KR20240126733A - Nozzle for combustor, combustor, and gas turbine including the same - Google Patents

Abstract

According to one aspect of the present invention, a nozzle for a combustor that combusts fuel containing hydrogen comprises: a plurality of mixing tubes through which air and fuel move; a multi-tube for inserting and supporting the mixing tubes; a fuel tube formed inside the multi-tubes and through which fuel moves; a tip plate coupled to a tip end of the multi-tubes; and a plurality of fuel injection tubes that protrude into the mixing tubes and inject fuel, wherein the fuel injection tubes can be arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tube.

Description

NOZZLE FOR COMBUSTOR, COMBUSTOR, AND GAS TURBINE INCLUDING THE SAME

The present invention relates to a nozzle for a combustor, a combustor, and a gas turbine including the same, and more particularly, to a nozzle for a combustor using a fuel containing hydrogen, a combustor, and a gas turbine including the same.

A gas turbine is a power engine that mixes compressed air and fuel from a compressor, combusts them, and rotates a turbine with the high-temperature gas generated by the combustion. Gas turbines are used to drive generators, aircraft, ships, trains, etc.

Typically, a gas turbine includes a compressor, a combustor, and a turbine. The compressor takes in outside air, compresses it, and then delivers it to the combustor. The compressed air from the compressor becomes high-pressure and high-temperature. The combustor mixes the compressed air from the compressor with fuel and combusts it. The combustion gas generated by the combustion is discharged to the turbine. The turbine blades inside the turbine rotate due to the combustion gas, and power is generated through this. The generated power is used in various fields such as power generation and driving mechanical devices.

Fuel is injected through nozzles installed in each combustor, and the nozzles can inject gaseous fuel and liquid fuel. Recently, the use of hydrogen fuel or fuel containing hydrogen has been recommended to suppress carbon dioxide emissions.

However, since hydrogen has a fast combustion rate, when these fuels are burned in a gas turbine combustor, there is a possibility that the flame formed inside the gas turbine combustor may approach and heat the structure of the gas turbine combustor, causing problems with the reliability of the gas turbine combustor.

To solve this problem, a combustor nozzle with multiple tubes is proposed in Korean Patent Publication No. 10-2020-0027894, etc., but the nozzle with multiple tubes has a problem in that it is difficult to uniformly mix fuel and air because a swirler is not installed.

Based on the technical background as described above, the present invention provides a nozzle for a combustor, a combustor, and a gas turbine capable of efficiently mixing fuel and air.

According to one aspect of the present invention, a nozzle for a combustor that combusts fuel containing hydrogen comprises: a plurality of mixing tubes through which air and fuel move; a multi-tube for inserting and supporting the mixing tubes; a fuel tube formed inside the multi-tubes and through which fuel moves; a tip plate coupled to a tip end of the multi-tubes; and a plurality of fuel injection tubes that protrude into the mixing tubes and inject fuel, wherein the fuel injection tubes can be arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tube.

According to one aspect of the present invention, the fuel injection pipe may protrude from the inner surface of the mixing tube in a direction facing downstream.

According to one aspect of the present invention, the fuel injection pipe may be arranged to be inclined at a second angle with respect to the longitudinal direction of the mixing tube.

According to one aspect of the present invention, the inlet portion of the fuel injection pipe may be formed in an oval shape, and the outlet portion may be formed in a circular shape.

According to one aspect of the present invention, the mixing tube may have an injection hole formed that is connected to the fuel injection pipe, and an introduction guide portion formed in the injection hole whose inner diameter gradually increases toward the outside.

According to one aspect of the present invention, the fuel injection pipe may include an injection tip whose outer diameter gradually decreases toward the tip.

According to one aspect of the present invention, a fuel injection pipe is connected to the mixing tube and has an inlet portion through which fuel flows in and an outlet portion through which fuel flows out, and the outlet portion can be positioned between 1/4 and 3/4 of a point from the outer side in the radial direction of the mixing tube.

