KR102433706B1 - 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 and injecting fuel and compressed air into a combustion chamber of the combustor, comprising: a nozzle body; and an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber, wherein the injection nozzle includes a first nozzle tube having a first flow path formed therein, and a radius of the first nozzle tube. Provided are a nozzle assembly including a second nozzle tube disposed to surround the outside in a direction and having a second flow path formed between the first nozzle tube and the first nozzle tube, a combustor, and a gas turbine including the same.

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 a combustor of a gas turbine and injecting fuel and compressed air into a combustion chamber of the combustor, and compressed air supplied from a compressor It relates to a combustor for mixing and combusting with fuel and supplying the generated combustion gas to a turbine, and a gas turbine including the same.

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

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

Looking at a steam turbine among turbomachines, the steam turbine includes an evaporator and a turbine. The evaporator generates steam by heating water supplied from the outside. In the turbine, a plurality of turbine vanes and turbine blades are alternately disposed in a turbine casing, similarly to 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 present invention has been developed to solve the above problems, and it is an object of the present invention to provide a nozzle assembly, a combustor, and a gas turbine including the same for preventing a flame generated in a combustion chamber of a combustor from sticking to or going backwards on an injection nozzle There is this.

The present invention provides a nozzle assembly provided in a combustor of a gas turbine and injecting fuel and compressed air into a combustion chamber of the combustor, comprising: a nozzle body; and an injection nozzle installed in the nozzle body and injecting fuel and compressed air into the combustion chamber, wherein the injection nozzle includes a first nozzle tube having a first flow path formed therein, and a radius of the first nozzle tube. There is provided a nozzle assembly including a second nozzle tube disposed to surround the outside in a direction and having a second flow path formed between the first nozzle tube and the first nozzle tube.

In addition, the present invention provides a combustor for mixing compressed air supplied from a compressor of a gas turbine with fuel, 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 burned; 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 injecting fuel and compressed air into the combustion chamber, wherein the nozzle assembly includes a nozzle body and a nozzle body installed in the nozzle body, the fuel and compressed air into the combustion chamber and a jet nozzle for jetting air, wherein the jet nozzle includes a first nozzle tube having a first flow path formed therein, and disposed to surround the first nozzle tube from the outside in a radial direction, and It may include a second nozzle tube having a second flow path therebetween.

In addition, the present invention, a compressor for compressing the air introduced from the outside; a combustor mixing the compressed air supplied from the compressor with fuel and combusting it; and a turbine for generating power for power generation by passing the combustion gas supplied from the combustor to the inside, wherein the combustor is connected to a nozzle casing and an end of the turbine side of the nozzle casing, and a fuel therein a liner having a combustion chamber in which a mixture of and compressed air is combusted; a transition piece connected to the turbine side end of the liner and supplying combustion gas generated in the combustion chamber to the turbine; and a nozzle assembly for injecting fuel and compressed air into the combustion chamber, wherein the nozzle assembly includes a nozzle body and an injection nozzle installed on the nozzle body and injecting fuel and compressed air into the combustion chamber. wherein the injection nozzle includes a first nozzle tube having a first flow path formed therein, and is disposed to surround the first nozzle tube radially outwardly, and a second flow path is formed between the first nozzle tube and the first nozzle tube. A gas turbine including a second nozzle tube is provided.

The first nozzle tube includes a first communication hole, the second nozzle tube is disposed radially outside the first communication hole, and a second communication hole through which fuel flows from the outside is formed, and the injection The nozzle is installed in the second flow path, is connected to an outer circumferential surface of the first nozzle tube and an inner circumferential surface of the second nozzle tube so as to communicate with the first communication hole and the second communication hole, and a communication tube into which fuel is introduced. may further include.

The second nozzle tube may have a second communication hole through which fuel is introduced from the outside.

In the injection nozzle, a downstream end may protrude from the nozzle body to a downstream side based on a flow direction of fuel and compressed air flowing therein.

The first nozzle tube and the second nozzle tube may have different protruding lengths from the nozzle body to the downstream end, respectively.

