KR102322597B1 - Nozzle assembly for combustor and gas turbine combustor including the same - Google Patents

Abstract

One embodiment of the present invention provides a nozzle assembly for a combustor, comprising: a central nozzle tube; an inner nozzle tube surrounding the central nozzle tube at a distance from the central nozzle tube; an outer nozzle tube surrounding the inner nozzle tube at a distance from the inner nozzle tube; a pilot fuel jetting part provided between the inner nozzle tube and the central nozzle tube; a main fuel jetting part provided between the outer nozzle part and the inner nozzle part; a pilot fuel supply tube provided to be extended in a longitudinal direction inside the central nozzle tube to supply fuel to the pilot fuel jetting part; and a main fuel supply tube provided to be extended in the longitudinal direction inside the central nozzle tube to supply fuel to the main fuel jetting part. In accordance with the present invention, as fuel is injected into two flow paths separated by a pilot annular ring and a main annular ring, respectively, a mixture state of the fuel and air can be improved, and ultimately the generation of nitrogen oxide can be reduced.

Description

NOZZLE ASSEMBLY FOR COMBUSTOR AND GAS TURBINE COMBUSTOR INCLUDING THE SAME

The present invention relates to a nozzle assembly for a combustor and a gas turbine combustor including the same, and more particularly, coaxial two-stage stratified combustion is possible, and as fuel is supplied through an annular ring, it has excellent fuel-air mixing properties and a flame It relates to a nozzle assembly for a combustor capable of increasing stability and a gas turbine combustor including the same.

In general, a gas turbine is a type of external combustion engine that converts thermal energy into mechanical energy by mixing fuel with high-pressure air compressed by a compressor and then injecting high-temperature and high-pressure combustion gas generated by combustion into the turbine and rotating it. Since these gas turbines do not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction part such as a piston-cylinder, so the consumption of lubricant is extremely low. There are advantages.

A gas turbine is a basic element, a compressor that compresses air, a combustor that burns the compressed air and fuel supplied from the compressor to generate combustion gas, and a turbine that rotates blades through high-temperature and high-pressure gas emitted from the combustor to generate power. includes

The combustion state generated in the combustor is an isobaric heating process that raises the temperature of the combustion gas to a temperature that the turbine metal can withstand. It corresponds to the part that performs the role of driving the turbine by transmitting it to the

1, the combustion air moves while cooling the combustor along between the sleeve 1 and the combustor liner 2, and after the direction of movement is changed, through the nozzle 3, the liner ( 2) and fuel is supplied from the nozzle (3), whereby fuel and air are ignited in the liner (2).

In the combustor, it is necessary to control the temperature of the reaction zone of the combustor to a low level so that air pollutants emitted through combustion, particularly nitrogen oxides (NOx), are formed below the reference value. To this end, fuel and air may be pre-mixed into a lean mixture before combustion in the nozzle 3 and supplied to the reaction zone of the combustor.

At this time, the fuel-air mixture leaving the combustor's premixing zone and entering the combustor's reaction zone must be very uniform to achieve the desired emission standards. This is because if there are regions where the fuel-air mixture is much more fuel-rich than average, combustion products in these regions can reach above-average temperatures and form thermal nitrogen oxides (NOx). Conversely, if there are regions where the fuel-air mixture is significantly lower than average in fuel shortage, the failure to oxidize hydrocarbons and/or carbon monoxide to equilibrium levels may result in quenching, which may result in unburned hydrocarbons (UHC) and/or carbon monoxide. Or it may not satisfy the emission standards of carbon monoxide (CO). Therefore, it is necessary to produce a sufficiently uniform fuel-air mixture distribution to meet the desired emission standards.

In addition, to achieve emission performance targets, it is necessary to reduce the fuel-air mixture strength to a level close to the lean flammability limit for most hydrocarbon fuels, resulting in reduced flame propagation rates and emissions. As a result, lean premixed combustors tend to be more unstable than typical diffuse flame combustors, and high levels of combustion driving dynamic pressure fluctuations occur. Since such dynamic pressure fluctuations can lead to negative consequences such as combustor damage, it is important to control the combustion dynamics to an acceptable low level.

For this purpose, conventionally, as disclosed in US Patent Application No. 6,438,961, a swozzle type burner having a cylindrical center body extending below the center line of the burner is provided. The end of the center body provides a bluff body to form a strong recirculation area where the flame is fixed, and thus can have excellent flame stability. However, the swozzle type burner as described above generally has a problem in that it does not achieve uniform mixing of fuel and air.

In addition, as disclosed in US Patent Application No. 5,165,241 in the prior art, a DACRS (Dual Annular Counter Rotating Swirler) type air-fuel mixer is provided. Such a DACRS type air-fuel mixer has excellent fuel-air mixing characteristics due to high fluid shear and turbulence. However, such a swirler does not generate a strong recirculation flow at the center line, and does not provide good flame stability because the flow structure in the combustion chamber is greatly changed by a sudden change of the turning angle occurring in the boundary layer. Accordingly, it is often necessary to additionally inject non-premixed fuel to stabilize the flame, and there is a problem in that the emission of nitrogen oxides (NOx) is increased by the non-premixed fuel.

US Patent Application No. 5,165,241 (Registered on Dec. 24, 1992) U.S. Patent Application No. 6,438,961 (registered on August 27, 2002)

The present invention is to solve the above problems, coaxial two-stage stratified combustion is possible, and as fuel is supplied through an annular ring, a nozzle assembly for a combustor that can improve flame stability while having excellent fuel-air mixing characteristics and to provide a gas turbine combustor comprising the same.