According to one aspect of the present invention, a plurality of guide protrusions may be formed on the outer surface of the fuel injection pipe, extending in the longitudinal direction of the fuel injection pipe and spaced apart in the circumferential direction of the fuel injection pipe.

According to one aspect of the present invention, a base portion may be formed at a portion of the fuel injection pipe connected to the mixing tube, the outer diameter of which gradually decreases toward the tip of the fuel injection pipe.

According to one aspect of the present invention, a plurality of guide vanes extending in the longitudinal direction of the fuel injection pipe may be installed on the outer surface of the fuel injection pipe.

According to another aspect of the present invention, a combustor comprises: a nozzle including a plurality of mixing tubes through which air and fuel move; a multi-tube for supporting the mixing tubes by inserting them; a fuel tube formed inside the multi-tubes and through which fuel moves; a tip plate coupled to a tip end of the multi-tubes; and a plurality of fuel injection tubes protruding into the mixing tubes and injecting fuel, wherein the fuel injection tubes can be arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tubes.

According to another aspect of the present invention, the fuel injection pipe may protrude from the inner surface of the mixing tube in a direction facing downstream.

According to another aspect of the present invention, the fuel injection pipe may be arranged to be inclined at a second angle with respect to the longitudinal direction of the mixing tube.

According to another aspect of the present invention, the inlet portion of the fuel injection pipe may be formed in an oval shape, and the outlet portion may be formed in a circular shape.

According to another aspect of the present invention, the mixing tube may have an injection hole formed that is connected to the fuel injection pipe, and an introduction guide portion formed in the injection hole whose inner diameter gradually increases toward the outside.

According to another aspect of the present invention, the fuel injector may include an injection tip whose outer diameter gradually decreases toward the tip.

According to another aspect of the present invention, a fuel injection pipe is connected to the mixing tube and has an inlet portion through which fuel flows in and an outlet portion through which fuel flows out, and the outlet portion can be located between 1/4 and 3/4 of a point from the outer side in the radial direction of the mixing tube.

According to another aspect of the present invention, a plurality of guide protrusions may be formed on the outer surface of the fuel injection pipe, extending in the longitudinal direction of the fuel injection pipe and spaced apart in the circumferential direction of the fuel injection pipe.

According to another aspect of the present invention, a base portion may be formed at a portion of the fuel injection pipe connected to the mixing tube, the outer diameter of which gradually decreases toward the tip of the fuel injection pipe.

According to another aspect of the present invention, a gas turbine includes a compressor that compresses air taken in from the outside, a combustor that mixes compressed air and fuel compressed in the compressor and combusts them, and a plurality of turbine blades that rotate by the combustion gas combusted in the combustor, wherein the combustor includes a burner having a plurality of nozzles that inject fuel and air, and a duct assembly that is coupled to one side of the burner and combusts the fuel and the air therein and delivers the combusted gas to the turbine, wherein the nozzles include a plurality of mixing tubes through which air and fuel move, a multi-tube that inserts and supports the mixing tubes, a fuel tube formed inside the multi-tubes and through which fuel moves, a tip plate coupled to the tip end of the multi-tubes, and a plurality of fuel injection tubes that protrude into the mixing tubes and inject fuel, wherein the fuel injection tubes can be arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tube.

As described above, according to the nozzle for a combustor, the combustor and the gas turbine according to one aspect of the present invention, a fuel injection pipe is installed in a mixing tube, and the fuel injection pipe is arranged at an angle with respect to the direction toward the center, so that the injected fuel can be uniformly mixed with the air while forming a swirl.

FIG. 1 is a drawing showing the interior of a gas turbine according to the first embodiment of the present invention.
Figure 2 is a drawing illustrating the combustor of Figure 1.
Figure 3 is a cross-sectional view taken longitudinally of a nozzle according to the first embodiment of the present invention.
FIG. 4 is a cross-sectional view taken longitudinally of a mixing tube and a fuel injection pipe according to the first embodiment of the present invention.
FIG. 5 is a cross-sectional view taken radially through a mixing tube and a fuel injection pipe according to the first embodiment of the present invention.
FIG. 6 is a perspective view illustrating a fuel injection pipe according to a second embodiment of the present invention.
FIG. 7 is a perspective view illustrating a fuel injection pipe according to a third embodiment of the present invention.
FIG. 8 is a perspective view illustrating a fuel injection pipe according to a fourth embodiment of the present invention.
FIG. 9 is a drawing of a fuel injection pipe according to a fourth embodiment of the present invention as viewed from the tip.

