KR20200038698A - Nozzle assembly, combustor and gas turbine including the same - Google Patents

Abstract

According to the present invention, provided are a nozzle assembly, a combustor and a gas turbine including the same. The nozzle assembly, which can spray compressed air supplied from a compressor of a gas turbine and fuel supplied from the outside to a combustion chamber of a combustor of the gas turbine by mixing the compressed air with the fuel, includes: a nozzle flange receiving fuel from the outside; a nozzle shroud placed on one side of the nozzle flange; a first main cylinder placed in a radius direction of the nozzle shroud, wherein a first main flow path is formed between the first main cylinder and the nozzle shroud; a first swirler installed on the first main cylinder; and a grid module installed to the upstream side of the first swirler when a flow direction of the compressed air is considered as a base point, and spraying the fuel supplied from the nozzle flange to the first swirler. According to the nozzle assembly, the combustor and the gas turbine including the same of the present invention, fuel and compressed air can be more evenly mixed to be sprayed to a combustion chamber.

Description

Nozzle assembly, combustor and gas turbine including the same {Nozzle assembly, combustor and gas turbine including the same}

The present invention relates to a nozzle assembly, a combustor, and a gas turbine including the same, and more specifically, to generate a combustion gas by burning a mixture of compressed air and fuel by mixing compressed air and fuel and injecting it into the combustion chamber. It relates to a combustor and a gas turbine comprising the same.

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 blades, 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, so 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.

On the other hand, in the conventional gas turbine, there is a problem that the compressed air and the fuel are not uniformly mixed as the fuel is directly injected from the swirl vane forming a vortex in the compressed air to be introduced.

The present invention was created to solve the above problems, the compressed air supplied from the compressor and the fuel supplied from the outside to be more uniformly mixed, to improve the combustion efficiency in the combustion chamber nozzle assembly, It is an object to provide a combustor and a gas turbine comprising the same.

A nozzle assembly according to an aspect of the present invention, by mixing the compressed air supplied from the compressor of the gas turbine and the fuel supplied from the outside to inject into the combustion chamber of the combustor of the gas turbine, the nozzle flange receiving the fuel from the outside; A nozzle shroud disposed on one side of the nozzle flange; A first main cylinder disposed in the radially inner side of the nozzle shroud and forming a first main flow path between the nozzle shroud; A first swirler installed in the first main cylinder; And a grating module installed on the upstream side of the first swirler when based on the flow direction of compressed air, and injecting fuel supplied from the nozzle flange to the first swirler side.

According to another aspect of the present invention, as a mixture of the compressed air supplied from the compressor of the gas turbine and the fuel supplied from the outside to be combusted, a nozzle assembly for mixing and injecting the supplied fuel and the compressed air; A liner having a combustion chamber in which a mixture of fuel and compressed air injected from the nozzle assembly is burned; And a transition piece receiving combustion gas generated from the combustion chamber, wherein the nozzle assembly includes: a nozzle flange supplied with fuel from the outside; a nozzle shroud disposed on one side of the nozzle flange; and the nozzle shroud. The first main cylinder is disposed inside the radial direction and forms a first main flow path between the nozzle shroud, the first swirler installed in the first main cylinder, and the flow direction of compressed air. It is installed on the upstream side of the first swirler at the time, and a combustor including a lattice module for injecting fuel supplied from the nozzle flange to the first swirler is provided.

According to another aspect of the invention, the compressor for compressing the air supplied from the outside; A combustor that mixes and compresses compressed air supplied from the compressor and fuel supplied from the outside; And a turbine for passing power through the combustion gas supplied from the combustor to generate power for generating electricity, wherein the combustor comprises a nozzle assembly for mixing and supplying the supplied fuel and compressed air, and from the nozzle assembly. A liner having a combustion chamber in which a mixture of the injected fuel and compressed air is burned, and a transition piece receiving combustion gas generated from the combustion chamber, wherein the nozzle assembly includes a nozzle flange supplied with fuel from the outside, A nozzle main shroud disposed on one side of the nozzle flange, a first main cylinder disposed radially inside the nozzle shroud, and forming a first main flow path between the nozzle shroud and the first main cylinder The installed first swirler and the upstream side of the first swirler when the flow direction of compressed air is used as a reference. Installation is, the gas turbine is provided comprising a grating module to the first injection side first swirler fuel supply received from the nozzle flange.