A downstream end of the first nozzle tube may protrude more downstream than a downstream end of the second nozzle tube based on a flow direction of fuel and compressed air flowing therein.

A downstream end of the second nozzle tube may protrude more downstream than a downstream end of the first nozzle tube based on a flow direction of fuel and compressed air flowing therein.

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 to have a double pipe structure including a first nozzle tube and a second nozzle tube, and compressed air or fuel and compressed air of the mixture is separated from each other inside the injection nozzle and injected into the combustion chamber of the combustor, so that the mixture of fuel and compressed air is combusted at a place more separated downstream than in the prior art by the compressed air injected into the combustion chamber. It is possible to do so, and thus, it is possible to prevent a flame holding phenomenon or a flashback phenomenon from occurring in the injection nozzle.

1 is a cross-sectional view of a gas turbine according to the present invention.
FIG. 2 is a perspective view illustrating a part of a nozzle assembly provided in the combustor shown in FIG. 1 as a first embodiment of the present invention.
3 is a view showing a second embodiment of the present invention.
FIG. 4 is a front view of the nozzle assembly shown in FIG. 2 or FIG. 3 as a third embodiment of the present invention.
5 is a view showing a fourth embodiment of the present invention.

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

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

Referring to FIG. 1 , a gas turbine 10 according to the present invention includes a compressor 11 , a combustor 100 , and a turbine 12 . Based on the flow direction of the gas (compressed air or combustion gas), the compressor 11 is disposed on the upstream side of the gas turbine 10 and the turbine 12 is disposed on the downstream side. And the combustor 100 is disposed between the compressor 11 and the turbine 12 .

The compressor 11 accommodates the compressor vanes and the compressor rotor inside the compressor casing, and the turbine 12 accommodates the turbine vanes and the turbine rotor inside 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 internal space of the compressor 11 decreases from the front-stage to the rear-stage side so that the sucked air can be compressed, and the turbine 12, on the other hand, expands the combustion gas supplied from the combustor. It is designed in such a way that the inner space increases from the front end to the rear end.

On the other hand, between the compressor rotor located at the rearmost end side of the compressor 11 and the turbine rotor located at the frontmost end side of the turbine 12 , the rotational torque generated in the turbine 12 is transmitted to the compressor 11 . 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, a deswarler serving as a guide blade may be installed in the compressor of the gas turbine to adjust the flow angle of the fluid entering the combustor inlet to the design flow angle after increasing the pressure of the fluid.

The combustor 100 mixes and combusts the introduced compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas, and the temperature of the combustion gas up to the heat resistance limit that the combustor and turbine parts can withstand through the isostatic combustion process. will be raised

A plurality of combustors constituting the combustion system of the gas turbine 10 may be arranged in the combustor casing formed in the form of a cell, and the nozzle casing 110 and the nozzle casing 110 are disposed inside, A nozzle assembly 140, 240, 340, 440 for injecting fuel, a liner 120 forming the combustion chamber 121, and a transition piece 130 that is a connection between the combustor 100 and the turbine 12 includes a transition piece do.

Specifically, the liner 120 provides a combustion space in which the fuel injected by the nozzle assemblies 140 , 240 , 340 , and 440 is mixed with the compressed air of the compressor 11 and combusted. The liner 120 is formed with a combustion chamber providing a combustion space in which fuel mixed with air is combusted, and a liner annular passage forming an annular space while surrounding the combustion chamber. In addition, nozzle assemblies 140 , 240 , 340 , 440 for injecting fuel are coupled to the front end of the liner 120 , and an igniter 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 120 flows, and the compressed air that has cooled the transition piece 130 to be described later also flows through it. As the compressed air flows along the outer wall portion of the liner 120 as described above, it is possible to prevent the liner 120 from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

At the rear end of the liner 120 , the transition piece 130 is connected to send the combustion gas combusted by the spark plug to the turbine side. Like the liner 120 , the transition piece 130 has a transition piece annular flow path surrounding the inner space of the transition piece 130 , and the transition piece is 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 100 is supplied to the turbine 12 described above. The high-temperature and high-pressure combustion gas supplied to the turbine 12 expands while passing through the inside of the turbine 12 , 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 12 is basically similar to the structure of the compressor 11 . That is, the turbine 12 is also provided with a plurality of turbine rotors similar to the compressor rotor of the compressor 11 . 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 140 , 240 , 340 , and 440 include a nozzle body 141 and a spray nozzle 142 .