The present invention can be modified in various ways and has various embodiments, and thus specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, but should be understood to include all modifications, equivalents, or substitutes included in the spirit and technical scope of the present invention.

The terminology used herein is only used to describe specific embodiments and is not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly indicates otherwise. In the present invention, it should be understood that the terms "comprise" or "have" and the like are intended to specify that a feature, number, step, operation, component, part or combination thereof described in the specification is present, but do not exclude in advance the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. At this time, it should be noted that the same components in the attached drawings are indicated by the same symbols as much as possible. In addition, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components in the attached drawings are exaggerated, omitted, or schematically illustrated.

Below, a gas turbine according to the first embodiment of the present invention is described.

FIG. 1 is a drawing illustrating the interior of a gas turbine according to one embodiment of the present invention, and FIG. 2 is a drawing illustrating the combustor of FIG. 1.

The thermodynamic cycle of the gas turbine (1000) according to the present embodiment can ideally follow the Brayton cycle. The Brayton cycle can be composed of four processes: isentropic compression (adiabatic compression), constant pressure rapid heating, isentropic expansion (adiabatic expansion), and constant pressure heat dissipation. That is, atmospheric air is sucked in, compressed at high pressure, fuel is combusted in a constant pressure environment to release heat energy, the high-temperature combustion gas is expanded to convert it into kinetic energy, and then the exhaust gas containing the remaining energy can be released into the atmosphere. That is, the cycle can be composed of four processes: compression, heating, expansion, and heat dissipation.

A gas turbine (1000) that realizes the Brayton cycle as described above may include a compressor (1100), a combustor (1200), and a turbine (1300), as illustrated in FIG. 1. The following description will refer to FIG. 1, but the description of the present invention may be broadly applied to a turbine engine having an equivalent configuration to the gas turbine (1000) exemplarily illustrated in FIG. 1.

Referring to FIG. 1, the compressor (1100) of the gas turbine (1000) can intake air from the outside and compress it. The compressor (1100) can supply compressed air compressed by the compressor blade (1130) to the combustor (1200), and can also supply cooling air to a high temperature area requiring cooling in the gas turbine (1000). At this time, since the intake air undergoes an adiabatic compression process in the compressor (1100), the pressure and temperature of the air passing through the compressor (1100) increase.

The compressor (1100) is designed as a centrifugal compressor or an axial compressor. While a centrifugal compressor is applied to a small gas turbine, a multi-stage axial compressor is generally applied to a large gas turbine (1000) such as that illustrated in FIG. 1 because a large amount of air must be compressed. At this time, in the multi-stage axial compressor, the compressor blades (1130) of the compressor (1100) rotate according to the rotation of the rotor disk to compress the intake air and move the compressed air to the compressor vanes (1140) of the rear stage. The air is compressed to an increasingly high pressure as it passes through the compressor blades (1130) formed in multiple stages.

The compressor vane (1140) is mounted inside the housing (1150), and a plurality of compressor vanes (1140) can be mounted to form a unit. The compressor vane (1140) guides compressed air moved from the compressor blade (1130) of the front end to the compressor blade (1130) of the rear end. In one embodiment, at least some of the plurality of compressor vanes (1140) can be mounted to be rotatable within a set range, such as for controlling the amount of air introduced.

The compressor (1100) can be driven using a portion of the power output from the turbine (1300). For this purpose, as illustrated in FIG. 1, the rotational axis of the compressor (1100) and the rotational axis of the turbine (1300) can be directly connected. In the case of a large gas turbine (1000), approximately half of the power produced by the turbine (1300) can be consumed in driving the compressor (1100). Therefore, improving the efficiency of the compressor (1100) directly affects improving the overall efficiency of the gas turbine (1000).