The nozzle assembly further includes a second main cylinder that is disposed inside the first main cylinder in a radial direction and forms a second main flow path between the first main cylinder.

The first swirler is interposed between the nozzle shroud and the second main cylinder, and the inner first swirl cylinder and the inner first swirl cylinder are engaged with the nozzle flange side end of the first main cylinder. And a first swirl vane installed between the nozzle shrouds.

The nozzle assembly is installed on the radially inner side of the grating module, and some of the fuel supplied from the nozzle flange is supplied to the grating module, and the other is mixed with the compressed air supplied and supplied to the second main channel. It further includes a second swirler.

The second swirler, the outer second swirl cylinder that the inner circumferential surface of the lattice module is in contact with the outer circumferential surface, is disposed radially inside the outer second swirl cylinder, one end is coupled to the nozzle flange and the other end is the The inner second swirl cylinder is coupled to the second main cylinder, and is installed between the outer second swirl cylinder and the inner second swirl cylinder, and includes a plurality of second swirl vanes communicating with the grid module.

The nozzle assembly is coupled to an end of the nozzle flange side of the outer circumferential surface of the grating module, and a first guide cylinder for guiding compressed air toward the first main flow path and an end of the nozzle flange side of the outer second swirl cylinder. It is combined, and further includes a second guide cylinder for guiding compressed air toward the second main flow path.

The grid modules, each having a different diameter, a plurality of grid rings are arranged so that the central axis is common to each other, and disposed between the plurality of grid rings, and spaced apart from each other along the circumferential direction of the grid ring In part, some of the fuel supplied from the radially inner side includes a plurality of lattice vanes that are injected to the first swirler side and the rest is supplied to the radially outer side.

The plurality of lattice vanes are arranged to stagger each other along the radial direction.

According to the nozzle assembly according to the present invention, a combustor and a gas turbine including the same, by injecting fuel from a lattice module disposed on the upstream side of the first swirler, and forming a vortex in the fuel and compressed air in the first swirler, Fuel and compressed air can be mixed more uniformly and injected into the combustion chamber.

1 is a cross-sectional view showing a gas turbine according to the present invention.
FIG. 2 is a cross-sectional view of the combustor shown in FIG. 1.
3 is a cross-sectional view of the nozzle assembly shown in FIG. 2.
4 is a perspective view of the first swirler shown in FIG. 3.
FIG. 5 is a perspective view of a part of the second swirler shown in FIG. 3 cut away.
6 is an enlarged view of part A of FIG. 3.
7 is a perspective view of the compartment ring shown in FIG. 3.

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 nozzle assembly according to the present invention, a combustor and a gas turbine including the same will be described with reference to the drawings.

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

The compressor 2 accommodates the compressor vane and compressor rotor inside the compressor casing, and the turbine 3 accommodates the turbine vane and turbine rotor inside the turbine casing. These compressor vanes and compressor rotors are arranged in a multi-stage along the flow direction of compressed air, and the turbine vanes and turbine rotors are also arranged in multiple stages along the flow direction of the combustion gas. At this time, the compressor 2, the internal space is reduced as it goes from the front (Front-stage) to the rear (Rear-stage) side so that the sucked air can be compressed, on the contrary, the turbine (3) is the combustion gas supplied from the combustor is expanded 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 2 and the turbine rotor located at the front end side of the turbine 3, the rotating torque generated by the turbine 3 is transmitted to the compressor 2 A torque tube as a torque transmission member is arranged. The torque tube may be composed of a plurality of torque tube discs having 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 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. More specifically, the respective compressor disks are aligned along the axial direction of each other with the central portion penetrated by the tie rod. In addition, each adjacent compressor disc is arranged such 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 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, 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 may be defined with a comprehensive name of a compressor stator to distinguish it from the compressor rotor.