The technical problems to be achieved by the present invention are not limited to the technical problems mentioned above, and other technical problems not mentioned can be clearly understood by those of ordinary skill in the art to which the present invention belongs from the description below. There will be.

In order to solve the above problems, the present invention includes a pilot annular ring and a main annular ring for respectively injecting fuel into two separate flow paths between the coaxial triple tube. Accordingly, coaxial two-stage stratified combustion is possible, the circumferential fuel-air mixing degree can be improved, and flame stability can be greatly improved.

An embodiment of the present invention provides a central nozzle tube; and an inner nozzle tube that surrounds the central nozzle tube in a spaced apart state; and an outer nozzle tube that surrounds the inner nozzle tube in a spaced apart state; and the center nozzle tube. and a pilot fuel injection unit provided between the inner nozzle tube; and a main fuel injection unit provided between the inner nozzle tube and the outer nozzle tube; and the center nozzle for supplying fuel to the pilot fuel injection unit. a pilot fuel supply pipe provided to extend along the longitudinal direction inside the pipe; and a main fuel supply pipe provided to extend in the longitudinal direction inside the central nozzle pipe to supply fuel to the main fuel injection unit.

According to an embodiment of the present invention, the pilot fuel injector may include: a pilot annular ring disposed between the center nozzle pipe and the inner nozzle pipe; and a plurality of pilot struts extending radially from the central nozzle tube toward the pilot annular ring, wherein a first fuel channel is provided inside the pilot annular ring, and a second fuel channel is provided inside each pilot strut. Two fuel channels may be provided.

According to an embodiment of the present invention, each of the second fuel channels may communicate with the first fuel channel.

According to an embodiment of the present invention, the pilot fuel supply pipe is formed in plurality, the plurality of pilot fuel supply pipes are arranged to be spaced apart along the circumferential direction of the center nozzle pipe, and each pilot fuel supply pipe is each It may communicate with the second fuel channel.

According to an embodiment of the present invention, the pilot annular ring is provided with a plurality of first fuel injection holes along the circumferential direction, and the plurality of first fuel injection holes may communicate with the first fuel channel.

According to an embodiment of the present invention, one or more second fuel injection holes may be provided in each of the plurality of pilot struts, and the plurality of second fuel injection holes may communicate with the second fuel channel.

According to an embodiment of the present invention, the main fuel injection unit, the main annular ring disposed between the inner nozzle tube and the outer nozzle tube; and a plurality of main struts extending in a radial direction from the inner nozzle tube toward the main annular ring, wherein a third fuel channel is provided inside the main annular ring, and a second fuel channel is provided inside each of the main struts. 4 fuel channels may be provided.

According to an embodiment of the present invention, each of the fourth fuel channels may communicate with the third fuel channel.

According to an embodiment of the present invention, a plurality of first fuel supply struts extending in a radial direction from the central nozzle pipe to the inner nozzle pipe; may further include.

According to an embodiment of the present invention, a fifth fuel channel may be provided inside each of the first fuel supply struts.

According to an embodiment of the present invention, the plurality of first fuel supply struts are disposed to correspond to positions of the plurality of pilot struts, and each of the first fuel supply struts is downstream of the respective pilot struts in an air flow. can be placed in

According to an embodiment of the present invention, the main fuel supply pipe is formed in plurality, the plurality of main fuel supply pipes are arranged to be spaced apart along the circumferential direction of the central nozzle pipe, and each of the main fuel supply pipes is each It may communicate with the fifth fuel channel.

According to an embodiment of the present invention, a sixth fuel channel is provided inside the inner nozzle tube, and the sixth fuel channel may communicate with the plurality of fifth fuel channels and the plurality of fourth fuel channels. .

According to an embodiment of the present invention, a plurality of third fuel injection holes may be provided in the main annular ring along a circumferential direction, and the plurality of third fuel injection holes may communicate with the third fuel channel.

According to an embodiment of the present invention, one or more fourth fuel injection holes may be provided in each of the plurality of main struts, and the plurality of fourth fuel injection holes may communicate with the fourth fuel channel.

According to an embodiment of the present invention, the pilot fuel supply pipe is formed in plurality, the plurality of pilot fuel supply pipes are arranged to be spaced apart along the circumferential direction of the center nozzle pipe, and the main fuel supply pipe is formed in plurality, The plurality of main fuel supply pipes are arranged to be spaced apart along the circumferential direction of the central nozzle pipe, and the plurality of pilot fuel supply pipes and the plurality of main fuel supply pipes are alternately arranged in the circumferential direction inside the central nozzle pipe. can

According to an embodiment of the present invention, a flange installed at one end of the central nozzle pipe; and a pilot fuel injection pipe provided inside the flange and connected from an end surface of the flange to the pilot fuel supply pipe; and a main fuel injection pipe provided inside the flange and connected from an end surface of the flange to the main fuel supply pipe.

According to an embodiment of the present invention, the plurality of first fuel supply struts may be arranged at uniform intervals along the circumferential direction of the central nozzle tube.

In addition, an embodiment of the present invention for solving the above problems, a liner forming a combustion chamber therein; and a flow sleeve disposed to surround the liner to form an annular flow space therebetween; an end plate coupled to the front of the flow sleeve; and a nozzle assembly supported by the end plate and coupled to the front of the liner.

In addition, an embodiment of the present invention for solving the above problems is a compressor that sucks air and compresses it to a high pressure; combustor; and a turbine for generating electric power by obtaining rotational force by the combustion gas delivered from the combustor.

