KR102437976B1 - Nozzle assembly, Combustor and Gas turbine comprising the same - Google Patents

Abstract

The present invention provides a nozzle assembly provided in a combustor of a gas turbine to inject fuel and compressed air supplied from a fuel injector into a combustion chamber of the combustor, comprising: a nozzle body; an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and a swirler part installed in the injection nozzle and guiding the flow of the supplied compressed air, wherein the injection nozzle has a first flow path formed therein, and fuel and compressed air supplied from the outside are supplied from the fuel injector A first nozzle tube and a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied. and a nozzle assembly, a combustor, and a gas turbine including the same provided in the second flow path.

Description

Nozzle assembly, Combustor and Gas turbine comprising the same

The present invention relates to a nozzle assembly, a combustor, and a gas turbine including the same, and more particularly, to a nozzle assembly provided in the combustor of the gas turbine and injecting fuel and compressed air into a combustion chamber of the combustor, and compressed air supplied from the compressor. The present invention relates to a combustor for mixing and burning fuel supplied from a fuel injector and supplying the generated combustion gas to a turbine, and a gas turbine including the same.

A turbomachine refers to a device for generating 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. Such turbomachines 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 the 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 the 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.

Meanwhile, in the case of a gas turbine among turbomachines, hydrogen may be used as a fuel. In such a hydrogen gas turbine, due to the nature of hydrogen combustion, a flame generated when a mixture of hydrogen and compressed air is combusted in the combustion chamber of the combustor is attached to the injection nozzle, and the flame is directed toward the turbine. There is a problem that the phenomenon of backfire / flash back occurs without proceeding.

The technology that is the background of the present invention is disclosed in Korean Patent No. 10-1882107 (registered on July 19, 2019).

The present invention has been created to solve the above problems, and includes a swirler part for injecting compressed air into the central part of the combustion chamber in the second flow path of the combustion assembly and inserting the downstream end of the second nozzle tube of the combustion assembly to the inside. An object of the present invention is to provide a nozzle assembly, a combustor, and a gas turbine including the same, which can prevent a flashback phenomenon in which the flame generated in the combustion chamber of the combustor sticks to the injection nozzle or goes backwards by having an inclined shape.

In order to achieve the above object, the present invention provides a nozzle assembly provided in a combustor of a gas turbine to inject fuel and compressed air supplied from a fuel injector into a combustion chamber of the combustor, comprising: a nozzle body; an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and a swirler part installed in the injection nozzle and guiding the flow of the supplied compressed air, wherein the injection nozzle has a first flow path formed therein, and fuel and compressed air supplied from the outside are supplied from the fuel injector A first nozzle tube and a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied. and a nozzle assembly provided in the second flow path.

In addition, the present invention provides a combustor for mixing compressed air supplied from a compressor of a gas turbine and fuel supplied from a fuel injector, and supplying the generated combustion gas to a turbine of a gas turbine, comprising: a nozzle casing; a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted; a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and a nozzle assembly installed inside the nozzle casing and configured to inject fuel and compressed air into the combustion chamber, wherein the nozzle assembly includes: a nozzle body; an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and a swirler part installed in the injection nozzle and guiding the flow of the supplied compressed air, wherein the injection nozzle has a first flow path formed therein, and fuel and compressed air supplied from the outside are supplied from the fuel injector A first nozzle tube and a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied. and the swirler unit provides a combustor provided inside the second flow path.

In addition, the present invention is a compressor for compressing the air introduced from the outside; a combustor for mixing the compressed air supplied from the compressor with the fuel supplied from the fuel injector; and a turbine for generating power for power generation by passing the combustion gas supplied from the combustor to the inside, wherein the combustor includes: a nozzle casing; a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted; a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and a nozzle assembly installed inside the nozzle casing and configured to inject fuel and compressed air into the combustion chamber, wherein the nozzle assembly includes: a nozzle body; an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and a swirler part installed in the injection nozzle and guiding the flow of the supplied compressed air, wherein the injection nozzle has a first flow path formed therein, and fuel and compressed air supplied from the outside are supplied from the fuel injector A first nozzle tube and a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied. and the swirler unit provides a gas turbine provided inside the second flow path.