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 side 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 gas turbine compressor may be provided with a desworler that serves as a guide for increasing the pressure of the fluid and adjusting the flow angle of the fluid entering the combustor to the design flow angle.

Referring to FIG. 2, the combustor 10 mixes and combusts the introduced compressed air with fuel to produce high-temperature, high-pressure combustion gas of high energy, and a heat-resistance limit that the combustor and turbine parts can withstand through an isothermal combustion process. Until the temperature of the combustion gas is increased.

The combustor 10 constituting the combustion system of the gas turbine 1 may be arranged in a plurality in a combustor casing formed in a cell shape, and a nozzle assembly 100 for injecting fuel and a combustion chamber It includes a liner (11), and a transition piece (12) that serves as a connection between the combustor (10) and the turbine (3).

Specifically, the liner 11 provides a combustion space in which fuel injected by the nozzle assembly 100 is mixed with compressed air of the compressor 2 and burned. The liner 11 is formed with a combustion chamber that provides a combustion space in which fuel mixed with air is combusted, and a liner annular flow path that encloses the combustion chamber and forms an annular space. In addition, a nozzle assembly 100 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 11 flows, and compressed air cooled by cooling a transition piece, which will be described later, also flows through it. As such, the compressed air flows along the outer wall portion of the liner 11, thereby preventing the liner 11 from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

At the rear end of the liner 11, the transition piece 12 is connected so that the combustion gas burned by the spark plug can be sent to the turbine 3 side. Like the liner, the transition piece 12 is formed with a transition piece annular flow path surrounding the inner space of the transition piece 12, and along the transition piece annular flow path to prevent damage due to high temperature of the combustion gas. The outer wall portion is cooled by flowing compressed air.

On the other hand, referring back to Figure 1, the high-temperature, high-pressure combustion gas from the combustor 10 is supplied to the above-described turbine (3). The high-temperature and high-pressure combustion gas supplied to the turbine 3 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, so that rotation torque is generated. The rotation 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 is basically similar to the structure of the compressor. That is, the turbine is also provided with a plurality of turbine rotors similar to the compressor rotor of the compressor. Accordingly, the turbine rotor also includes a turbine disk and a plurality of turbine blades radially disposed therefrom. Between the turbine blades, a plurality of turbine vanes are provided in the turbine casing annularly when the same stage is used as a reference, and the turbine vanes guide the flow direction of the combustion gas passing through the turbine blades. At this time, the turbine casing and the turbine vane may also be defined with a comprehensive name of a turbine stator to distinguish it from the turbine rotor.

3, the nozzle assembly 100 according to the present invention, the nozzle flange 110, the nozzle shroud 120, the first main cylinder 130, the second main cylinder 140, the first swirler ( 150), a second swirler 160, a grid module 170, a first guide cylinder 180 and a second guide cylinder 190.

The nozzle flange 110 is a disk-shaped member and receives fuel from the outside. The nozzle shroud 120 is a hollow cylindrical member, and is disposed on the liner 11 side of the nozzle flange 110.

The first main cylinder 130 is a hollow cylindrical member having a smaller diameter than the nozzle shroud 120. In addition, the first main cylinder 130 is disposed inside the nozzle shroud 120 and the nozzle shroud 120 in a radially inner direction so that the central axis thereof coincides with the nozzle shroud 120 and the first main between the nozzle shroud 120. The flow path 131 is formed. The second main cylinder 140 is a hollow cylindrical member having a smaller diameter than the first main cylinder 130. In addition, the second main cylinder 140 is disposed inside the first main cylinder 130 in a radial direction so that the first main cylinder 130 and its central axis coincide with the first main cylinder 130. A second main flow path 141 is formed between and.

