Patent Description:
A gas turbine is a power engine that mixes air compressed by a compressor with fuel for combustion and rotates a turbine with hot gas produced by the combustion. The gas turbine is used to drive a generator, an aircraft, a ship, a train, etc..

The gas turbine typically includes a compressor, a combustor, and a turbine. The compressor sucks and compresses outside air, and then transmits the compressed air to the combustor. The air compressed by the compressor becomes high pressure and high temperature. The combustor mixes the compressed air flowing from the compressor with fuel and burns a mixture thereof. The combustion gas produced by the combustion is discharged to the turbine. Turbine blades in the turbine are rotated by the combustion gas, thereby generating power. The generated power is used in various fields, such as generating electric power and actuating machines.

Fuel is injected through nozzles installed in each combustor section of the combustor, and the nozzles allow for injection of gas fuel and liquid fuel. In recent years, it is recommended to use hydrogen fuel or fuel containing hydrogen to inhibit the emission of carbon dioxide.

However, since hydrogen has a high combustion rate, when hydrogen fuel or fuel containing hydrogen is burned in a gas turbine combustor, the flame formed in the gas turbine combustor approaches and heats the structure of the gas turbine combustor, which may cause a problem with the reliability of the gas turbine combustor.

In addition, in a gas turbine that burns hydrogen, it is necessary to efficiently cool a nozzle tip part in order to prevent deterioration of the nozzle tip part.

<CIT> presents a fuel injection nozzle that includes a body member having an upstream wall opposing a downstream wall, and an internal wall disposed between the upstream wall and the downstream wall, a first chamber partially defined by the an inner surface of the upstream wall and a surface of the internal wall, a second chamber partially defined by an inner surface of the downstream wall and a surface of the internal wall a first gas inlet communicative with the first chamber operative to emit a first gas into the first chamber, a second gas inlet communicative with the second chamber operative to emit a second gas into the second chamber, and a plurality of mixing tubes, each of the mixing tubes having a tube inner surface, a tube outer surface, a first inlet communicative with an aperture in the upstream wall operative to receive a third gas.

<CIT> provides a gas turbine combustor that includes: an air supply flow passage constitution member in which plural air supply flow passages for supplying air to a combustion chamber are formed; and plural fuel nozzles that injects fuel to the combustion chamber through the air supply flow passages. In the gas turbine combustor, swirl flow is formed in the air supply flow passage, and contraction flow is made occur in the swirl flow, to thereby supply air and fuel to the combustion chamber.

<CIT> presents a combustor nozzle, and a combustor and gas turbine including the same. The combustor nozzle includes a main cylinder having a fuel passage through which fuel flows, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel, wherein the fuel injection module includes a plurality of first struts protruding from the main cylinder and having strut injection holes to inject fuel, a first support tube coupled to outer ends of the first struts, and a plurality of second struts protruding from the first support tube and having strut injection holes to inject fuel, and each of the first and second struts includes a swirl guide inclined with respect to a longitudinal direction of the main cylinder.

<CIT> presents a combustor that includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion.

<CIT> presents an apparatus for supplying fuel to the combustion chamber of a gas turbine engine.

<CIT> presents a premixer injector assembly in a gas turbine engine.

It is an object to overcome one or more of the problems of the prior art. It is an object to provide a combustor nozzle having a nozzle tip part capable of being efficiently cooled, a combustor, and a gas turbine including the same. In addition, it is an object to provide a combustor nozzle capable of uniformly mixing fuel and air, a combustor, and a gas turbine including the same. At least one of these objects is solved by the features of the independent claims.

Additional aspects will be set forth in part in the description which follows and, in part, will become apparent from the description, or may be learned by practice of the exemplary embodiments.

According to an aspect of an exemplary embodiment, the front plate may include a center hole connected to the fuel tube. The front plate may include further an outer hole disposed outside the center hole to allow fuel to pass therethrough.

The multi-tube may be equipped with a rear plate disposed at a rear end thereof. The multi-tube may further be equipped with a manifold plate spaced apart from the rear plate to define a distribution space.

The at least one mixing guide may consist of a plurality of mixing guides installed in the mixing tube. The mixing guides may be fixed to an inner wall of the mixing tube and/or spaced apart from each other in a circumferential direction of the mixing tube.