According to the nozzle assembly, the combustor, and the gas turbine including the same according to the present invention, the injection nozzle provided in the nozzle assembly is designed in a double-tube structure composed of a first nozzle tube and a second nozzle tube, and a mixture of fuel and compressed air and Compressed air is separated from each other inside the injection nozzle, and is injected into the combustion chamber of the combustor. The mixture of fuel and compressed air can be combusted at a place more distant to the downstream side compared to the conventional one, and the flame holding phenomenon or flashback phenomenon in the injection nozzle is prevented by preventing the flame from sticking to the outer wall of the injection nozzle can do.

1 is a cross-sectional view showing a gas turbine according to the present invention.
FIG. 2 is an enlarged view of a part of a nozzle assembly provided in the combustor shown in FIG. 1 as a first embodiment of the present invention.
3 is an enlarged view illustrating a nozzle assembly provided in a combustor according to a second embodiment of the present invention.
4 is an enlarged view of a nozzle assembly provided in a combustor according to a third embodiment of the present invention.
5 is an enlarged view illustrating a nozzle assembly provided in a combustor according to a fourth embodiment of the present invention.
FIG. 6 is a view schematically illustrating a first swinger assembly provided inside the second flow path shown in FIG. 2 .
FIG. 7 is a view schematically illustrating a second swinger assembly provided in the second flow path illustrated in FIG. 2 .

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the accompanying drawings. Prior to this, the terms or words used in the present specification and claims should not be construed as being limited to conventional or dictionary meanings, and the inventor should properly understand the concept of the term in order to best describe his invention. Based on the principle that it can be defined, it should be interpreted as meaning and concept consistent with the technical idea of the present invention.

Referring to FIG. 1 , a gas turbine 100 according to the present invention includes a compressor 110 , a combustor 1000 , and a turbine 120 . Based on the flow direction of the gas (compressed air or combustion gas), the compressor 110 is disposed on the upstream side of the gas turbine 100 and the turbine 120 is disposed on the downstream side, and the compressor 110 and the turbine 120 ) between the combustor 1000 is disposed.

The compressor 110 accommodates the compressor vane and the compressor rotor in the compressor casing, and the turbine 120 accommodates the turbine vane and the turbine rotor in the turbine casing. The compressor vanes and the compressor rotor are arranged in multi-stages along the flow direction of the compressed air, and the turbine vanes and the turbine rotor are also arranged in multiple stages along the flow direction of the combustion gas.

At this time, the compressor 110 decreases the internal space from the front-stage to the rear-stage side so that the sucked air can be compressed, and the turbine 120 is the combustion gas supplied from the combustor 1000 . It is preferable to design a structure in which the inner space increases from the front end to the rear end side so that the inner space can be expanded.

On the other hand, between the compressor rotor located on the rearmost end side of the compressor 110 and the turbine rotor located on the most forward end side of the turbine 120 , the rotational torque generated in the turbine 120 is transferred to the compressor 110 . A torque tube as a torque transmitting member is disposed. 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 axially with each other with a central portion pierced by the tie rods. In addition, each of the adjacent compressor disks is 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 the 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 central portion of the plurality of compressor disks and a turbine disk to be described later, and one end is fastened in the compressor disk located at the frontmost end 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 portion 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 in FIG. 1, the compressor of the gas turbine may be provided with a deswirler serving as a guide blade 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 100 mixes and combusts the introduced compressed air with fuel supplied from a fuel injector (not shown) to produce high-energy, high-temperature, high-pressure combustion gas. It raises the temperature of the combustion gas to the limit of heat resistance.

A plurality of combustors 1000 constituting the combustion system of the gas turbine 100 may be arranged in a combustor casing (not shown) having a cell shape, and a nozzle casing 1100 and a liner 1200 and , and a transition piece 1300 and nozzle assemblies 1400, 2400, 3400, and 4400.

The nozzle assemblies 1400 , 2400 , 3400 , 4400 are disposed inside the nozzle casing 1100 and inject fuel and compressed air, and the liner 1200 is the turbine 120 of the nozzle casing 1100 . The combustion chamber 1210 is connected to the side end, and a mixture of fuel supplied from a fuel injector (not shown) and compressed air supplied from the compressor 110 is combusted inside the liner 1200 is formed.

The transition piece 1300 is connected to the end of the liner 1200 on the turbine 120 side, and supplies the combustion gas generated in the combustion chamber 1210 to the turbine 120 .