3 and 4, the first swirler 150 is disposed between the nozzle shroud 120 and the second main cylinder 140. More specifically, the first swirler 150 may include an inner first swirl cylinder 151 and a plurality of first swirl vanes 152.

The inner first swirl cylinder 151 is a cylindrical member having the same diameter as the end of the nozzle flange 110 side of the first main cylinder 130, the nozzle flange of the first main cylinder 130 It is coupled to the (110) side end. At this time, a first swirl flow path 150a is formed between the inner first swirl cylinder 151 and the nozzle shroud 120, and the inner first swirl cylinder 151 and the second main cylinder 140 are formed. Between the second swirl flow path (160a) is formed.

The plurality of first swirl vanes 152 are installed on the outer circumferential surface of the inner first swirl cylinder 151, and are arranged to be spaced apart from each other along a circumferential direction of the inner first swirl cylinder 151. In addition, the plurality of first swirl vanes 152 form a vortex in the flow of compressed air and fuel flowing in from the upstream side, and uniformly mix the compressed air and fuel, and then make it into the first main flow path 131. To supply.

3 and 5, the second swirler 160 is installed at ends of the nozzle flange 110 of the first swirler 150 and the second main cylinder 140. More specifically, the second swirler 160 may include an outer second swirl cylinder 161, an inner second swirl cylinder 162, and a plurality of second swirl vanes 163.

The outer second swirl cylinder 161 is a cylindrical member having the same diameter as the inner first swirl cylinder 151 and is coupled to the inner first swirl cylinder 151. The inner second swirl cylinder 162 is a cylindrical member having the same diameter as the second main cylinder 140 and is coupled to the second main cylinder 140.

The plurality of second swirl vanes (163) is installed between the outer second swirl cylinder (161) and the inner second swirl cylinder (162), and the circumferential direction of the inner second swirl cylinder (162). It is arranged to be spaced apart from each other. In addition, the plurality of second swirl vanes 163 form a vortex in the flow of compressed air and fuel flowing in from the upstream side, and then uniformly mix the compressed air and fuel, and then make them into the second main flow path 141. To supply.

5 and 6, the inner second swirl cylinder 162 is formed with a fuel flow groove 162a extending along the longitudinal direction of the inner second swirl cylinder 162. In addition, the plurality of second swirl vanes 163 communicate with the grid module 170, respectively. The fuel supplied to the nozzle flange 110 is supplied to the second swirl vane 163 along the fuel flow groove 162a. And the fuel supplied to the second swirl vane 163 is injected into the second swirl channel 160a or is supplied to the grid module 170 and injected into the first swirl channel 150a.

3 and 7, the grid module 170 is disposed on the upstream side of the first swirler 150 and is disposed on the radially outer side of the second swirler. And the grid module 170, by injecting the fuel supplied from the second swirler 160 into the first swirl flow path (150a), the compressed air and fuel introduced from the upstream side together with the plurality of first While passing through the swirl vane (152) to be uniformly mixed with each other.

More specifically, the grid module 170 may include a plurality of grid rings 171 and a plurality of grid vanes 172. The plurality of lattice rings 171 are annular members having different diameters, and the central axes are arranged to be common to each other. The plurality of lattice vanes 172 are disposed between the plurality of lattice rings 171 and spaced apart from each other along the circumferential direction of the lattice rings 171. And the plurality of lattice vanes 172, some of the fuel supplied from the second swirler 160 is injected into the first swirl passage (150a), the rest of the lattice vane 172 on the radially outer side To supply.

As described above, the fuel injected from the grid module 170 disposed on the upstream side of the first swirl vane 152 is mixed with the compressed air introduced to the upstream side and passes through the first swirl vane 152, so that the In comparison, the compressed air and the fuel can be mixed more uniformly than the fuel injected from the first swirl vane and flowed to the first main channel 131. Accordingly, the nozzle assembly 100 according to the present invention can further improve the combustion efficiency of the liner 11 in the combustion chamber.