The mixing tube may include an inlet formed at one longitudinal end thereof to introduce air through the inlet. The mixing tube may include an injection port formed at the other longitudinal end thereof to inject, a mixture in which fuel and air are premixed, through the injection port. The mixing tube may include an injection hole formed on an outer peripheral surface thereof to inject fuel to the inside through said injection hole.

The mixing guide may be positioned between said injection holes.

A first gap between a radially central portion of the front plate and the tip plate may be smaller than a second gap formed between a radially outer portion of the front plate and the tip plate.

The front plate may be formed to be inclined rearward from the radial center thereof toward the outside.

According to an aspect, there is provided a combustor including: a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to one side of the burner to burn a mixture of the fuel and the air therein and transmit combustion gas to a turbine, wherein at least one of or each of the nozzles is a nozzle according to any one of the herein described embodiments.

According to an aspect of another exemplary embodiment, there is provided a combustor including a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to one side of the burner to burn a mixture of the fuel and the air therein and transmit combustion gas to a turbine. Each of the nozzles includes a plurality of mixing tubes through which air and fuel flow, a multi-tube configured to contain and support the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, and a front plate spaced apart from the tip plate to define a cooling space.

The front plate may include a center hole connected to the fuel tube, and an outer hole disposed outside the center hole to allow fuel to pass therethrough.

The multi-tube may be equipped with a rear plate disposed at a rear end thereof, and with a manifold plate spaced apart from the rear plate to define a distribution space.

According to an aspect, there is provided a gas turbine including: a compressor configured to compress air introduced thereinto from the outside, a combustor configured to mix fuel with the air compressed by the compressor for combustion, and a turbine having a plurality of turbine blades rotated by combustion gas produced by the combustion in the combustor. The combustor may be a combustor according to any one of the herein described embodiments.

According to an aspect of a further exemplary embodiment, there is provided a gas turbine including a compressor configured to compress air introduced thereinto from the outside, a combustor configured to mix fuel with the air compressed by the compressor for combustion, and a turbine having a plurality of turbine blades rotated by combustion gas produced by the combustion in the combustor. The combustor comprises a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to the burner to burn a mixture of the fuel and the air therein and transmit combustion gas to a turbine. At least one of or each of the nozzles includes a plurality of mixing tubes through which air and fuel flow, a multi-tube configured to contain and support the mixing tubes, a fuel tube formed inside the multi-tube and through which fuel flows, a tip plate coupled to a tip of the multi-tube, and a front plate spaced apart from the tip plate to define a cooling space.

The above and other aspects will become more apparent from the following description of the exemplary embodiments with reference to the accompanying drawings, in which:.

Various modifications and different embodiments will be described below in detail with reference to the accompanying drawings so that those skilled in the art can easily carry out the disclosure. It should be understood, however, that the present disclosure is not intended to be limited to the specific embodiments, but the present disclosure includes all modifications, equivalents or replacements that fall within the scope of the disclosure as defined in the following claims.

The terminology used herein is for the purpose of describing specific embodiments only and is not intended to limit the scope of the disclosure. In the disclosure, terms such as "comprises", "includes", or "have/has" should be construed as designating that there are such features, integers, steps, operations, components, parts, and/or combinations thereof, not to exclude the presence or possibility of adding of one or more of other features, integers, steps, operations, components, parts, and/or combinations thereof.

Exemplary embodiments will be described below in detail with reference to the accompanying drawings. It should be noted that like reference numerals refer to like parts throughout various drawings and exemplary embodiments. In certain embodiments, a detailed description of functions and configurations well known in the art may be omitted to avoid obscuring appreciation of the disclosure by those skilled in the art. For the same reason, some components may be exaggerated, omitted, or schematically illustrated in the accompanying drawings.

Hereinafter, a gas turbine according to a first exemplary embodiment will be described.

<FIG> is a view illustrating the interior of the gas turbine according to the first exemplary embodiment. <FIG> is a view illustrating the combustor of <FIG>.

The thermodynamic cycle of the gas turbine, which is designated by reference numeral <NUM>, according to the present embodiment may ideally follow a Brayton cycle. The Brayton cycle may consist of four phases including isentropic compression (adiabatic compression), isobaric heat addition, isentropic expansion (adiabatic expansion), and isobaric heat dissipation. In other words, in the Brayton cycle, thermal energy may be released by combustion of fuel in an isobaric environment after the atmospheric air is sucked and compressed to a high pressure, hot combustion gas may be expanded to be converted into kinetic energy, and exhaust gas with residual energy may then be discharged to the atmosphere. The Brayton cycle may consist of four processes, i.e., compression, heating, expansion, and exhaust.