Specifically, the liner 1200 provides a combustion space in which the fuel injected by the nozzle assemblies 1400 , 2400 , 3400 , and 4400 is mixed and combusted. The liner 1200 has a combustion chamber 1210 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 1210 . In addition, it is preferable that nozzle assemblies 1400 , 2400 , 3400 , and 4400 for injecting fuel are coupled to the front end of the liner 1200 , and an igniter (not shown) is coupled to the sidewall.

In the liner annular flow path, compressed air introduced through a plurality of holes provided in the outer wall of the liner 1200 flows, and the compressed air that has cooled the transition piece 1300, which will be described later, also flows through it. As the compressed air flows along the outer wall portion of the liner 1200 as described above, it is possible to prevent the liner 1200 from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

A transition piece 1300 is connected to the rear end of the liner 1200 so as to send the combustion gas burned by the spark plug to the turbine side. Like the liner 1200 , the transition piece 1300 has a transition piece annular flow path surrounding the inner space of the transition piece 1300 , and the transition piece annular to prevent damage due to the high temperature of the combustion gas. The outer wall portion is cooled by the compressed air flowing along the flow path.

On the other hand, the high-temperature, high-pressure combustion gas from the combustor 1000 is supplied to the turbine 120 described above. The high-temperature and high-pressure combustion gas supplied to the turbine 120 expands while passing through the turbine 120 , and accordingly, an impulse and reaction force are applied to the turbine blades 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 120 is basically similar to the structure of the compressor 110 . That is, the turbine 120 is also provided with a plurality of turbine rotors similar to the compressor rotor of the compressor 110 . The turbine rotor thus also comprises a turbine disk and a plurality of turbine blades arranged radially therefrom. Also between the turbine blades, a plurality of turbine vanes installed in an annular shape on the turbine casing are provided on the same stage as a reference, and the turbine vanes guide the flow direction of the combustion gas passing through the turbine blades. In this case, the turbine casing and the turbine vane may also be defined as a generic name of a turbine stator in order to distinguish them from the turbine rotor.

2 to 5 , the nozzle assemblies 1400 , 2400 , 3400 , and 4400 include a nozzle body 1410 , a spray nozzle 1420 , and a swirler unit 1430 . The nozzle body 1410 is formed in a disk shape, and only a part thereof is shown in FIGS. 2 to 5 . The nozzle body 1410 is disposed on an upstream side of the combustion chamber 1210 of the lighter 1200 based on the flow direction of the combustion gas. Therefore, the nozzle body 1410 separates the internal space of the combustion chamber 1210 and the nozzle casing 1100 from each other.

The injection nozzle 1420 is installed in the nozzle body 1410, and injects fuel and compressed air into the combustion chamber 1210, and the injected fuel may be hydrogen. In addition, the injection nozzle 1420 is provided in plurality and may be inserted into the nozzle body 1410, respectively. The injection nozzle 1420 includes a first nozzle tube 1421 and a second nozzle tube 1422 . The first nozzle tube 1421 is a cylindrical member having a first flow path 1421a formed therein. The second nozzle tube 1422 is a cylindrical member disposed to surround the first nozzle tube 1421 from the radially outer side of the first nozzle tube 1421 , and is disposed between the first nozzle tube 1421 and the second nozzle tube 1421 . A second flow path 1422a is formed in the .

6 and 7, the swirler unit 1430 is installed in the second flow path 1422 of the injection nozzle 1420 to guide the flow of compressed air supplied to the second flow path 1422a. The swinger part 1430 includes a first swinger assembly 1431 and a second swinger assembly 1432 .

The first swinger assembly 1431 is provided on the upstream side of the hub with respect to the flow direction of the compressed air flowing in the second flow passage 1422a, and the second swinger assembly 1432 is It is provided on the tip side of the second flow path 1422a that is spaced apart from the first swinger assembly 1431 in the downstream side. The first swinger assembly 1431 and the second swinger assembly 1432 include a plurality of first airfoils 1431a and second airfoils 1432a provided to be spaced apart from each other.

The first airfoil 1431a of the first swinger assembly 1431 is inclined in the second flow path 1422a to have a larger angle than the second airfoil 1432a of the second swinger assembly 1432. Preferably, the second airfoil 1432a of the second swirler assembly 1432 has an upright shape rather than an inclined shape in the second flow path 1422a, so that a mixture of fuel and compressed air is produced. Compared to the prior art, it is possible to burn in a place more spaced to the downstream side, and the flame does not stick to the outer wall of the injection nozzle 1410, thereby preventing the occurrence of a backfire.