On the other hand, the plurality of grid vanes 172, as shown in Figure 7, may be arranged to stagger with each other along the radial direction. In this case, the spaces inside the grid module 170 partitioned by the plurality of grid vanes 172 are also formed to be staggered, and compressed air introduced into the upstream side of the grid module 170 is compressed into the plurality of grid vanes. While passing through the interior spaces partitioned by 172, the fuel injected from the plurality of grid vanes 172 is mixed more uniformly.

Referring to FIG. 3 again, the first guide cylinder 180 of the plurality of grating rings 171 has the largest diameter and is the outermost of the grating rings 171 when based on the radial direction. It is coupled to the nozzle flange 110 side end. In addition, the first guide cylinder 180 guides compressed air supplied from the compressor 2 to the first main flow path 131. The second guide cylinder 190 is coupled to the nozzle flange 110 side end of the outer second swirl cylinder 161. In addition, the second guide cylinder 190 guides compressed air supplied from the compressor 2 to the second main flow path 141 side. In this case, the first swirl flow path 150a may be formed to extend between the first guide cylinder 180 and the second guide cylinder 190. In addition, the second swirl flow path 160a may include: It may be formed to extend between the second guide cylinder 190 and the inner second swirl cylinder 162.

As described above, in the nozzle assembly 100 according to the present invention, compressed air and fuel flowing along the first swirl flow path 150a are mixed by the plurality of first swirl vanes 152 to form the first main flow path. Compressed air and fuel flowing through (131) and flowing along the second swirl flow passage (160a) are mixed by the plurality of second swirl vanes (163) and flowed into the second main flow passage (141). Compressed air and fuel introduced into the nozzle assembly 100 may be mixed in two independent flow paths and injected into the combustion chamber of the liner 11.

Accordingly, according to the nozzle assembly 100 according to the present invention, it is possible to make the compressed air and the fuel more uniformly mixed, as compared to the case where only one flow path through which compressed air and fuel flows is provided in the nozzle assembly. In addition, according to this, according to the nozzle assembly 100 according to the present invention, it is possible to further improve the combustion efficiency in the combustion chamber of the liner 11 compared to the prior art.

On the other hand, the nozzle assembly 100, the first main cylinder 130 and the end of the liner 11 side of the second main cylinder 140, the liner 11 side of the nozzle shroud 120 Compared to the end, it may be installed to be more indented toward the nozzle flange (110). In this case, the mixture of compressed air and fuel flowing along the first main flow path 131 is compressed air flowing along the second main flow path 141 at the outlet side of the second main flow path 141. After being mixed with the mixture of fuels and injected into the combustion chamber of the liner 11, compressed air and fuel can be mixed more uniformly.

Further, the first swirl vane 152 and the second swirl vane 163, along the flow direction of the compressed air, are the circumferences of the inner first swirl cylinder 151 and the inner second swirl cylinder 162, respectively. It may be formed in a shape bent in the direction. In this case, a mixture of compressed air and fuel flowing along the first swirl flow path 150a and the second swirl flow path 160a may include the first swirl vane 152 and the second swirl vane 163. The inner first swirl cylinder 151 and the inner second swirl cylinder 162 flow along a circumferential direction along the surface to be more uniformly mixed.

1: Gas turbine 2: Compressor
3: Turbine 10: Combustor
11: Liner 12: Transition Piece
100: nozzle assembly 110: nozzle flange
120: nozzle shroud 130: the first main cylinder
140: second main cylinder 150: first swirler
160: second swirler 170: grid module
180: first guide cylinder 190: second guide cylinder

Claims (24)