The gas turbine <NUM> using the above Brayton cycle may include a compressor <NUM>, a combustor <NUM>, and a turbine <NUM>, as illustrated in <FIG>. Although the following description is given with reference to <FIG>, the present disclosure may be widely applied to a turbine engine having the same configuration as the gas turbine <NUM> exemplarily illustrated in <FIG>.

Referring to <FIG>, the compressor <NUM> of the gas turbine <NUM> may suck air from the outside and compress the air. The compressor <NUM> may supply the combustor <NUM> with the air compressed by compressor blades <NUM>, and may supply cooling air to a hot region required for cooling in the gas turbine <NUM>. In this case, since the air sucked into the compressor <NUM> is subject to an adiabatic compression process therein, the pressure and temperature of the air that has passed through the compressor <NUM> increase.

The compressor <NUM> is designed as a centrifugal compressor or an axial compressor. In general, the centrifugal compressor is applied to a small gas turbine, whereas the multistage axial compressor is applied to the large gas turbine <NUM> as illustrated in <FIG> because it is necessary to compress a large amount of air. In the multistage axial compressor, the compressor blades <NUM> of the compressor <NUM> rotate along with the rotation of rotor disks to compress air introduced thereinto while delivering the compressed air to rear-stage compressor vanes <NUM>. The air is compressed increasingly to a high pressure while passing through the compressor blades <NUM> formed in a multistage manner.

A plurality of compressor vanes <NUM> may be formed in a multistage manner and mounted in a compressor casing <NUM>. The compressor vanes <NUM> guide the compressed air, which flows from front-stage compressor blades <NUM>, to rear-stage compressor blades <NUM>. In an exemplary embodiment, at least some of the plurality of compressor vanes <NUM> may be mounted so as to be rotatable within a fixed range for regulating the inflow rate of air or the like.

The compressor <NUM> may be driven by some of the power output from the turbine <NUM>. To this end, the rotary shaft of the compressor <NUM> may be directly connected to the rotary shaft of the turbine <NUM>, as illustrated in <FIG>. In the large gas turbine <NUM>, the compressor <NUM> may require almost half of the power generated by the turbine <NUM> for driving. Accordingly, the overall efficiency of the gas turbine <NUM> can be enhanced by directly increasing the efficiency of the compressor <NUM>.

The turbine <NUM> includes a plurality of rotor disks <NUM>, a plurality of turbine blades radially arranged on each of the rotor disks <NUM>, and a plurality of turbine vanes. Each of the rotor disks <NUM> has a substantially disk shape and has a plurality of grooves formed on the outer peripheral portion thereof. The grooves are each formed to have a curved surface so that the turbine blades are inserted into the grooves, and the turbine vanes are mounted in a turbine casing. The turbine vanes are fixed so as not to rotate and serve to guide the direction of flow of the combustion gas that has passed through the turbine blades. The turbine blades generate rotational force while rotating by the combustion gas.

Meanwhile, the combustor <NUM> may mix the compressed air, which is supplied from the outlet of the compressor <NUM>, with fuel for isobaric combustion to produce combustion gas with high energy. <FIG> illustrates an example of the combustor <NUM> applied to the gas turbine <NUM>. The combustor <NUM> may include a combustor casing <NUM>, a burner <NUM>, a nozzle <NUM>, and a duct assembly <NUM>.

The combustor casing <NUM> may have a substantially circular shape so as to surround a plurality of burners <NUM>. The burners <NUM> may be disposed along the annular combustor casing <NUM> downstream of the compressor <NUM>. Each of the burners <NUM> includes a plurality of nozzles <NUM>, and the fuel injected from the nozzles <NUM> is mixed with air at an appropriate rate so that the mixture thereof is suitable for combustion.

The gas turbine <NUM> may use gas fuel, especially fuel containing hydrogen. The fuel may be either hydrogen fuel alone or fuel containing hydrogen and natural gas.

Compressed air is supplied to the nozzles <NUM> along the outer surface of the duct assembly <NUM>, which connects an associated one of the burners <NUM> to the turbine <NUM> so that hot combustion gas flows through the duct assembly <NUM>. In this process, the duct assembly <NUM> heated by the hot combustion gas is properly cooled.