The turbine (1300) includes a rotor disk (1310) and a plurality of turbine blades and turbine vanes radially arranged on the rotor disk (1310). The rotor disk (1310) has an approximately circular shape, and a plurality of grooves are formed on its outer periphery. The grooves are formed to have curved surfaces, and turbine blades and turbine vanes are inserted into the grooves. The turbine vanes are fixed so as not to rotate and guide the flow direction of combustion gas passing through the turbine blades. The turbine blades generate rotational force by rotating due to the combustion gas.

Meanwhile, the combustor (1200) can mix compressed air supplied from the outlet of the compressor (1100) with fuel and combust it under isobaric pressure to produce high energy combustion gas. Fig. 2 shows an example of a combustor (1200) applied to a gas turbine (1000). The combustor (1200) can include a combustor casing (1210), a burner (1220), a nozzle (1400), and a duct assembly (1250).

The combustor casing (1210) may be formed in an approximately circular shape, surrounding a plurality of burners (1220). The burners (1220) are arranged downstream of the compressor (1100) and may be arranged along the combustor casing (1210) forming an annular shape. Each burner (1220) is provided with a plurality of nozzles (1400), and fuel sprayed from the nozzles (1400) is mixed with air at an appropriate ratio to form a state suitable for combustion.

The gas turbine (1000) can use gaseous fuel, and in particular, a fuel containing hydrogen. The fuel can consist of hydrogen fuel alone or a fuel containing hydrogen and natural gas.

Compressed air flows along the outer surface of a duct assembly (1250) connecting the burner (1220) and the turbine (1300) through which high-temperature combustion gas flows and is supplied toward the nozzle (1400), and in this process, the duct assembly (1250) heated by the high-temperature combustion gas is appropriately cooled.

The duct assembly (1250) may include a liner (1251), a transition piece (1252), and a flow sleeve (1253). The duct assembly (1250) has a double structure in which the flow sleeve (1253) surrounds the outside of the liner (1251) and the transition piece (1252), and compressed air penetrates into the annular space inside the flow sleeve (1253) to cool the liner (1251) and the transition piece (1252).

The liner (1251) is a tubular member connected to the burner (1220) of the combustor (1200), and the space inside the liner (1251) forms a combustion chamber (1240). One longitudinal end of the liner (1251) is connected to the burner (1220), and the other longitudinal end of the liner (1251) is connected to a transition piece (1252).

And, the transition piece (1252) is connected to the inlet of the turbine (1300) and serves to guide high-temperature combustion gas to the turbine (1300). One longitudinal end of the transition piece (1252) is connected to the liner (1251), and the other longitudinal end of the transition piece (1252) is connected to the turbine (1300). The fluid sleeve (1253) protects the liner (1251) and the transition piece (1252) while preventing high-temperature heat from being directly released to the outside.

FIG. 3 is a cross-sectional view taken along the longitudinal direction of a nozzle according to the first embodiment of the present invention, FIG. 4 is a cross-sectional view taken along the longitudinal direction of a mixing tube and a fuel injection pipe according to the first embodiment of the present invention, and FIG. 5 is a cross-sectional view taken along the radial direction of a mixing tube and a fuel injection pipe according to the first embodiment of the present invention.

Referring to FIGS. 3 to 5, the nozzle (1400) may include a plurality of mixing tubes (1420) through which air and fuel move, a multi-tube (1410) surrounding the mixing tube (1420), a fuel tube (1450) formed inside the multi-tube (1410), a tip plate (1415) coupled to the tip end of the multi-tube (1410), and a front plate (1460) spaced apart from the tip plate (1415).

The multi-tube (1410) is formed in a cylindrical shape and has a space formed inside. In addition, the nozzle (1400) may further include a fuel supply pipe (1430) that supplies fuel to the multi-tube (1410). Here, the fuel may be formed of a gas containing hydrogen. The multi-tube (1410) may finely spray hydrogen and air.