According to the present invention, as fuel is injected into the two flow paths separated between the coaxial triple tube by the pilot annular ring and the main annular ring, respectively, the fuel-air mixture can be improved, and ultimately the nitrogen of the gas turbine combustor Oxide (NOx) generation may be minimized.

In addition, since two-stage stratified combustion with different combustion conditions for pilot and main is possible, flame stability can be improved, and stable combustion is possible by suppressing combustion vibration.

In addition, as the fuel injection hole is additionally provided in the outer nozzle tube to inject fuel, fuel-air mixing can be enhanced even near the outer nozzle tube having a relatively long distance between adjacent struts.

It should be understood that the effects of the present invention are not limited to the above-described effects, and include all effects that can be inferred from the configuration of the invention described in the detailed description or claims of the present invention.

1 is a schematic cross-sectional view of a conventional gas turbine combustor.
Figure 2 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention.
FIG. 3 is an enlarged cross-sectional view of a combustor included in the gas turbine of FIG. 2 ;
4 is a cross-sectional view illustrating a nozzle assembly for a combustor according to an embodiment of the present invention.
5 is a side view of FIG. 4 as viewed from A;
Fig. 6 is a perspective view showing a part of Fig. 4;
7 is a conceptual diagram illustrating a fuel supply structure of the nozzle assembly of FIG. 4 .
Fig. 8 is a cross-sectional view of a central nozzle tube;
9 is a cross-sectional view of a pilot annular ring according to another embodiment.
10 is a side view of the pilot annular ring of FIG. 9 as viewed from the rear;
11 is a perspective view illustrating a part of a nozzle assembly for a combustor according to another embodiment;

Hereinafter, a preferred embodiment of a nozzle assembly for a combustor of the present invention and a gas turbine combustor including the same will be described with reference to the accompanying drawings.

In addition, the terms to be described below are terms defined in consideration of the functions in the present invention, which may vary according to the intention or custom of the user or operator, and the following embodiments do not limit the scope of the present invention but do not limit the scope of the present invention. It is merely exemplary of the elements presented in the claims.

In order to clearly explain the present invention, parts irrelevant to the description are omitted, and the same reference numerals are given to the same or similar elements throughout the specification. Throughout the specification, when a part "includes" a certain element, it means that other elements may be further included, rather than excluding other elements, unless otherwise stated.

First, a configuration of a gas turbine according to an embodiment of the present invention will be described with reference to FIGS. 2 and 3 .

A gas turbine according to an embodiment of the present invention includes a casing 10 , a compressor 20 for sucking in air and compressing it to a high pressure, and the air compressed by the compressor 20 is mixed with fuel and combusted. It may include a combustor 30 for generating power, and a turbine 40 for generating electric power by obtaining rotational force by the combustion gas delivered from the combustor 30 .

The casing 10 includes a compressor casing 12 in which the compressor 20 is accommodated, a combustor casing 13 in which the combustor 30 is accommodated, and a turbine casing 14 in which the turbine 40 is accommodated. can do. Here, the compressor casing 12, the combustor casing 13, and the turbine casing 14 may be sequentially arranged from an upstream side to a downstream side in a fluid flow direction.

A rotor 50 is rotatably provided inside the casing 10 , a generator (not shown) is interlocked with the rotor 50 for power generation, and the turbine 40 is located downstream of the casing 10 . A diffuser for discharging the combustion gas passing through may be provided.

The rotor 50 includes a compressor rotor disk 52 accommodated in the compressor casing 12 , a turbine rotor disk 54 accommodated in the turbine casing 14 , and the combustor casing 13 accommodated in the compressor. A torque tube 53 connecting the rotor disk 52 and the turbine rotor disk 54 , the compressor rotor disk 52 , the torque tube 53 , and a tie rod 55 connecting the turbine rotor disk 54 . and a fixing nut 56 .

The compressor rotor disk 52 may be formed in plurality, and the plurality of compressor rotor disks 52 may be arranged along the axial direction of the rotor 50 . That is, the compressor rotor disk 52 may be formed in multiple stages. In addition, each of the compressor rotor disks 52 may be formed in a substantially disk shape, and a compressor blade coupling slot coupled to a compressor blade 22 to be described later may be formed on an outer periphery thereof.

The turbine rotor disk 54 may be formed similarly to the compressor rotor disk 52 . That is, the turbine rotor disk 54 may be formed in plurality, and the plurality of turbine rotor disks 54 may be arranged along the axial direction of the rotor 50 . That is, the turbine rotor disk 54 may be formed in multiple stages. In addition, each of the turbine rotor disk 54 is formed in a substantially circular plate shape, the outer peripheral portion may be formed with a turbine blade coupling slot coupled to the turbine blade 42 to be described later.

The torque tube 53 is a torque transmission member that transmits the rotational force of the turbine rotor disk 54 to the compressor rotor disk 52 , and has one end at the most downstream in the air flow direction among the plurality of compressor rotor disks 52 . It may be engaged with the compressor rotor disk located at the end, and the other end may be engaged with the turbine rotor disk located at the most upstream end in the flow direction of the combustion gas among the plurality of turbine rotor disks 54 . Here, a protrusion is formed on each of one end and the other end of the torque tube 53 , and a groove engaged with the protrusion is formed on each of the compressor rotor disk 52 and the turbine rotor disk 54 , (53) relative rotation with respect to the compressor rotor disk (52) and the turbine rotor disk (54) can be prevented. In addition, the torque tube 53 may be formed in a hollow cylinder shape so that air supplied from the compressor 20 may flow to the turbine 40 through the torque tube 53 .

