape through Electric Discharge Machining (EDM). The impingement plate 1420 is inserted into the shroud body through the insertion hole 1413. When the impingement plate 1420 is not required, the space inside the insertion hole may be left as an empty space to block the entrance, thereby reducing the mass of the entire blade shroud.

A fixed portion 1450 is formed at the entrance of the insertion hole 1413 to prevent the separation by fixing the inserted impingement plate. The fixing part 1450 may be formed through a process such as a welding process or punching. When the impingement plate 1420 is fixed by the fixing part 1450, the surface of the fixing part is ground to form a smooth surface.

Meanwhile, a cooling air guide 1440 is formed on the downstream side of the first cooling flow path 1431. The cooling air guide 1440 is disposed downstream of the first cooling flow path 1431, and the cooling air supplied through the first cooling flow path 1431 is the impingement plate 1420 on the second cooling flow path side. ). The cooling air guide 1440 is formed of a curved plate on one end of which is arranged on the inlet side of the first cooling channel and the other end on the side of the impingement plate 1420. Accordingly, the cooling air transferred through the first cooling passage 1431 flows to the impingement plate 1420. In this embodiment, the cooling air guide 1440 is formed as a separate plate, but it is also possible to form the cooling air guide integrally with the shroud body by processing the shape of the inner wall of the shroud body into a curved shape.

The blade shroud 1400 according to an embodiment of the present invention may form an impingement plate in a cooling channel to efficiently cool the blade shroud.

4 is an end cross-sectional view of a blade shroud according to another embodiment of the present invention.

4, the blade shroud 2400 according to another embodiment of the present invention includes a shroud body 2410 and an impingement plate 2420, wherein the shroud body 2410 is a blade tip of a gas turbine Is formed therein, a cooling passage 2430 through which cooling air flows is formed.

The cooling flow path 2430 includes a first cooling flow path 2431 and a second cooling flow path 2432. The first cooling passage 2431 is formed in a position close to the outer end of the blade shroud (upper end of FIG. 4) parallel to the tip portion of the blade, the second cooling passage 2432 is from the first cooling passage It is bent toward the tip portion (lower side in FIG. 4) of the blade to be extended.

A first cooling hole 2411 communicating the outside of the first cooling flow path 2431 and the shroud body 2410 is formed on a shroud body downstream of the first cooling flow path 2431 (right side in FIG. 4 ). A portion of the cooling air supplied through the first cooling channel 2431 is discharged to the outside of the shroud body 2410 through the first cooling hole 2411, and accordingly, the side surface 2410a of the shroud body Can be cooled.

5 is an end cross-sectional view of a blade shroud 3400 according to another embodiment of the present invention.

5, the blade shroud 3400 according to another embodiment of the present invention includes a shroud body 3410 and an impingement plate 3420, wherein the shroud body 3410 is a blade of a gas turbine It is formed on the tip, and a cooling passage through which cooling air flows is formed inside.

The cooling flow path 3430 includes a first cooling flow path 3431 and a second cooling flow path 3432. The first cooling passage 3430 is formed in a position close to the outer end of the blade shroud (the upper end of FIG. 5) in parallel with the tip portion of the blade, and the second cooling passage 3432 is from the first cooling passage The blade is bent toward the tip portion (the lower side of FIG. 5) to be extended.

In the shroud body 3410 of the blade tip side of the second cooling flow path, a second cooling hole 3412 is formed to communicate the second cooling flow path 3432 and the outside of the shroud body. A part of the cooling air supplied through the second cooling passage 3432 is discharged to the outside of the shroud body 3410 through the second cooling hole 3412 (Fig. 5) The lower surface 3410a is cooled.

Although the present invention has been described with reference to the embodiments shown in the drawings, these are merely exemplary, and those skilled in the art will understand 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.

1: Gas turbine 10: Turbine
1000: turbine blade 1100: air foil
1400: Blade shroud 1410: Shroud body
1430: cooling passage 1431: first cooling passage
1432: Second cooling passage 1440: Cooling air guide

Claims (21)