A fuel tube (1450) is arranged at the radial center of the multi-tube (1410) to provide a space for fuel to move. One longitudinal end of the fuel tube (1450) is connected to a fuel supply pipe (1430) to receive fuel, and the other longitudinal end of the fuel tube (1450) is connected to a front plate (1460) to supply fuel to a cooling space (CS1).

The tip plate (1415) is connected to the tip end of the multi-tube (1410) to form a cooling space (CS1). The tip end of a plurality of mixing tubes (1420) can be inserted into the tip plate (1415). The front plate (1460) is spaced apart from the tip plate (1415) to form a cooling space. The front plate (1460) can be fixed to the inner wall of the multi-tube (1410).

The front plate (1460) may include a center hole (1461) to which a fuel tube (1450) is coupled, and an outer hole (1462) formed on the outside of the center hole (1461) so that fuel that has undergone cooling passes through it and moves rearward (upstream with respect to the direction of movement of air). The center hole (1461) may be formed at the radial center of the front plate (1460), and the outer hole (1462) may be formed at an outer end of the front plate (1460). The outer hole (1462) may be formed along the circumference of the front plate (1460), or a plurality of outer holes (1462) may be spaced apart from each other in the circumference of the front plate (1460).

Accordingly, the fuel introduced into the cooling space (CS1) through the center hole (1461) cools by impacting the tip plate (1415), and then moves radially outward to cool the multi-tube (1410) and can move rearward (downstream based on the direction of air movement) through the outer hole (1462). A movement space (FS1) separated by the front plate (1460) is formed at the rear of the cooling space (CS1), and in the movement space (FS1), the fuel moves toward the inlet of the mixing tube (1420).

Meanwhile, a manifold plate (1470) forming a distribution space (MS1) is installed inside the mixing tube (1420). A rear plate (1418) is installed at the rear end of the multi-tube (1410), and the manifold plate (1470) is spaced apart from the rear plate (1418). A plurality of holes for the movement of fuel may be formed in the manifold plate (1470).

The rear plate (1418) forms a distribution space (MS1) between it and the manifold plate (1470). Fuel can be injected into the mixing tube (1420) after moving from the movement space (FS1) to the distribution space (MS1).

A plurality of mixing tubes (1420) are installed inside the multi-tube (1410) so as to form a plurality of small flames using hydrogen gas. The plurality of mixing tubes (1420) may be spaced apart from each other within the multi-tube (1410) and formed parallel to each other. The mixing tube (1420) may be formed in a cylindrical shape.

An injection port (1423) through which air mixed with fuel is injected may be formed at the front of the mixing tube (1420), and an inlet port (1422) through which air is introduced may be formed at the rear of the mixing tube (1420).

A plurality of fuel injection pipes (1500) are installed in the mixing tube (1420), and the fuel injection pipes (1500) protrude into the mixing tube (1420) to inject hydrogen gas, which is a fuel. A plurality of fuel injection pipes (1500) are installed in the mixing tube (1420), and two to six fuel injection pipes (1500) may be installed. In addition, four fuel injection pipes (1500) may be installed in the mixing tube (1420).

The fuel injection pipe (1500) is arranged to be inclined at a first angle (A11) with respect to the direction toward the radial center of the mixing tube (1420). That is, the central axis (X1) of the fuel injection pipe (1500) is arranged to be inclined at a first angle (A11) with respect to the radial line (R1) toward the radial center of the mixing tube (1420), and the first angle (A11) may be 5 degrees to 45 degrees. Accordingly, the fuel injected from the fuel injection pipe (1500) may move while forming a swirl eccentrically from the center direction, so as to be uniformly mixed with the air. In addition, since a swirl is formed in the flow of air by the fuel injection pipe (1500) arranged to be inclined, the air and the fuel may be mixed more uniformly.

Meanwhile, the fuel injection pipe (1500) protrudes in a direction toward the downstream of the mixing tube (1420), and the fuel injection pipe (1500) may be formed to be inclined at a second angle (A12) with respect to the inner surface of the mixing tube (1420). Here, the second angle (A12) may be 10 to 30 degrees. Accordingly, the flow recirculation of the fuel can be minimized.