The tie rod 55 is formed to pass through the plurality of compressor rotor disks 52 , the torque tube 53 , and the plurality of turbine rotor disks 54 , and one end of the air of the plurality of compressor rotor disks 52 is formed. The compressor 20 is fastened in the compressor rotor disk located at the most upstream end in the flow direction, and the other end is located at the most downstream end in the flow direction of the combustion gas among the plurality of turbine rotor disks 54 based on the turbine rotor disk. It may protrude to the opposite side of the and be fastened to the fixing nut 56 .

Here, the fixing nut 56 presses the turbine rotor disk 54 located at the most downstream end toward the compressor 20 , and the compressor rotor disk 52 located at the most upstream end and the turbine located at the most downstream end. As the spacing between the rotor disks 54 is reduced, the plurality of compressor rotor disks 52 , the torque tube 53 and the plurality of turbine rotor disks 54 may be compressed in the axial direction of the rotor 50 . . Accordingly, axial movement and relative rotation of the plurality of compressor rotor disks 52 , the torque tube 53 and the plurality of turbine rotor disks 54 can be prevented.

Meanwhile, in the present embodiment, one tie rod is formed to pass through the central portions of the plurality of compressor rotor disks, the torque tube, and the plurality of turbine rotor disks, but is not limited thereto. That is, separate tie rods may be provided on the compressor side and the turbine side, respectively, and a plurality of tie rods may be radially disposed along the circumferential direction, and a mixture thereof is also possible.

The compressor 20 includes a compressor blade 22 rotated together with the rotor 50 and a compressor vane 24 installed in the compressor casing 12 to align the flow of air flowing into the compressor blade 22 . ) may be included.

The compressor blades 22 are formed in plurality, and the plurality of compressor blades 22 are formed in a plurality of stages along the axial direction of the rotor 50 , and radially along the rotation direction of the rotor 50 at each stage. can be formed with A root portion 22a of the compressor blade 22 engages a compressor blade engagement slot of the compressor rotor disk 52, and the root portion 22a connects the compressor blade 22 to the compressor blade engagement slot from the compressor blade engagement slot. It may be formed in a fir-tree shape to prevent the rotor 50 from being separated in the radial direction of rotation. In this case, the compressor blade coupling slot may be formed in the shape of a fir tree to correspond to the root portion 22a of the compressor blade.

In the present embodiment, the compressor blade root portion 22a and the compressor blade coupling slot are formed in a fir tree shape, but are not limited thereto and may be formed in a dovetail shape or the like. Alternatively, the compressor blade may be fastened to the compressor rotor disk using other fastening devices other than the above type, for example, a fastener such as a key or bolt.

Here, the compressor rotor disk 52 and the compressor blade 22 are typically coupled in a tangential type or an axial type. In this embodiment, the compressor blade root portion 22a is formed in a so-called axial type to be inserted into the compressor blade coupling slot along the axial direction of the rotor 50 . Accordingly, a plurality of the compressor blade coupling slots according to the present embodiment may be formed, and the plurality of compressor blade coupling slots may be radially arranged along the circumferential direction of the compressor rotor disk 52 .

The compressor vanes 24 may be formed in plurality, and the plurality of compressor vanes 24 may be formed in a plurality of stages along the axial direction of the rotor 50 . Here, the compressor vane 24 and the compressor blade 22 may be alternately arranged along the air flow direction. In addition, the plurality of compressor vanes 24 may be formed radially along the rotation direction of the rotor 50 for each stage.

The combustor 30 mixes the air flowing in from the compressor 20 with fuel and burns it to produce high-temperature and high-pressure combustion gas having high energy. The combustor 30 is formed in plurality, and the plurality of combustors 30 may be arranged in the combustor casing along the rotational direction of the rotor 50 .

As shown in FIG. 3 , each combustor 30 includes a liner 32 through which the compressed air from the compressor 20 flows, and a liner 32 located behind the liner 32 to convert combustion gas into the turbine ( 40 ) and a transition piece 34 . The liner 32 defines a combustion chamber 31 therein, and a flow sleeve 36 is disposed to surround the liner 32 and the transition piece 34 to form an annular flow space therebetween.

In addition, each combustor 30 includes a plurality of combustor nozzle assemblies 1000 for mixing the air and fuel supplied from the compressor 20 , and the nozzle assemblies 1000 are located in front of the liner 32 . is coupled to An end plate 38 is coupled to the front of the combustor casing 13 or the flow sleeve 36 , the nozzle assembly 1000 is supported by the end plate 38 , and the combustor may be sealed.

Cooling the liner 32 and the transition piece 34 exposed to the high-temperature and high-pressure combustion gas is an important part for increasing the durability of the combustor. To this end, the liner 32 through a plurality of collision holes defined by the combustor casing 13 and formed in the flow sleeve 36 from the receiving space in which the compressed air discharged from the compressor 20 is accommodated; Compressed air (combustion air) may be introduced into the annular flow path between the transition piece 34 and the flow sleeve 36 .

In this way, the compressed air introduced into the annular flow path between the liner 32, the transition piece 34 and the flow sleeve 36 cools the outer wall portions of the liner 32 and the transition piece 34, and the front of the combustor is moved to After reaching the end plate 38 , the compressed air is switched in the opposite direction and supplied to the nozzle assembly 1000 . As such, the compressed air flowing in from the compressor 20 is injected into the combustion chamber 31 while being mixed with fuel through the nozzle assembly 1000, and in the combustion chamber 31, a spark plug (not shown) is applied. is ignited and combustion occurs. Thereafter, the combusted gas is discharged to the turbine 40 through the transition piece 34 to generate rotational force. The structure of the nozzle assembly 1000 will be described in detail below.