The nozzle body 141 is formed in a disk shape, and only a part thereof is shown in FIGS. 2 and 3 . The nozzle body 141 is disposed on the upstream side of the combustion chamber 121 of the liner 120 based on the flow direction of the combustion gas. Therefore, the nozzle body 141 separates the internal space of the combustion chamber 121 and the nozzle casing 110 from each other.

The injection nozzle 142 is installed in the nozzle body 141 and injects fuel and compressed air into the combustion chamber 121 . Here, the fuel may be hydrogen. And the injection nozzle 142 is provided in plurality and may be inserted into the nozzle body 141, respectively. The injection nozzle 142 includes a first nozzle tube 143 and a second nozzle tube 144 . The first nozzle tube 143 is a cylindrical member having a first flow path 143a formed therein. The second nozzle tube 144 is a cylindrical member disposed to surround the first nozzle tube 144 from the radially outer side of the first nozzle tube 144 , and the first nozzle tube 143 . A second flow path 144a is formed between the

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 140 according to the first embodiment of the present invention, in the first nozzle tube 143 , a first communication hole 143b is formed through the wall. In the second nozzle tube 144, a second communication hole 144b is formed through the wall. And the nozzle assembly 140 further includes a communication tube 145 . The communication tube 145 is installed in the second flow path 144a, and an inner end of the first nozzle tube 143 communicates with the first communication hole 143b based on the radial direction of the first communication tube 143b. It is connected to the outer circumferential surface of the nozzle tube 143, and on the inner circumferential surface of the second nozzle tube 144 so that the outer end communicates with the second communication hole 143b based on the radial direction of the first nozzle tube 143. Connected.

The compressed air supplied from the compressor 11 to the combustor 100 flows into the upstream side of the first flow path 143a and the second flow path 144a, and the first flow path 143a and the second flow path It flows downstream along 144a, that is, toward the combustion chamber 121 side. Then, the fuel supplied from the outside to the combustor 100 is introduced into the communication tube 145 through the second communication hole 144b, and then is supplied to the first flow path 143a. In addition, the fuel supplied to the first flow path 143a is mixed with the compressed air introduced from the upstream side of the first flow path 143a and then injected toward the combustion chamber 121 .

According to the first embodiment of the present invention, a mixture of fuel and compressed air injected into the combustion chamber 121 along the first flow path 143a is transferred to the combustion chamber along the second flow path 144a. Compressed air injected to 121 can be combusted at a position more spaced to the downstream side than in the prior art, and thus it is possible to prevent a flame holding phenomenon or a backfire phenomenon from occurring in the injection nozzle 142 .

Referring to FIG. 3 , in the nozzle assembly 240 according to the second embodiment of the present invention, in the second nozzle tube 144 , a second communication hole 144b is formed through the wall. Unlike the first embodiment of the present invention, in the second embodiment, a separate communication hole is not formed in the first nozzle tube 143 . And the fuel introduced into the second flow path 144a through the second communication hole 144b is mixed with the compressed air introduced into the second flow path 144a from the upstream side of the second flow path 144a. after being supplied to the combustion chamber 121 . In addition, only the compressed air introduced upstream flows through the first flow path 143a and is then injected into the combustion chamber 121 .

According to the second embodiment of the present invention, a mixture of fuel and compressed air injected into the combustion chamber 121 along the second flow path 144a is transferred to the combustion chamber along the first flow path 143a. Compressed air injected to 121 can be combusted at a position more spaced to the downstream side than in the prior art, and thus it is possible to prevent a flame holding phenomenon or a backfire phenomenon from occurring in the injection nozzle 142 .

4 and 5, in the nozzle assemblies 340 and 440 according to the third and fourth embodiments of the present invention, the injection nozzle 142 is based on the flow direction of the fuel and compressed air flowing therein. A downstream end may further protrude toward the combustion chamber 121 from the downstream surface of the nozzle body 141 . In addition, the first nozzle tube 143 and the second nozzle tube 144 may have different protruding lengths from the downstream surface of the nozzle body 141 to the downstream end, respectively.