An injection hole (1425) connected to a fuel injection pipe (1500) is formed in the mixing tube (1420), and an introduction guide part (1426) is formed on the outside of the injection hole (1425) with an inner diameter that gradually increases toward the outside. The introduction guide part (1426) is formed as a curved surface, and when the introduction guide part (1426) is formed, the flow resistance can be reduced when fuel flows into the injection hole (1425).

The fuel injection pipe (1500) is connected to the injection hole (1425) and has an inlet (1521) through which fuel is introduced and an outlet (1523) through which fuel is discharged. The inlet (1521) may have an oval cross-section, and the outlet (1523) may have a circular cross-section.

In addition, an injection passage (1550) through which fuel moves is formed inside the fuel injection pipe (1500), and an injection tip (1510) whose outer diameter gradually decreases toward the tip is formed on the outlet side (1523) of the fuel injection pipe.

When the mixing tube (1420) is divided into four parts in the radial direction, the outlet (1523) can be located between 1/4 and 3/4 points from the outer side in the radial direction of the mixing tube (1420). That is, when the mixing tube (1420) is divided into four parts in the radial direction and regions are designated as P1, P2, P3, and P4 from the outermost side, the outlet (1523) can be located in the P2 region or the P3 region.

In this way, when the fuel is injected in an area adjacent to the center of the mixing tube (1420), the fuel concentration in the radial central portion of the mixing tube (1420) increases, thereby preventing flashback and effectively pushing out the flame.

Below, a nozzle according to a second embodiment of the present invention is described.

FIG. 6 is a perspective view illustrating a fuel injection pipe according to a second embodiment of the present invention.

Referring to FIG. 6, the nozzle according to the second embodiment has the same structure as the nozzle according to the first embodiment except for the fuel injection pipe (1600), so a duplicate description of the same configuration is omitted.

A fuel injection pipe (1600) protrudes into the inside of the mixing tube and is arranged at an angle with respect to the direction toward the center of the radius of the mixing tube. A plurality of fuel injection pipes (1600) may be arranged spaced apart from each other in the circumferential direction of the mixing tube in the mixing tube. An injection passage (1650) through which fuel moves is formed inside the fuel injection pipe (1600), and the injection passage (1650) is formed to extend in the longitudinal direction of the fuel injection pipe (1600). In addition, an injection tip (1610) is formed in the fuel injection pipe (1600) whose outer diameter gradually decreases toward the tip.

A guide protrusion (1630) is formed on the outer surface of the fuel injection pipe (1600), and the guide protrusion (1630) extends in the longitudinal direction of the fuel injection pipe (1600). A plurality of guide protrusions (1630) are formed on the fuel injection pipe (1600), and the guide protrusions (1630) can be spaced apart in the circumferential direction of the fuel injection pipe (1600).

As described above, according to the present embodiment, since a guide protrusion (1630) is formed in the fuel injection pipe (1600), the fuel injection pipe (1600) guides the flow of air and forms a swirl, so that air and fuel can be uniformly mixed.

Below, a nozzle according to a third embodiment of the present invention is described.

FIG. 7 is a perspective view illustrating a fuel injection pipe according to a third embodiment of the present invention.

Referring to FIG. 7, the nozzle according to the third embodiment has the same structure as the nozzle according to the first embodiment described above except for the fuel injection pipe (1700), so a duplicate description of the same configuration is omitted.

The fuel injection pipe (1700) protrudes into the inside of the mixing tube but is arranged at an angle with respect to the direction toward the center of the mixing tube. An injection passage (1750) through which fuel moves is formed inside the fuel injection pipe (1700), and a base portion (1720) whose outer diameter gradually decreases toward the tip of the fuel injection pipe (1700) is formed at a portion where the fuel injection pipe (1700) is connected to the mixing tube. In addition, an injection tip (1710) whose outer diameter gradually decreases toward the tip is formed on the fuel injection pipe (1700), and a connecting portion (1730) having a uniform outer diameter is formed between the injection tip (1710) and the base portion (1720). The minimum outer diameter of the base portion (1720) may be formed to be greater than or equal to the outer diameter of the connecting portion (1730) and the maximum outer diameter of the injection tip (1710).