Next, the turbine 40 may be formed similarly to the compressor 20 . The turbine 40 is a turbine blade 42 rotated together with the rotor 50 and a turbine vane ( 44) may be included.

The turbine blades 42 are formed in plurality, and the plurality of turbine blades 42 are formed in a plurality of stages along the axial direction of the rotor 50 , and radially along the rotation direction of the rotor 50 at each stage. can be formed with

A root portion 42a of the turbine blade 42 engages a turbine blade engagement slot of the turbine rotor disk 54 , and the root portion 42a connects the turbine blade 42 from its turbine blade engagement slot. In order to prevent the rotor 50 from being separated in the radial direction of rotation, it may be formed in a fir-tree shape. In this case, the turbine blade coupling slot may be formed in the shape of a fir tree to correspond to the root portion 42a of the turbine blade.

The turbine vanes 44 are formed in plurality, and the plurality of turbine vanes 44 may be formed in a plurality of stages along the axial direction of the rotor 50 . Here, the turbine vane 44 and the turbine blade 42 may be alternately arranged with each other along the air flow direction. In addition, the plurality of turbine vanes 44 may be radially formed along the rotational direction of the rotor 50 for each stage.

Here, the turbine 40, unlike the compressor 20, comes in contact with high-temperature and high-pressure combustion gas, and thus requires a cooling means to prevent damage such as deterioration. To this end, the compressor 20 may include a cooling passage for extracting compressed air from a portion of the compressor 20 and supplying it to the turbine 40 .

The cooling flow path may extend from the outside of the casing 10 (external flow path) or extend through the inside of the rotor 50 (internal flow path), and use both the external flow path and the internal flow path, depending on the embodiment. may be In this case, the cooling passage communicates with a turbine blade cooling passage formed inside the turbine blade 42 , so that the turbine blade 42 may be cooled by cooling air. In addition, the turbine blade cooling passage communicates with a turbine blade film cooling hole formed on the surface of the turbine blade 42 , and cooling air is supplied to the surface of the turbine blade 42 , so that the turbine blade 42 is It can be so-called film cooling by cooling air. The turbine vane 44 may also be cooled by receiving cooling air from the cooling passage similarly to the turbine blade 42 .

Here, the gas turbine is merely an embodiment of the present invention, and the combustor of the present invention, which will be described in detail below, may be widely applied to not only a general gas turbine, but also a jet engine in which air and fuel are combusted.

Hereinafter, the nozzle assembly 1000 for a combustor according to an embodiment of the present invention will be described in detail with reference to the accompanying FIGS. 4 to 6 .

The nozzle assembly 1000 for a combustor according to an embodiment of the present invention includes a central nozzle tube 100 , an inner nozzle tube 200 surrounding the center nozzle tube 100 in a spaced apart state, and the inner nozzle tube 200 . ) and an outer nozzle tube 300 surrounding the spaced apart state, and the center nozzle tube 100 , the inner nozzle tube 200 , and the outer nozzle tube 300 are coaxial. For this reason, a pilot flow path 220 is formed between the center nozzle pipe 100 and the inner nozzle pipe 200 , and a main flow path 320 is formed between the inner nozzle pipe 200 and the outer nozzle pipe 300 . is formed That is, two separate flow paths are formed due to the coaxial triple tube structure of the nozzle assembly 1000 .

A pilot fuel injector 400 for injecting fuel is provided between the center nozzle tube 100 and the inner nozzle tube 200 , that is, in the pilot passage 220 . The pilot fuel injector 400 may include a pilot annular ring 420 and a plurality of pilot struts 440 extending radially from the central nozzle tube 100 toward the pilot annular ring 420 . have. Although not limited thereto, the plurality of pilot struts 440 are preferably provided at uniform intervals along the circumferential direction.

The plurality of pilot struts 440 extend from the central nozzle tube 100 to the pilot annular ring 420 , and further radially from the pilot annular ring 420 toward the inner nozzle tube 200 . may be extended. In this embodiment, as shown in FIG. 5 , each of the plurality of pilot struts 440 includes a first pilot strut 440a extending from the central nozzle tube 100 to the pilot annular ring 420 and , a second pilot strut 440b extending radially from the pilot annular ring 420 toward the inner nozzle tube 200 . In this case, the radially outer end of the second pilot strut 440b is spaced apart from the inner nozzle tube 200 , but is not limited thereto, and the second pilot strut 440b extends up to the inner nozzle tube 200 . Of course, it may be extended.

As shown in FIG. 6 , the pilot annular ring 420 is provided with a plurality of first fuel injection holes 422 along the circumferential direction. The plurality of first fuel injection holes 422 are preferably provided on both the inner surface facing the radially inner side of the pilot annular ring 420 and the outer surface facing the radially outer side of the pilot annular ring 420 . Accordingly, fuel may be injected to both the radially inner and outer sides of the pilot annular ring 420 , and the fuel-air mixture may be improved. In addition, although not limited thereto, it is preferable that the plurality of first fuel injection holes 422 are uniformly provided along the circumferential direction of the pilot annular ring 420 . For example, as shown in FIG. 6 , the two first fuel injection holes 422 may be disposed at regular intervals between adjacent pilot struts 440 . Accordingly, the fuel-air is uniformly mixed along the circumferential direction of the pilot annular ring 420 and the degree of mixing can be improved.