The duct assembly <NUM> may include a liner <NUM>, a transition piece <NUM>, and a flow sleeve <NUM>. The duct assembly <NUM> has a double structure in which the flow sleeve <NUM> surrounds the liner <NUM> and the transition piece <NUM>. The liner <NUM> and the transition piece <NUM> are cooled by the compressed air permeated into an annular space inside the flow sleeve <NUM>.

The liner <NUM> is a tubular member connected to the burner <NUM> of the combustor <NUM>, and the combustion chamber <NUM> is a space within the liner <NUM>. The liner <NUM> has one longitudinal end coupled to the burner <NUM> and the other longitudinal end coupled to the transition piece <NUM>.

The transition piece <NUM> is connected to the inlet of the turbine <NUM> and serves to guide hot combustion gas to the turbine <NUM>. The transition piece <NUM> has one longitudinal end coupled to the liner <NUM> and the other longitudinal end coupled to the turbine <NUM>. The flow sleeve <NUM> serves to protect the liner <NUM> and the transition piece <NUM> while preventing high-temperature heat from being directly released to the outside.

<FIG> is a longitudinal cross-sectional view illustrating one nozzle according to the first exemplary embodiment. <FIG> is a rear cutaway perspective view illustrating the nozzle according to the first exemplary embodiment. <FIG> is a cross-sectional view illustrating a mixing guide according to the first exemplary embodiment. <FIG> is a cross-sectional view illustrating a guide plate of the mixing guide according to the first exemplary embodiment.

Referring to <FIG>, the nozzle <NUM> may include a plurality of mixing tubes <NUM> through which air and fuel flow, a multi-tube <NUM> surrounding the mixing tubes <NUM>, a fuel tube <NUM> formed inside the multi-tube <NUM>, a tip plate <NUM> coupled to the tip of the multi-tube <NUM>, and a front plate <NUM> spaced apart from the tip plate <NUM>.

The multi-tube <NUM> is generally in a cylindrical shape and has a space defined therein. The nozzle <NUM> may further include a fuel supply pipe <NUM> for supplying fuel to the multi-tube <NUM>. Here, the fuel may be gas containing hydrogen. The multitube <NUM> may allow for fine injection of hydrogen and air.

The fuel tube <NUM> may be disposed in the radial center of the multi-tube <NUM> to provide a flow space of fuel. The direction of the flow of the fuel in the fuel tube <NUM> may be referred to as the longitudinal direction or an axial direction. The fuel tube <NUM> may have one longitudinal end connected to the fuel supply pipe <NUM> to receive fuel, and the other longitudinal end connected to the front plate <NUM> to supply fuel to a cooling space CS1. The one longitudinal end of the fuel tube <NUM> connected to the fuel supply pipe <NUM> may be referred to as an upstream end of the fuel tube <NUM> or an rear end of the fuel tube <NUM> and the other longitudinal end of the fuel tube connected to the front plate may be referred to as a downstream end of the fuel tube <NUM> or an front end of the fuel tube <NUM>.

The tip plate <NUM> is coupled to the tip of the multi-tube <NUM> to define the cooling space CS1. The tips of the plurality of mixing tubes <NUM> may be inserted into the tip plate <NUM>. The front plate <NUM> is spaced apart from the tip plate <NUM> to define the cooling space. In other words, the cooling space CS1 may be disposed between the front plate <NUM> and the tip plate <NUM>. The cooling space CS1 may be disposed between the tip plate <NUM> and the front plate <NUM> and between the plurality of mixing tubes <NUM>. The front plate <NUM> may be fixed to the inner wall of the multi-tube <NUM>.

The front plate <NUM> may include a center hole <NUM> to which the fuel tube <NUM> is coupled, and an outer hole <NUM> formed outside the center hole <NUM> to allow the cooled fuel to flow rearward (upstream direction based on the flow direction of the fuel in the fuel tube <NUM>) therethrough. In other words, the fuel may flow in the fuel tube <NUM> toward the front plate <NUM> in the downstream direction, and then flow through the center hole <NUM> of the front plate <NUM> in the downstream direction, and then flow through the outer hole <NUM> of the front plate <NUM> in the upstream direction, and then flow away from the front plate <NUM> in the upstream direction. When the fuel flows after the center hole <NUM> and before the outer hole <NUM>, the fuel may flow through the cooling space CS1 generally in a direction radially outward from the radial center of the multi-tube <NUM>. The center hole <NUM> may be disposed in the radial center of the front plate <NUM>, and the outer hole <NUM> may be formed at the radially outer end of the front plate <NUM>. The outer hole <NUM> may be formed continuously in a circumferential direction of the front plate <NUM>, or may consist of a plurality of outer holes spaced apart from each other in the circumferential direction of the front plate <NUM>.