When the fuel injection pipe (1700) includes a base portion (1720) as in the present embodiment, the flow recirculation of the fuel injected from the fuel injection pipe (1700) can be prevented and the fuel can be stably discharged.

Below, a nozzle according to the fourth embodiment of the present invention is described.

FIG. 8 is a perspective view showing a fuel injection pipe according to a fourth embodiment of the present invention, and FIG. 9 is a view of the fuel injection pipe according to the fourth embodiment of the present invention as seen from the front end.

Referring to FIGS. 8 and 9, the nozzle according to the fourth embodiment has the same structure as the nozzle according to the first embodiment described above except for the fuel injection pipe (1800), and therefore, a duplicate description of the same configuration is omitted.

The fuel injection pipe (1800) protrudes into the inside of the mixing tube, but is arranged at an angle with respect to the direction toward the center of the mixing tube. An injection passage (1850) through which fuel moves is formed inside the fuel injection pipe (1800), and an injection tip (1810) whose outer diameter gradually decreases toward the tip may be formed on the fuel injection pipe (1800).

In addition, a plurality of guide vanes (1860) extending in the longitudinal direction of the fuel injection pipe (1800) may be installed on the outer surface of the fuel injection pipe. The guide vanes (1860) may be formed in the shape of an airfoil or a flat plate, and guide the flow of air.

As described above, according to the present embodiment, since a guide vane is formed in the fuel injection pipe (1800), the fuel injection pipe (1800) guides the flow of air and forms a swirl, so that air and fuel can be uniformly mixed.

Above, one embodiment of the present invention has been described, but those skilled in the art will be able to modify and change the present invention in various ways by adding, changing, deleting or adding components, etc., within the scope that does not depart from the spirit of the present invention described in the claims, and this will also be considered to be included within the scope of the rights of the present invention.

1000: Gas turbine 1100: Compressor
1130: Compressor Blade 1140: Vane
1150: Housing 1200: Combustor
1210: Combustor casing 1220: Burner
1240: Combustion chamber 1400: Nozzle
1410: Multi-tube 1415: Tip plate
1418: Rear plate 1420: Mixing tube
1422: Inlet 1423: Nozzle
1425: Injection hole 1426: Introduction guide
1450: Fuel tube 1460: Front plate
1461: Center Hall 1462: Outer Hall
1500, 1600, 1700, 1800: Fuel Injector
1510, 1610, 1710, 1810: Injection tip 1521: Inlet
1523: Exit 1550, 1650, 1750, 1850: Injection passage
1630: Guide lug 1720: Base
1730: Joint 1860: Guide Wing

Claims (20)