In the nozzle assembly for mixing the compressed air supplied from the compressor of the gas turbine and the fuel supplied from the outside to inject into the combustion chamber of the gas turbine combustor,
A nozzle flange supplied with fuel from the outside;
A nozzle shroud disposed on one side of the nozzle flange;
A first main cylinder disposed in the radially inner side of the nozzle shroud and forming a first main flow path between the nozzle shroud;
A first swirler installed in the first main cylinder; And
A nozzle assembly including a grid module installed on an upstream side of the first swirler when the compressed air is flowed as a reference, and injecting fuel supplied from the nozzle flange to the first swirler. The method according to claim 1,
The nozzle assembly further includes a second main cylinder disposed in the radially inner side of the first main cylinder and forming a second main flow path between the first main cylinder. The method according to claim 2,
The first swirler,
An inner first swirl cylinder interposed between the nozzle shroud and the second main cylinder, and coupled to an end of the nozzle flange side of the first main cylinder;
A nozzle assembly including a first swirl vane installed between the inner first swirl cylinder and the nozzle shroud. The method according to claim 2,
A second swirler that is installed on the radially inner side of the grid module, supplies some of the fuel supplied from the nozzle flange to the grid module, and mixes the rest with the compressed air supplied and supplies it to the second main channel. Further comprising a nozzle assembly. The method according to claim 4,
The second swirler,
An outer second swirl cylinder in contact with the inner circumferential surface of the grid module on the outer circumferential surface,
An inner second swirl cylinder having one end coupled to the nozzle flange and the other end coupled to the second main cylinder, which is disposed radially inside the outer second swirl cylinder;
A nozzle assembly including a plurality of second swirl vanes installed between the outer second swirl cylinder and the inner second swirl cylinder and communicating with the grid module. The method according to claim 5,
A first guide cylinder coupled to an end of the nozzle flange side of the outer circumferential surface of the grid module and guiding compressed air toward the first main flow path;
A nozzle assembly further comprising a second guide cylinder coupled to an end of the nozzle flange side of the outer second swirl cylinder and guiding compressed air toward the second main flow path. The method according to claim 1,
The grid module,
A plurality of lattice rings, each having a different diameter, and having a central axis in common with each other,
It is disposed between the plurality of grating rings, and arranged to be spaced apart from each other along the circumferential direction of the grating rings, and some of the fuel supplied from the radial inside is injected to the first swirler side, and the others are radially outward. Nozzle assembly including a plurality of grid vanes to supply. The method according to claim 7,
The plurality of grid vanes, the nozzle assembly is arranged to be staggered with each other along the radial direction. In the combustor for mixing the compressed air supplied from the compressor of the gas turbine and the fuel supplied from the outside to burn,
A nozzle assembly for mixing and supplying the supplied fuel and compressed air;
A liner having a combustion chamber in which a mixture of fuel and compressed air injected from the nozzle assembly is burned; And
It comprises a transition piece receiving the combustion gas generated from the combustion chamber,
The nozzle assembly,
Nozzle flange to receive fuel from the outside,
A nozzle shroud disposed on one side of the nozzle flange,
A first main cylinder disposed radially inside the nozzle shroud and forming a first main flow path between the nozzle shroud,
A first swirler installed in the first main cylinder,
A combustor including a grid module installed on the upstream side of the first swirler when the compressed air is flowed as a reference, and injecting fuel supplied from the nozzle flange to the first swirler. The method according to claim 9,
The nozzle assembly, the combustor further comprises a second main cylinder disposed in the radially inner side of the first main cylinder and forming a second main flow path between the first main cylinder. The method according to claim 10,
The first swirler,
An inner first swirl cylinder interposed between the nozzle shroud and the second main cylinder, and coupled to an end of the nozzle flange side of the first main cylinder;
A combustor comprising a first swirl vane installed between the inner first swirl cylinder and the nozzle shroud. The method according to claim 10,
The nozzle assembly is installed on the radially inner side of the grating module, and some of the fuel supplied from the nozzle flange is supplied to the grating module, and the other is mixed with the compressed air supplied and supplied to the second main channel. A combustor further comprising a second swirler. The method according to claim 12,
The second swirler,
An outer second swirl cylinder in contact with the inner circumferential surface of the grid module on the outer circumferential surface,