In addition, according to an embodiment, a second fuel injection hole 442 may also be provided in each of the pilot struts 440 . It is preferable that the second fuel injection holes 442 are provided in plurality for each pilot strut 440 and are respectively formed on side surfaces of the pilot strut 440 facing each other in the circumferential direction. Accordingly, not only fuel can be injected radially by the first fuel injection hole 422 of the pilot annular ring 420 , but also by the second fuel injection hole 442 of the pilot strut 440 . Fuel may also be injected circumferentially. Accordingly, the fuel-air mixture can be improved, and a uniform fuel-air mixture can be produced. In this way, the number and position of the fuel injection holes may be adjusted to achieve a desired equivalence ratio distribution.

In addition, a main fuel injection unit 500 for injecting fuel is provided between the inner nozzle tube 200 and the outer nozzle tube 300 , that is, the main flow passage 320 . The main fuel injection unit 500 may include a main annular ring 520 and a plurality of main struts 540 extending radially from the inner nozzle tube 200 toward the main annular ring 520 . have. Although not limited thereto, the plurality of main struts 540 are preferably provided at uniform intervals along the circumferential direction.

The plurality of main struts 540 extend from the inner nozzle tube 200 to the main annular ring 520 , and further radially from the main annular ring 520 toward the outer nozzle tube 300 . may be extended. In this embodiment, as shown in FIG. 5 , each of the plurality of main struts 540 includes a first main strut 540a extending from the inner nozzle tube 200 to the main annular ring 520 and , consists of a second main strut (540b) extending radially from the main annular ring (520) toward the outer nozzle tube (300). At this time, the second main strut 540b extends to the outer nozzle tube 300, but is not limited thereto, and the radially outer end of the second main strut 540b is connected to the outer nozzle tube 300 and the outer nozzle tube 300. Of course, they may be separated. Also, of course, the first main strut 540a and the second main strut 540b may be alternately disposed in the circumferential direction of the main annular ring 520 .

The main annular ring 520 is provided with a plurality of third fuel injection holes 522 along the circumferential direction. The plurality of third fuel injection holes 522 are preferably provided on both the inner surface facing the radially inner side of the main annular ring 520 and the outer surface facing the radially outer side of the main annular ring 520 . Accordingly, both the fuel may be injected radially inside and outside of the main annular ring 520 , and the fuel-air mixture may be improved. In addition, although not limited thereto, it is preferable that the plurality of third fuel injection holes 522 are uniformly provided along the circumferential direction of the main annular ring 520 . For example, as shown in FIG. 6 , three third fuel injection holes 522 may be disposed at regular intervals between adjacent main struts 540 . Accordingly, fuel-air is uniformly mixed along the circumferential direction of the main annular ring 520 and the degree of mixing can be improved.

In addition, a fourth fuel injection hole 542 may be provided in each of the main struts 540 according to an embodiment. It is preferable that the fourth fuel injection holes 542 are provided in plurality for each main strut 540 and are respectively formed on side surfaces of the main strut 540 facing each other in the circumferential direction. Accordingly, fuel can be injected radially by the third fuel injection hole 522 of the main annular ring 520 as well as by the fourth fuel injection hole 542 of the main strut 540 . Fuel may also be injected circumferentially. Accordingly, the fuel-air mixture can be improved, and a uniform fuel-air mixture can be produced. In this way, the number and position of the fuel injection holes may be adjusted to achieve a desired equivalence ratio distribution.

At this time, the fuel-air concentration in the pilot flow passage 220 and the fuel-air concentration in the main flow passage 320 are differently adjusted to enable two-stage stratified combustion under different combustion conditions, It can greatly improve the flame stability. In particular, by adjusting the concentration of fuel in the pilot passage 220 to be higher than the concentration of fuel in the main passage 320 , flame stability in the center of the nozzle assembly 1000 may be enhanced. However, the present invention is not limited thereto, and the fuel-air concentration in the pilot flow passage 220 and the fuel-air concentration in the main flow passage 320 may be adjusted to be the same according to the driving purpose. Also, it goes without saying that the concentration of fuel in the pilot passage 220 may be adjusted to be lower than the concentration of fuel in the main passage 320 depending on the driving purpose.

Next, a structure for supplying fuel to the pilot annular ring 420 and the plurality of pilot struts 440 will be described with reference to FIGS. 7 and 8 . The pilot annular ring 420 and the plurality of pilot struts 440 each have a hollow. Accordingly, a first fuel channel 421 corresponding to a hollow annular annular shape is provided inside the pilot annular ring 420 , and the inside of each pilot strut 440 corresponds to a bar shape hollow. A second fuel channel 441 is provided. In this case, each of the second fuel channels 441 communicates with the first fuel channel 421 , and the fuel of the second fuel channel 441 may be delivered into the first fuel channel 421 .

In order to supply fuel from the outside of the nozzle assembly 1000 to the second fuel channel 441 of the pilot strut 440 , a pilot fuel supply pipe extending along the longitudinal direction of the center nozzle pipe 100 is inside the center nozzle pipe 100 . 102 is provided. The pilot fuel supply pipe 102 extends along the longitudinal direction of the central nozzle pipe 100 and communicates with the second fuel channel 441 of the pilot strut 440 . In this case, in order to supply fuel to each of the plurality of second fuel channels 441 formed in the plurality of pilot struts 440 , one pilot fuel supply pipe 102 may be provided for each pilot strut 440 . . That is, as shown in FIG. 8 , a plurality of pilot fuel supply pipes 102 may be formed to be spaced apart from each other inside the center nozzle pipe 100 .