In the blade shroud formed on the blade tip of the gas turbine,
A shroud body in which a cooling flow path through which cooling air flows is formed; And
It includes an impingement plate is formed a plurality of injection holes for spraying the cooling air supplied through the cooling passage to the inner wall of the shroud body,
Insertion holes are formed in the shroud body on one side of the impingement plate,
It is formed in the insertion hole further comprises a fixing portion for preventing the separation of the impingement plate,
The cooling flow path includes a first cooling flow path that is formed parallel to the tip portion of the blade, and a second cooling flow path that is bent and extended from the first cooling flow path toward the tip portion of the blade, and the first cooling flow path and the first 2 the impingement plate is disposed between the cooling passages,
The injection hole is a blade shroud made of a shape that gradually decreases in diameter as it goes from the first cooling flow path toward the second cooling flow path.
delete The method according to claim 1,
Blade shroud further comprises a cooling air guide disposed on the downstream side of the first cooling flow path to guide the cooling air supplied through the first cooling flow path to the second cooling flow path. The method according to claim 3,
The cooling air guide is a blade shroud which is a plate having a curved surface formed on the inner wall of the shroud body. The method according to claim 1,
A blade shroud in which a first cooling hole for supplying a portion of the cooling air supplied from the first cooling flow path to the outside of the shroud body is formed on the downstream shroud body of the first cooling flow path. The method according to claim 1,
A blade shroud in which a second cooling hole for supplying cooling air supplied to the second cooling channel to the outside of the shroud body is formed on the blade tip portion side of the second cooling channel.
delete The method according to claim 1,
The fixing part is a blade shroud formed through a welding process. In the turbine through which the tie rod passes through the center, generates power for generating electric power through the combustion gas supplied from the combustor, and is cooled by the compressed air supplied from the compressor,
A stator including a casing and vanes installed on an inner circumferential surface of the casing and arranged in a multi-stage along a flow direction of combustion gas; A disk installed between the casing and the tie rod, and a blade installed on an outer circumferential surface of the disk and disposed between the vane and the vane to rotate by combustion gas; And a rotor including a blade shroud formed on the tip of the blade,
The blade shroud, a shroud body in which a cooling flow path through which cooling air flows is formed; And an impingement plate in which a plurality of injection holes for spraying cooling air supplied through the cooling passage to the inner wall of the shroud body are formed,
Insertion holes are formed in the shroud body on one side of the impingement plate,
It is formed in the insertion hole further comprises a fixing portion for preventing the separation of the impingement plate,
The cooling flow path includes a first cooling flow path that is formed parallel to the tip portion of the blade, and a second cooling flow path that extends from the first cooling flow path toward the tip portion of the blade, and includes the first cooling flow path and the first cooling flow path. 2, the impingement plate is disposed between the cooling passages,
The injection hole is a turbine made of a shape that gradually decreases in diameter as it goes from the first cooling passage to the second cooling passage. The method according to claim 9,
A turbine having one end communicating with the first cooling channel and forming a blade cooling channel formed inside the blade to supply cooling air to the first cooling channel through the blade cooling channel. delete The method according to claim 9,
The turbine further comprises a cooling air guide disposed on the downstream side of the first cooling flow path and guiding cooling air supplied through the first cooling flow path to the second cooling flow path. The method according to claim 12,
The cooling air guide is a turbine which is a plate having a curved surface formed on the inner wall of the shroud body. The method according to claim 9,
A turbine in which a first cooling hole for supplying a portion of the cooling air supplied from the first cooling flow path to the outside of the shroud body is formed in the shroud body downstream of the first cooling flow path.
The method according to claim 9,
A turbine in which a second cooling hole for supplying cooling air supplied to the second cooling channel to the outside of the shroud body is formed in the shroud body at the blade tip side of the second cooling channel.
delete A compressor that sucks air and compresses it; A combustor that combusts the compressed air supplied from the compressor with fuel; A turbine that generates power for generating electricity by passing the combustion gas supplied from the combustor therein, and is cooled by compressed air supplied from the compressor; And a tie rod passing through the center of the compressor and turbine,
The turbine, a stator comprising a casing, a vane installed on the inner circumferential surface of the casing and disposed in a multi-stage along the flow direction of the combustion gas, and a disc installed between the casing and the tie rod, It is installed on the outer circumferential surface of the disk, and is disposed between the vane and the vane, respectively, and a rotor including a blade rotating by combustion gas and a blade shroud formed at the tip of the blade,
The blade shroud, a shroud body in which a cooling flow path through which cooling air flows is formed; And an impingement plate in which a plurality of injection holes for spraying cooling air supplied through the cooling passage to the inner wall of the shroud body are formed,
Insertion holes are formed in the shroud body on one side of the impingement plate,
It is formed in the insertion hole further comprises a fixing portion for preventing the separation of the impingement plate,
The cooling flow path includes a first cooling flow path that is formed parallel to the tip portion of the blade, and a second cooling flow path that is bent and extended from the first cooling flow path toward the tip portion of the blade, and the first cooling flow path and the first 2, the impingement plate is disposed between the cooling passages,
The injection hole is a gas turbine made of a shape that gradually decreases in diameter as it goes from the first cooling passage to the second cooling passage.
delete The method according to claim 17,
A gas turbine further disposed in a downstream side of the first cooling flow path, the cooling air guide guiding cooling air supplied through the first cooling flow path to the second cooling flow path. The method according to claim 19,
The cooling air guide is a gas turbine which is a plate having a curved surface formed on the inner wall of the shroud body. The method according to claim 17,
A first cooling hole for supplying a portion of the cooling air supplied from the first cooling channel to the outside of the shroud body is formed in the shroud body downstream of the first cooling channel,
A gas turbine in which a second cooling hole for supplying cooling air supplied to the second cooling channel to the outside of the shroud body is formed on the blade tip side of the second cooling channel.

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