Accordingly, the fuel introduced into the cooling space CS1 through the center hole <NUM> may cool the multi-tube <NUM> while flowing radially outwards after impacting and cooling the tip plate <NUM>, and flow rearward (upstream direction based on the flow direction of the fuel in the fuel tube <NUM>) through the outer hole <NUM>. At the rear side of the cooling space CS1, a separate movement space FS1 may be defined by the front plate <NUM>. In the movement space FS1, the fuel may flow toward the inlet of each mixing tube <NUM>.

Meanwhile, each of the mixing tubes <NUM> may be equipped with a manifold plate <NUM> to define a distribution space MS1. The movement space FS1 may be disposed between the front plate <NUM> and the manifold plate <NUM>. A rear plate <NUM> may be installed at the rear end of the multi-tube <NUM>, and the manifold plate <NUM> may be spaced apart from the rear plate <NUM>. The manifold plate <NUM> may have a plurality of holes formed therein for flow of fuel.

The distribution space MS1 may be defined between the rear plate <NUM> and the manifold plate <NUM>. The fuel, after flowing from the movement space FS1 to the distribution space MS1, may be injected into each mixing tube <NUM> from the distribution space MS1.

The plurality of mixing tubes <NUM> may be installed inside the multi-tube <NUM> to form several small flames using hydrogen gas. The mixing tubes <NUM> may be spaced apart from each other in the multi-tube <NUM> and formed parallel to each other. Each of the mixing tubes <NUM> may have a cylindrical shape.

The mixing tube <NUM> may have an injection port <NUM> formed at the front thereof to inject a mixture of air and fuel through the injection port <NUM>, and an inlet <NUM> formed at the rear thereof to introduce air through the inlet <NUM>.

The mixing tube <NUM> may have a plurality of injection holes <NUM> connected to the distribution space MS1. The fuel may be injected into the mixing tube <NUM> through said injection holes <NUM> from the distribution space MS1. The injection holes <NUM> may allow fuel to be injected toward the radial center of the mixing tube <NUM>.

The mixing tube <NUM> are equipped with a mixing guide <NUM> therein, which extends spirally and is positioned between the first injection holes <NUM>. The mixing guide <NUM> may be fixed to the inner wall of the mixing tube <NUM>. Alternatively, the mixing guide <NUM> may consist of a plurality of mixing guides spaced apart from each other in the circumferential direction of the mixing tube <NUM> on the inner wall of the mixing tube <NUM>.

The mixing guide <NUM> includes a spiral part <NUM> extending spirally and a guide plate <NUM> protruding from the spiral part <NUM> toward the inlet and having a flat shape. The spiral part <NUM> extends spirally to induce a rotational flow, and fuel and air may be uniformly mixed by the rotational flow.

Meanwhile, the guide plate <NUM> has a chamber <NUM> for accommodation of fuel therein and a further injection hole <NUM> through which fuel is injected. The guide plate <NUM> has a flat shape formed in the axial direction, and the chamber <NUM> is connected to the distribution space MS <NUM> to receive fuel. The guide plate <NUM> may have an inclined surface <NUM> formed at a portion thereof toward the inlet <NUM> to be inclined with respect to the inner peripheral surface of the mixing tube <NUM>, and the second injection hole <NUM> may be formed on the inclined surface <NUM>. The inclined surface <NUM> may be inclined toward the downstream of the mixing tube <NUM> as the inclined surface <NUM> is formed inwardly from the inner surface of the mixing tube <NUM>. The second injection hole <NUM> may allow fuel to be injected in a direction opposite to the direction of inflow of air, thereby inducing turbulence so that fuel and air may be uniformly mixed.

Hereinafter, one nozzle according to a second exemplary embodiment will be described.

<FIG> is a cross-sectional view illustrating a front plate and a tip plate according to the second exemplary embodiment.

Referring to <FIG>, since the nozzle, which is designated by reference numeral <NUM>, according to the second exemplary embodiment has the same structure as the nozzle according to the first exemplary embodiment, except for a front plate, a redundant description thereof will be omitted.