Referring to FIG. 4 , in the nozzle assembly 340 according to the third embodiment of the present invention, the downstream end of the first nozzle tube 143 is more downstream than the downstream end of the second nozzle tube 144 . It may protrude further to the side. Referring to FIG. 5 , in the nozzle assembly 440 according to the fourth embodiment of the present invention, the downstream end of the second nozzle tube 144 is more downstream than the downstream end of the first nozzle tube 143 . It may protrude further to the side.

According to the third and fourth embodiments of the present invention as described above, the injection of fuel and compressed air is made at a position more spaced to the downstream side than the nozzle body 141, as well as compressed air and fuel-compressed air mixture The fuel-compressed air mixing efficiency and combustion efficiency in the combustion chamber 121 are improved, and the fuel-compressed air mixing efficiency and combustion efficiency in the combustion chamber 121 are improved, It is possible to prevent a flame holding phenomenon or a flashback phenomenon from occurring in the injection nozzle 142 .

Meanwhile, the third and fourth embodiments of the present invention described above can be applied to either the first embodiment of the present invention shown in FIG. 2 or the second embodiment of the present invention shown in FIG. 3 . That is, referring to FIGS. 4 and 5 , in the third and fourth embodiments of the present invention described above, a mixture of fuel and compressed air flows through the first flow path 143a, and the second flow path 144a The furnace can flow compressed air. Conversely, compressed air may flow through the first flow path 143a, and a mixture of fuel and compressed air may flow through the second flow path 144a.

In this case, the length of the plurality of injection nozzles 142 protruding downstream from the nozzle body 141 may be different for each injection nozzle 142 . In addition, the third embodiment may be applied to any of the plurality of injection nozzles 142 and the fourth embodiment may be applied to others.

In addition, the flow cross-sectional area of the fluid of the first flow path 143a and the second flow path 144a based on one injection nozzle 142 may be formed differently from each other, and based on one injection nozzle 142, the The radial thicknesses of the walls of the first nozzle tube 143 and the second nozzle tube 144 may also be formed differently. In addition, the area of each of the first flow passages 143a and the second flow passages 144a of the plurality of injection nozzles 142 is also formed differently for each injection nozzle 142 , and each of the first nozzles of the plurality of injection nozzles 142 is formed differently. The radial thickness of the tube 143 and the wall of the second nozzle tube 144 may also be formed differently for each injection nozzle 142 .

10: gas turbine 11: compressor
12: turbine 100: combustor
110: nozzle casing 120: liner
121: combustion chamber 130: transition piece
140,240,340,440 : nozzle assembly
141: nozzle body 142: spray nozzle
143: first nozzle tube 143a: first flow path
143b: first communication hole 144: second nozzle tube
144a: 2nd euro 144b: 2nd communication hole
145: communication tube

Claims (21)