In a nozzle for a combustor that burns fuel containing hydrogen,
A plurality of mixing tubes through which air and fuel move;
A multi-tube that supports by inserting the above mixing tubes;
A fuel tube formed inside the above multi-tube and through which fuel moves;
A tip plate coupled to the tip of the above multi-tube;
It comprises a plurality of fuel injectors that protrude into the mixing tube and inject fuel,
A nozzle for a combustor, characterized in that the fuel injection pipe is arranged to be inclined at a first angle with respect to the direction toward the center of the mixing tube. In the first paragraph,
A nozzle for a combustor, characterized in that the fuel injection pipe protrudes from the inner surface of the mixing tube in a direction facing downstream. In the second paragraph,
A nozzle for a combustor, characterized in that the fuel injection pipe is arranged to be inclined at a second angle with respect to the longitudinal direction of the mixing tube. In the second paragraph,
A nozzle for a combustor, characterized in that the inlet portion of the fuel injection pipe is formed in an oval shape and the outlet portion is formed in a circular shape. In the first paragraph,
An injection hole connected to the fuel injection pipe is formed in the above mixing tube,
A nozzle for a combustor, characterized in that an introduction guide part is formed in the injection hole, the inner diameter of which gradually increases toward the outside. In the first paragraph,
A nozzle for a combustor, characterized in that the fuel injector includes an injection tip whose outer diameter gradually decreases toward the tip. In the first paragraph,
The fuel injection pipe is connected to the mixing tube and has an inlet port through which fuel flows in and an outlet port through which fuel flows out.
A nozzle for a combustor, characterized in that the outlet portion is located between 1/4 and 3/4 from the outer side in the radial direction of the mixing tube. In the first paragraph,
A nozzle for a combustion chamber, characterized in that a plurality of guide protrusions are formed on the outer surface of the fuel injection pipe, extending in the longitudinal direction of the fuel injection pipe and spaced apart in the circumferential direction of the fuel injection pipe. In the first paragraph,
A nozzle for a combustion chamber, characterized in that a base portion is formed at a portion where the fuel injection pipe is connected to the mixing tube, the outer diameter of which gradually decreases toward the tip of the fuel injection pipe. In the first paragraph,
A nozzle for a combustion chamber, characterized in that a plurality of guide vanes extending in the longitudinal direction of the fuel injection pipe are installed on the outer surface of the fuel injection pipe. A combustor comprising a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to one side of the burner, wherein the fuel and the air are combusted inside and the combusted gas is delivered to a turbine,
A combustor characterized in that the nozzle includes a plurality of mixing tubes through which air and fuel move, a multi-tube for inserting and supporting the mixing tubes, a fuel tube formed inside the multi-tubes and through which fuel moves, a tip plate coupled to the tip of the multi-tubes, and a plurality of fuel injection tubes protruding into the mixing tubes and injecting fuel, and the fuel injection tubes are arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tubes. In Article 11,
A combustor characterized in that the fuel injection pipe protrudes from the inner surface of the mixing tube in a direction facing downstream. In Article 12,
A combustor, characterized in that the fuel injection pipe is arranged to be inclined at a second angle with respect to the longitudinal direction of the mixing tube. In Article 12,
A combustor characterized in that the inlet portion of the fuel injection pipe is formed in an oval shape and the outlet portion is formed in a circular shape. In Article 11,
An injection hole connected to the fuel injection pipe is formed in the above mixing tube,
A combustor characterized in that an introduction guide part is formed in the above injection hole, the inner diameter of which gradually increases toward the outside. In Article 11,
A combustor characterized in that the fuel injector includes an injection tip whose outer diameter gradually decreases toward the tip. In Article 11,
The fuel injection pipe is connected to the mixing tube and has an inlet port through which fuel flows in and an outlet port through which fuel flows out.
A combustor, characterized in that the outlet portion is located between 1/4 and 3/4 points from the radial outer side of the mixing tube. In Article 11,
A combustor characterized in that a plurality of guide protrusions are formed on the outer surface of the fuel injection pipe, extending in the longitudinal direction of the fuel injection pipe and spaced apart in the circumferential direction of the fuel injection pipe. In Article 11,
A combustor characterized in that a base portion is formed at the portion where the fuel injection pipe is connected to the mixing tube, the outer diameter of which gradually decreases toward the tip of the fuel injection pipe. A gas turbine comprising a compressor that compresses air taken in from the outside, a combustor that mixes compressed air compressed in the compressor with fuel and combusts it, and a turbine including a plurality of turbine blades that rotate by combustion gas combusted in the combustor.
The above combustor comprises a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to one side of the burner, wherein the fuel and the air are combusted inside and the combusted gas is delivered to a turbine.
A gas turbine according to claim 1, wherein the nozzle comprises a plurality of mixing tubes through which air and fuel move, a multi-tube for supporting the mixing tubes by inserting them, a fuel tube formed inside the multi-tubes and through which fuel moves, a tip plate coupled to the tip of the multi-tubes, and a plurality of fuel injection tubes protruding into the mixing tubes and injecting fuel, wherein the fuel injection tubes are arranged to be inclined at a first angle with respect to a direction toward the center of the mixing tubes.

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