Hereinafter, first to fourth embodiments of the present invention will be described with reference to FIGS. 2 to 5 .

Referring to FIG. 2 , in the nozzle assembly 1400 according to the first embodiment of the present invention, the first nozzle tube 1421 and the second nozzle tube 1422 are end portions downstream from the nozzle body 1410 . The protruding lengths are different from each other, and the end of the second nozzle tube 1422 protrudes further downstream than the end of the first nozzle tube 1421 .

An inlet hole 1422b through which compressed air is introduced from the outside is formed in the second nozzle tube 1422 , and the first nozzle tube 1421 is provided in the second flow path 1422a of the second nozzle tube 1422 . ), a supply hole 1421b for supplying the compressed air flowing through the second flow path 1422a to the first flow path 1421a is formed. Comparing the positions of the supply hole 1421b and the inlet hole 1432b, it is preferable that the supply hole 1421b is located on the downstream side from the nozzle body 1410 than the inlet hole 1422b.

The compressed air supplied from the compressor 110 to the combustor 1000 is introduced into the upstream side of the second flow path 1422a, and a portion of the compressed air introduced into the second flow path 1422a is supplied through the supply hole 1421b. ) flows into the upstream side of the first flow path 1421a and flows downstream along the first flow path 1421a and the second flow path 1422a, that is, toward the combustion chamber 1210 side. And the fuel supplied to the combustor 1000 from the outside through a fuel injector (not shown) is supplied to the first flow path 1421a, and the fuel supplied to the first flow path 1421a is the first flow path. After mixing with the compressed air introduced from the upstream side of 1421a, it is injected into the combustion chamber 1210 side. The first nozzle tube 1421 has a cone shape whose diameter decreases downstream from the first nozzle tube 1421 , or the downstream end of the first nozzle tube 1421 is the inner side of the first nozzle tube 1421 . It is preferable to have an inclined shape.

According to the first embodiment of the present invention as described above, the mixture of fuel and compressed air injected into the combustion chamber 1210 along the first flow path 1421a may have the shape of the first nozzle tube 1421 and the By the compressed air injected into the combustion chamber 1210 along the second flow path 1422a, it can be combusted at a position more spaced to the downstream side than in the prior art, and thus the flame holding phenomenon or backfire in the injection nozzle 1420 phenomenon can be prevented.

Referring to FIG. 3 , in the nozzle assembly 2400 according to the second embodiment of the present invention, the first nozzle tube 2431 and the second nozzle tube 2432 are end portions downstream from the nozzle body 2410 . The protruding lengths up to are different from each other, and the end of the second nozzle tube 2432 protrudes further downstream than the end of the first nozzle tube 2431 .

A supply hole 2431b and an inlet hole 2432b are formed in the first nozzle tube 2431 and the second nozzle tube 2432, respectively, and a supply hole 2431b, an inlet hole 2432b, and the first nozzle are formed. Since the tube 2431 and the second nozzle tube 2432 have been described in detail in the nozzle assembly 1400 according to the first embodiment of the present invention, a description of overlapping parts will be omitted.

The downstream end of the second nozzle tube 2432 has an inwardly inclined shape of the second nozzle tube 2432 , and the first nozzle tube 1431 moves downstream from the first nozzle tube 1410 . Preferably, a cone shape having a reduced diameter or a downstream end of the first nozzle tube 1431 has an inwardly inclined shape of the first nozzle tube 1431 .

According to the second embodiment of the present invention as described above, the mixture of fuel and compressed air injected into the combustion chamber 1210 along the first flow path 2431a may include the shape of the first nozzle tube 2431 and the Due to the shape of the second nozzle tube 2432, the compressed air injected into the central portion of the combustion chamber 1210 along the second flow path 2422a can be combusted at a position more distant from the downstream side than in the prior art. , therefore, it is possible to prevent a flame holding phenomenon or a backfire phenomenon from occurring in the injection nozzle 1420 .

Referring to FIG. 4 , in the nozzle assembly 3400 according to the third embodiment of the present invention, only the shape of the nozzle assembly 2400 and the second nozzle tube 3432 according to the second embodiment of the present invention is different. An insertion protrusion 3432c protruding inward of the second nozzle tube 3432 is preferably provided on a downstream side of the second nozzle tube 3432 of the nozzle assembly 3400 according to the third embodiment of the present invention.