The tip plate <NUM> is coupled to the tip of the multi-tube <NUM>. The tips of the plurality of mixing tubes may be inserted into the tip plate <NUM>. The front plate, which is designated by reference numeral <NUM>, is spaced apart from the tip plate <NUM> to define the cooling space CS1. The cooling space CS1 may be disposed between the tip plate <NUM> and the front plate <NUM> and between the plurality of mixing tubes. The front plate <NUM> and the tip plate <NUM> may be fixed to the inner wall of the multi-tube <NUM>.

The front plate <NUM> may include a center hole <NUM> to which the fuel tube is coupled, and an outer hole <NUM> formed radially outside the center hole <NUM> to allow the cooled fuel to flow rearward ( upstream direction based on the flow direction of the fuel in the fuel tube <NUM>) therethrough. In addition, the front plate <NUM> may have an installation hole <NUM> into which the mixing tube <NUM> is inserted.

The first gap G21 between the radially central portion of the front plate <NUM> and the tip plate <NUM> may be smaller than the second gap G22 between the radially outer portion of the front plate <NUM> and the tip plate <NUM>. The front plate <NUM> may include a portion parallel to the tip plate <NUM> and a portion inclined rearward with respect to the tip plate <NUM>.

Accordingly, the front plate <NUM> may be formed to have at least one inclined portion and at least one parallel portion, such that each of the inclined portion is inclined rearward step by step, and the at least one parallel portion is parallel to the radially central portion of the front plate <NUM> and the gap between the front plate <NUM> and the tip plate <NUM> increases step by step toward the outside. The fuel introduced into the central portion of the nozzle may be heated and flow outwards, in which case, if the amount of fuel accommodated in the outer portion of the nozzle increases, that portion may also be sufficiently cooled by the fuel.

Hereinafter, one nozzle according to a third exemplary embodiment will be described.

<FIG> is a cross-sectional view illustrating a front plate and a tip plate according to the third exemplary embodiment.

Referring to <FIG>, since the nozzle, according to the third exemplary embodiment has the same structure as the nozzle according to the first exemplary embodiment, except for a redundant description thereof will be omitted.

The front plate <NUM> may include a center hole <NUM> to which the fuel tube <NUM> is coupled, and an outer hole <NUM> formed outside the center hole <NUM> to allow the cooled fuel to flow rearward ( upstream direction based on the flow direction of the fuel in the fuel tube <NUM>) therethrough. In addition, the front plate <NUM> may have an installation hole <NUM> into which the mixing tube is inserted.

The first gap G31 between the radially central portion of the front plate <NUM> and the tip plate <NUM> may be smaller than the second gap G32 between the radially outer portion of the front plate <NUM> and the tip plate <NUM>. The front plate <NUM> may have a truncated cone shape such that the portion other than the radially central portion of the front plate is inclined rearward from the radial center thereof toward the outside.

Accordingly, the front plate <NUM> may be inclined rearward, and the gap between the front plate <NUM> and the tip plate <NUM> increases continuously and gradually toward the outside. The fuel introduced into the central portion of the nozzle may be heated and flow outwards, in which case, if the amount of fuel accommodated in the outer portion of the nozzle increases, that portion may also be sufficiently cooled by the fuel.

Based on the above description, in the combustor nozzle, the combustor, and the gas turbine according to the exemplary embodiments, the cooling space may be defined between the tip plate and the front plate. Therefore, it is possible to efficiently cool the tip part of the nozzle by supplying fuel to the cooling space.

Claim 1:
A nozzle (<NUM>) for a combustor for a gas turbine, the combustor configured to burn fuel containing hydrogen, the nozzle (<NUM>) comprising:
a plurality of mixing tubes (<NUM>) for allowing air and fuel to flow through;
a multi-tube (<NUM>) supporting the mixing tubes (<NUM>);
a fuel tube (<NUM>) formed inside the multi-tube (<NUM>) for allowing fuel to flow through;
a tip plate (<NUM>) coupled to a tip of the multi-tube (<NUM>); and
a front plate (<NUM>, <NUM>, <NUM>) spaced apart from the tip plate (<NUM>) to define a cooling space (CS1);
characterized in that:
each of the mixing tubes (<NUM>) is equipped with at least one mixing guide (<NUM>) extending spirally,
wherein each of the mixing guides (<NUM>) comprises a spiral part (<NUM>) extending spirally and a guide plate (<NUM>) protruding from the spiral part (<NUM>) toward an inlet and having a flat shape, and
wherein the guide plate (<NUM>) has a chamber for accommodation of fuel therein and an injection hole (<NUM>) through which fuel is injected.