Accordingly, the fuel introduced into the plurality of pilot fuel supply pipes 102 from the outside of the nozzle assembly 1000 is respectively supplied to the second fuel channels 441 of the pilot struts 440 , and the plurality of second It may be supplied from the fuel channel 441 to the first fuel channel 421 of the pilot annular ring 420 . At this time, since all of the plurality of first fuel injection holes 422 communicate with the first fuel channel 421 , the fuel supplied to the first fuel channel 421 communicates with the plurality of first fuels. It may be injected into the pilot passage 220 through the injection hole 422 . In addition, even when the plurality of second fuel injection holes 442 are formed in the pilot strut 440, since all of the plurality of second fuel injection holes 442 communicate with the second fuel channel 441, The fuel supplied to the second fuel channel 441 may be injected into the pilot passage 220 through the plurality of second fuel injection holes 442 communicating therewith.

As described above, the fuel may be directly introduced into the plurality of pilot fuel supply pipes 102 from the outside of the nozzle assembly 1000 , but according to an embodiment, the flange 120 installed at the front end of the central nozzle pipe 100 . may be introduced through To this end, a plurality of pilot fuel injection pipes 122 connected from an end surface of the flange 120 to the plurality of pilot fuel supply pipes 102 may be provided inside the flange 120 . That is, fuel may be respectively introduced into the plurality of pilot fuel supply pipes 102 from the end surface of the flange 120 through the plurality of pilot fuel injection pipes 122 .

Next, a structure for supplying fuel to the main annular ring 520 and the plurality of main struts 540 will be described. The main annular ring 520 and the plurality of main struts 540 each have a hollow. Accordingly, a third fuel channel 521 corresponding to a hollow annular ring shape is provided inside the main annular ring 520 , and the inside of each main strut 540 corresponds to a bar shape hollow A fourth fuel channel 541 is provided. In this case, each of the fourth fuel channels 541 communicates with the third fuel channel 521 , and the fuel of the fourth fuel channel 541 may be delivered into the third fuel channel 521 .

In order to supply fuel from the outside of the nozzle assembly 1000 to the fourth fuel channel 541 of the main strut 540 , a main fuel supply pipe extending along the longitudinal direction of the central nozzle pipe 100 is located inside the center nozzle pipe 100 . (104) is provided. In addition, a plurality of first fuel supply struts 240 extending from the center nozzle tube 100 to the inner nozzle tube 200 in a radial direction are provided in the pilot passage 220 . The plurality of first fuel supply struts 240 are preferably arranged at uniform intervals along the circumferential direction. Although not limited thereto, the plurality of first fuel supply struts 240 may be disposed at the rear end of each pilot strut 440 to correspond to positions of the plurality of pilot struts 440 . Each of the plurality of first fuel supply struts 240 has a hollow, and accordingly, a fifth fuel channel 241 corresponding to a bar-shaped hollow is provided inside each of the first fuel supply struts 240 . . For this reason, the main fuel supply pipe 104 extends along the longitudinal direction of the central nozzle pipe 100 to communicate with the fifth fuel channel 241 of the first fuel supply strut 240 . At this time, in order to supply fuel to each of the plurality of fifth fuel channels 241 formed in the plurality of first fuel supply struts 240 , the main fuel supply pipe 104 for each of the first fuel supply struts 240 . One of these may be provided. That is, as shown in FIG. 8 , a plurality of main fuel supply pipes 104 may be formed to be spaced apart from each other inside the central nozzle pipe 100 . Although not limited thereto, the plurality of pilot fuel supply pipes 102 and the plurality of main fuel supply pipes 104 are alternately disposed in the center nozzle pipe 100 in the circumferential direction.

The inner nozzle tube 200 has a hollow as well, and accordingly, a sixth fuel channel 201 corresponding to a hollow annular annular shape is provided inside the inner nozzle tube 200 . The sixth fuel channel 201 of the inner nozzle pipe 200 communicates with the plurality of fifth fuel channels 241 positioned inside the radial direction and at the same time, the plurality of fourth fuel channels positioned on the radially outer side ( 541).

Accordingly, the fuel introduced into the plurality of main fuel supply pipes 104 from the outside of the nozzle assembly 1000 is respectively supplied to the fifth fuel channel 241 of the first fuel supply strut 240 , and the plurality of fuel supply pipes 104 . It can be supplied to the sixth fuel channel 201 of the inner nozzle pipe 200 from the fifth fuel channel 241 of the. Subsequently, fuel is supplied from the sixth fuel channel 201 to the fourth fuel channel 541 of the main strut 540 , and the main annular ring 520 from the plurality of fourth fuel channels 541 . may be supplied to the third fuel channel 521 of At this time, since all of the plurality of third fuel injection holes 522 communicate with the third fuel channel 521 , the fuel supplied to the third fuel channel 521 communicates with the plurality of third fuels. It may be injected into the main flow path 320 through the injection hole 522 . In addition, since all of the plurality of fourth fuel injection holes 542 communicate with the fourth fuel channel 541 , the fuel supplied to the fourth fuel channel 541 communicates with the plurality of fourth fuels communicated therewith. It may be injected into the main flow path 320 through the injection hole 542 .

Similarly, fuel may be directly introduced into the plurality of main fuel supply pipes 104 from the outside of the nozzle assembly 1000 , but according to an embodiment, the flange 120 installed at the front end of the central nozzle pipe 100 may be used. It may be introduced through To this end, a plurality of main fuel injection pipes 124 connected from the end surface of the flange 120 to the plurality of main fuel supply pipes 104 may be provided inside the flange 120 . That is, fuel may be introduced into the plurality of main fuel supply pipes 104 through the plurality of main fuel injection pipes 124 from the end surface of the flange 120 , respectively.