Due to the shape of the second nozzle tube 3432, the compressed air injected into the central portion of the combustion chamber 1210 along the second flow path 3422a can be combusted at a position more distant from the downstream side than in the prior art. Accordingly, it is possible to prevent a flame holding phenomenon or a backfire phenomenon from occurring in the injection nozzle 1420 .

Referring to FIG. 5 , the nozzle assembly 4400 according to the fourth embodiment of the present invention is the same as the nozzle assembly 1400 according to the first embodiment, and the second nozzle tube 4432 of the nozzle assembly 4400 is ), a crushing chain 4422c for spraying the cooling air supplied from the outside to the second flow path 4422a is formed on the downstream side. A plurality of the grinding slits 4422c are formed to have a straight shape along the circumferential direction of the second nozzle tube 4432 , and cooling air is supplied through the grinding slits 4422c inside the second nozzle tube 4432 . As it is supplied to the , it can be combusted at a position more spaced apart from the downstream side than in the prior art by the compressed air injected into the central portion of the combustion chamber 1210 along the second flow path 4422a, and thus the injection nozzle 1420. It is possible to prevent flame holding or backfire from occurring.

2 to 5 , the flow cross-sectional area of the fluid in the first flow path 1421a and the second flow path 1422a may be different from each other based on one injection nozzle 1420, and one injection nozzle The radial thicknesses of the walls of the first nozzle tube 1421 and the second nozzle tube 1422 based on the reference numeral 1420 may also be formed to be different from each other. In addition, the area of each of the first passage 1421a and the second passage 1422a of the plurality of injection nozzles 1420 is also formed differently for each injection nozzle 1420, and each of the first nozzles of the plurality of injection nozzles 1420 is formed differently. The radial thickness of the tube 1421 and the wall of the second nozzle tube 1422 may also be formed differently for each injection nozzle 1420 .

Although the present invention has been described with reference to the embodiment shown in the drawings, which is only exemplary, those of ordinary skill 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.

100: gas turbine 110: compressor
120: turbine 1000: combustor
1100: nozzle casing 1200: liner
1210: combustion chamber 1300: transition piece
1400, 2400, 3400, 4400 : Nozzle assembly
1410: nozzle body 1420: spray nozzle
1421: first nozzle tube 1422: second nozzle tube
1430: swivel part 1431: first swinger assembly
1432: second swinger assembly

Claims (24)

In the nozzle assembly provided in the combustor of the gas turbine to inject fuel and compressed air supplied from a fuel injector to the combustion chamber of the combustor,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
An inlet hole through which compressed air is introduced from the outside is formed in the second nozzle tube, the inlet hole is formed in an upstream side connected to the nozzle body in the second nozzle tube, and the second nozzle tube has the second nozzle tube. A nozzle assembly in which a supply hole for supplying compressed air moving to the flow path to the first flow path is formed.

delete In the nozzle assembly provided in the combustor of the gas turbine to inject fuel and compressed air supplied from a fuel injector to the combustion chamber of the combustor,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The swirler part,
a first swinger assembly provided on the upstream side of the hub based on the flow direction of the compressed air flowing in the second flow path;
and a second swinger assembly provided on a downstream tip side to be spaced apart from the first swinger assembly,
The nozzle assembly is provided to be inclined in the second flow path such that the first swinger assembly has a larger angle than the second swinger assembly.
In the nozzle assembly provided in the combustor of the gas turbine to inject fuel and compressed air supplied from a fuel injector to the combustion chamber of the combustor,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The first nozzle tube and the second nozzle tube have different protruding lengths from the nozzle body to the downstream end,
A nozzle assembly in which an end of the second nozzle tube protrudes further downstream than an end of the first nozzle tube.
5. The method according to claim 4,
The first nozzle tube is a nozzle assembly having a cone shape with a diameter decreasing downstream from the nozzle body.
5. The method according to claim 4,
The downstream end of the second nozzle tube has an inwardly inclined shape of the second nozzle assembly.
5. The method according to claim 4,
A nozzle assembly having an insertion protrusion protruding inward of the second nozzle tube at a downstream side of the second nozzle tube.
5. The method according to claim 4,
A nozzle assembly in which a crushing slit for spraying cooling air supplied from the outside into the inside of the second nozzle tube is formed on a downstream side of the second nozzle tube.
In a combustor for mixing compressed air supplied from a compressor of a gas turbine and fuel supplied from a fuel injector, and supplying the generated combustion gas to a turbine of a gas turbine,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
An inlet hole through which compressed air is introduced from the outside is formed in the second nozzle tube, the inlet hole is formed in an upstream side connected to the nozzle body in the second nozzle tube, and the second nozzle tube has the second nozzle tube. A combustor in which a supply hole for supplying compressed air moving to the flow path to the first flow path is formed.