In the nozzle assembly provided in the combustor of the gas turbine and injecting fuel and compressed air into the combustion chamber of the combustor,
nozzle body; and
It is installed in the nozzle body, including an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The second nozzle tube is a nozzle assembly in which a second communication hole through which fuel is introduced from the outside is formed. The method according to claim 1,
The first nozzle tube, a first communication hole is formed,
The second nozzle tube is disposed radially outside the first communication hole,
The spray nozzle is
It is installed in the second flow path, is connected to the outer circumferential surface of the first nozzle tube and the inner circumferential surface of the second nozzle tube so as to communicate with the first communication hole and the second communication hole, further comprising a communication tube into which fuel is introduced the nozzle assembly. delete In the nozzle assembly provided in the combustor of the gas turbine and injecting fuel and compressed air into the combustion chamber of the combustor,
nozzle body; and
It is installed in the nozzle body, including an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The injection nozzle is a nozzle assembly in which a downstream end protrudes from the nozzle body to a downstream side based on a flow direction of fuel and compressed air flowing therein. 5. The method according to claim 4,
The first nozzle tube and the second nozzle tube have different protruding lengths from the nozzle body to the downstream end, respectively. In the nozzle assembly provided in the combustor of the gas turbine and injecting fuel and compressed air into the combustion chamber of the combustor,
nozzle body; and
It is installed in the nozzle body, including an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
In the first nozzle tube, a downstream end with respect to a flow direction of fuel and compressed air flowing therein is more protruded to a downstream side than a downstream end of the second nozzle tube. The method according to claim 1,
In the second nozzle tube, a downstream end with respect to the flow direction of fuel and compressed air flowing therein protrudes further downstream than the downstream end of the first nozzle tube. In the combustor for mixing compressed air supplied from the compressor of the gas turbine with fuel, and supplying the generated combustion gas to the turbine of the 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 burned;
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
and a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The second nozzle tube is a combustor in which a second communication hole through which fuel is introduced from the outside is formed. 9. The method of claim 8,
The first nozzle tube, a first communication hole is formed,
The second nozzle tube is disposed radially outside the first communication hole,
The spray nozzle is
It is installed in the second flow path, is connected to the outer circumferential surface of the first nozzle tube and the inner circumferential surface of the second nozzle tube so as to communicate with the first communication hole and the second communication hole, further comprising a communication tube into which fuel is introduced combustor. delete In the combustor for mixing compressed air supplied from the compressor of the gas turbine with fuel, and supplying the generated combustion gas to the turbine of the 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 burned;
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
and a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The injection nozzle is a combustor with a downstream end protruding from the nozzle body to a downstream side based on a flow direction of fuel and compressed air flowing therein. 12. The method of claim 11,
The first nozzle tube and the second nozzle tube have different lengths protruding from the nozzle body to the downstream end, respectively. In the combustor for mixing compressed air supplied from the compressor of the gas turbine with fuel, and supplying the generated combustion gas to the turbine of the 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 burned;
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
and a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The first nozzle tube, the downstream (Downstream) side end based on the flow direction of the fuel and compressed air flowing therein, the combustor more protruding to the downstream side than the downstream end of the second nozzle tube. 9. The method of claim 8,
The second nozzle tube, the downstream (Downstream) side end based on the flow direction of the fuel and compressed air flowing therein, the combustor more protruding to the downstream side than the downstream end of the first nozzle tube. a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with fuel; 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 burned;
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 injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The second nozzle tube is a gas turbine having a second communication hole through which fuel is introduced from the outside. 16. The method of claim 15,
The first nozzle tube, a first communication hole is formed,
The second nozzle tube is disposed radially outside the first communication hole,
The spray nozzle is
It is installed in the second flow path, is connected to the outer circumferential surface of the first nozzle tube and the inner circumferential surface of the second nozzle tube so as to communicate with the first communication hole and the second communication hole, further comprising a communication tube into which fuel is introduced gas turbine. delete a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with fuel; 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 burned;
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 injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
The injection nozzle is a gas turbine having a downstream end protruding from the nozzle body to a downstream side based on a flow direction of fuel and compressed air flowing therein. 19. The method of claim 18,
The first nozzle tube and the second nozzle tube have different lengths protruding from the nozzle body to the downstream end, respectively. a compressor for compressing air introduced from the outside;
a combustor for mixing the compressed air supplied from the compressor with fuel; 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 burned;
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 injecting fuel and compressed air into the combustion chamber,
The nozzle assembly,
nozzle body,
It is installed on the nozzle body and includes an injection nozzle for injecting fuel and compressed air into the combustion chamber,
The spray nozzle is
a first nozzle tube having a first flow path formed therein;
a second nozzle tube disposed to surround the first nozzle tube from the outside in a radial direction, and a second nozzle tube having a second flow path formed between the first nozzle tube and the first nozzle tube;
In the first nozzle tube, a downstream end with respect to a flow direction of fuel and compressed air flowing therein is more protruded to a downstream side than a downstream end of the second nozzle tube. 16. The method of claim 15,
In the second nozzle tube, a downstream end with respect to a flow direction of fuel and compressed air flowing therein is more protruded to a downstream side than a downstream end of the first nozzle tube.

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