An inner second swirl cylinder having one end coupled to the nozzle flange and the other end coupled to the second main cylinder, which is disposed radially inside the outer second swirl cylinder;
A combustor installed between the outer second swirl cylinder and the inner second swirl cylinder and including a plurality of second swirl vanes communicating with the grid module. The method according to claim 13,
The nozzle assembly,
A first guide cylinder coupled to an end of the nozzle flange side of the outer circumferential surface of the grid module and guiding compressed air toward the first main flow path;
A combustor further comprising a second guide cylinder coupled to an end of the nozzle flange side of the outer second swirl cylinder and guiding compressed air toward the second main flow path. The method according to claim 9,
The grid module,
A plurality of lattice rings, each having a different diameter, and having a central axis in common with each other,
It is disposed between the plurality of grating rings, and arranged to be spaced apart from each other along the circumferential direction of the grating rings, and some of the fuel supplied from the radial inside is injected to the first swirler side, and the others are radially outward. Combustor comprising a plurality of grid vanes to supply. The method according to claim 15,
The plurality of lattice vanes, combustors arranged to be staggered with each other along the radial direction. A compressor that compresses air supplied from the outside;
A combustor that mixes and compresses compressed air supplied from the compressor and fuel supplied from the outside; And
It includes a turbine for passing through the combustion gas supplied from the combustor to generate power for generating electricity,
The combustor,
A nozzle assembly that mixes and supplies the supplied fuel and compressed air, and
A liner having a combustion chamber in which a mixture of fuel and compressed air injected from the nozzle assembly is burned;
It includes a transition piece receiving the combustion gas generated from the combustion chamber,
The nozzle assembly,
Nozzle flange to receive fuel from the outside,
A nozzle shroud disposed on one side of the nozzle flange,
A first main cylinder disposed radially inside the nozzle shroud and forming a first main flow path between the nozzle shroud,
A first swirler installed in the first main cylinder,
Gas turbine is installed on the upstream side of the first swirler when based on the flow direction of the compressed air, and includes a grating module for injecting the fuel supplied from the nozzle flange to the first swirler side. The method according to claim 17,
The nozzle assembly, the gas turbine is disposed in the radially inner side of the first main cylinder, further comprising a second main cylinder forming a second main flow path between the first main cylinder. The method according to claim 18,
The first swirler,
An inner first swirl cylinder interposed between the nozzle shroud and the second main cylinder, and coupled to an end of the nozzle flange side of the first main cylinder;
A gas turbine including a first swirl vane installed between the inner first swirl cylinder and the nozzle shroud. The method according to claim 18,
The nozzle assembly is installed on the radially inner side of the grating module, and some of the fuel supplied from the nozzle flange is supplied to the grating module, and the other is mixed with the compressed air supplied and supplied to the second main channel. Gas turbine further comprising a second swirler. The method according to claim 20,
The second swirler,
An outer second swirl cylinder in contact with the inner circumferential surface of the grid module on the outer circumferential surface,
An inner second swirl cylinder having one end coupled to the nozzle flange and the other end coupled to the second main cylinder, which is disposed radially inside the outer second swirl cylinder;
A gas turbine including a plurality of second swirl vanes which are installed between the outer second swirl cylinder and the inner second swirl cylinder and communicate with the grid module. The method of claim 21,
The nozzle assembly,
A first guide cylinder coupled to an end of the nozzle flange side of the outer circumferential surface of the grid module and guiding compressed air toward the first main flow path;
A gas turbine further comprising a second guide cylinder coupled to the nozzle flange side end of the outer second swirl cylinder and guiding compressed air toward the second main flow path. The method according to claim 17,
The grid module,
A plurality of lattice rings, each having a different diameter, and having a central axis in common with each other,
It is disposed between the plurality of grating rings, and arranged to be spaced apart from each other along the circumferential direction of the grating rings, and some of the fuel supplied from the radial inside is injected to the first swirler side, and the others are radially outward. A gas turbine comprising a plurality of grid vanes to supply. The method according to claim 23,
The plurality of lattice vanes, gas turbines arranged to be staggered with each other along a radial direction.

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