delete In a combustor for mixing compressed air supplied from a compressor of a gas turbine and fuel supplied from a fuel injector, and supplying the generated combustion gas to a turbine of a gas turbine,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The swirler part,
a first swinger assembly provided on the upstream side of the hub based on the flow direction of the compressed air flowing in the second flow path;
and a second swinger assembly provided on a downstream tip side to be spaced apart from the first swinger assembly,
The combustor is provided to be inclined in the second flow path such that the first swinger assembly has a larger angle than the second swinger assembly.
In a combustor for mixing compressed air supplied from a compressor of a gas turbine and fuel supplied from a fuel injector, and supplying the generated combustion gas to a turbine of a gas turbine,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The first nozzle tube and the second nozzle tube have different protruding lengths from the nozzle body to the downstream end,
An end of the second nozzle tube protrudes further downstream than an end of the first nozzle tube.
13. The method of claim 12,
The first nozzle tube is a combustor having a cone shape with a diameter decreasing downstream from the nozzle body.
13. The method of claim 12,
The downstream end of the second nozzle tube has an inwardly inclined shape of the second nozzle tube.
13. The method of claim 12,
A combustor provided with an insertion protrusion protruding inward of the second nozzle tube on a downstream side of the second nozzle tube.
13. The method of claim 12,
A combustor in which a pulverization chain for injecting cooling air supplied from the outside into the inside of the second nozzle tube is formed on a downstream side of the second nozzle tube.
a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with the fuel supplied from the fuel injector; and
A turbine for generating power for power generation by passing the combustion gas supplied from the combustor to the inside,
the combustor,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
An inlet hole through which compressed air is introduced from the outside is formed in the second nozzle tube, the inlet hole is formed in an upstream side connected to the nozzle body in the second nozzle tube, and the second nozzle tube has the second nozzle tube. A gas turbine having a supply hole for supplying compressed air moving to the flow path to the first flow path.

delete a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with the fuel supplied from the fuel injector; and
A turbine for generating power for power generation by passing the combustion gas supplied from the combustor to the inside,
the combustor,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The swirler part,
a first swinger assembly provided on the upstream side of the hub based on the flow direction of the compressed air flowing in the second flow path;
and a second swinger assembly provided on a downstream tip side to be spaced apart from the first swinger assembly,
The gas turbine is inclined in the second flow path so that the first swinger assembly has a larger angle than the second swinger assembly.
a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with the fuel supplied from the fuel injector; and
A turbine for generating power for power generation by passing the combustion gas supplied from the combustor to the inside,
the combustor,
nozzle casing;
a liner connected to the turbine side end of the nozzle casing and having a combustion chamber in which a mixture of fuel and compressed air is combusted;
a transition piece connected to the turbine side end of the liner and supplying the combustion gas generated in the combustion chamber to the turbine; and
It is installed in the inside of the nozzle casing, comprising a nozzle assembly for injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body;
an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber; and
It is installed on the injection nozzle and includes a swirler part for guiding the flow of the supplied compressed air,
The spray nozzle is
a first nozzle tube having a first flow path formed therein and to which fuel and compressed air supplied from the outside are supplied from the fuel injector;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, a second flow path is formed between the first nozzle tube and a second nozzle tube to which compressed air supplied from the outside is supplied,
The swirler part is provided inside the second flow path,
The first nozzle tube and the second nozzle tube have different protruding lengths from the nozzle body to the downstream end,
An end of the second nozzle tube protrudes further downstream than an end of the first nozzle tube.
21. The method of claim 20,
The first nozzle tube is a gas turbine having a cone shape with a diameter decreasing downstream from the nozzle body.
21. The method of claim 20,
The downstream end of the second nozzle tube has an inwardly inclined shape of the second nozzle tube.
21. The method of claim 20,
A gas turbine having an insertion protrusion protruding inwardly of the second nozzle tube at a downstream side of the second nozzle tube.
21. The method of claim 20,
A gas turbine having a pulverization chain formed on a downstream side of the second nozzle tube for spraying cooling air supplied from the outside into the inside of the second nozzle tube.

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