A main swirler 700 may be further provided downstream of the main fuel injection unit 500 in the main flow path 320 . The main swirler 700 may generate a swirling flow to further improve the mixing characteristics of the fuel-air mixture. The main swirler 700 may have a structure to increase aerodynamic properties by having an airfoil-shaped cross-section, and may be simplified and applied to a plate-shaped structure. Meanwhile, although not shown, it goes without saying that a swirler may be further provided downstream of the pilot fuel injector 400 in the pilot passage 220 .

Since the main flow path 320 is positioned radially outside the pilot flow path 220 and has a larger diameter, the distance between the adjacent main struts 540 is relatively larger than the distance between the adjacent pilot struts 440 . far. For this reason, in the radial outer side of the main flow path 320 , that is, near the outer nozzle pipe 300 , the fuel injected by the main annular ring 520 and the main strut 540 does not reach the area (zero). -fuel area) may exist.

In this way, in order to prevent fuel-air mixing from occurring due to the occurrence of a region where fuel cannot reach near the outer nozzle tube 300, the present invention additionally provides the outer nozzle tube 300 according to an embodiment. ) may include a plurality of eighth fuel injection holes 302 provided in.

The plurality of eighth fuel injection holes 302 are provided on the inner surface facing the radially inner side of the outer nozzle tube 300 , so that fuel can be injected radially inward of the outer nozzle tube 300 . have. In addition, the plurality of eighth fuel injection holes 302 are provided along the circumferential direction of the outer nozzle tube 300 , and are preferably provided uniformly. For example, three eighth fuel injection holes 302 may be disposed at regular intervals between the adjacent main struts 540 . In particular, the eighth fuel injection hole 302 is located at a position where there is a high possibility that fuel cannot be reached by the third fuel injection hole 522 and the fourth fuel injection hole 542 , that is, at the center of the adjacent main strut 540 . ) is preferably arranged. Accordingly, even near the outer nozzle tube 300 , fuel-air mixing is uniformly performed along the circumferential direction, and excellent fuel-air mixing characteristics can be obtained.

In this case, with reference to FIG. 7 , a structure for supplying fuel to the outer nozzle pipe 300 will be described. The outer nozzle tube 300 has a hollow, and accordingly, an eighth fuel channel 301 corresponding to a hollow annular annular shape is provided inside the outer nozzle tube 300 . Since the plurality of eighth fuel injection holes 302 are all in communication with the eighth fuel channel 301, the fuel supplied to the eighth fuel channel 301 is in communication with the plurality of eighth fuel injection holes ( 302 may be injected into the main flow path 320 .

In addition, a plurality of second fuel supply struts 340 extending from the inner nozzle tube 200 to the outer nozzle tube 300 in a radial direction are provided in the main flow passage 320 . The plurality of second fuel supply struts 340 are preferably arranged at uniform intervals along the circumferential direction. Although not limited thereto, the plurality of second fuel supply struts 340 may be disposed at the rear end of each of the main struts 540 to correspond to the positions of the plurality of main struts 540 . Each of the plurality of second fuel supply struts 340 has a hollow, and accordingly, a seventh fuel channel 341 corresponding to a bar-shaped hollow is provided inside each of the second fuel supply struts 340 . . The plurality of seventh fuel channels 341 communicate with the sixth fuel channel 201 of the inner nozzle tube 200 located inside the radial direction and at the same time as the outer nozzle tube 300 located outside in the radial direction. It communicates with the eighth fuel channel 301 .

Accordingly, as described above, fuel flows from the outside of the nozzle assembly 1000 through the plurality of main fuel supply pipes 104 , the plurality of fifth fuel channels 241 , and the sixth fuel channel 201 . It may be supplied to the seventh fuel channel 341 of the second fuel supply strut 340 , and from the plurality of seventh fuel channels 341 to the eighth fuel channel 301 of the outer nozzle pipe 300 . can be supplied. The fuel supplied to the eighth fuel channel 301 may be injected into the main flow passage 320 through the plurality of eighth fuel injection holes 302 communicating therewith.

According to an embodiment, a structure having wrinkles up and down in the radial direction may be applied to the tail portion, which is the rear end of the airflow phase of the pilot annular ring 420 . 9 is a cross-sectional view of the pilot annular ring 420 to which a corrugated tail is applied, and FIG. 10 is a side view of the pilot annular ring 420 to which a corrugated tail is applied, as viewed from the rear end. The corrugated tail mixes the flow of the fuel-air mixture in the radial direction up and down in the pilot flow path 220, so that the fuel-air mixture can be further improved.

According to an embodiment, as shown in FIG. 11 , the first to fourth fuel injection holes 422 , 442 , 522 , and 542 may be formed toward the rear end of the nozzle assembly 1000 . That is, the plurality of first fuel injection holes 422 are at the rear end of the pilot annular ring 420 , and the plurality of second fuel injection holes 442 are at the rear end of the pilot strut 440 , and the The plurality of third fuel injection holes 522 are formed at the rear end of the main annular ring 520 , and the plurality of fourth fuel injection holes 542 are formed at the rear end of the main strut 540 . Accordingly, the fuel is injected toward the rear end of the nozzle assembly 1000 through the first to fourth fuel injection holes 422 , 442 , 522 , and 542 , so that the annular ring and the tail of the strut through high-speed fuel injection. It is possible to prevent the formation of a stagnation region in the As described above, as the fuel injection holes are formed toward the rear end of the nozzle assembly 1000 , it is possible to prevent combustion in the nozzle assembly 1000 due to the stagnant area, and at the same time, prevent the fuel injection holes from occurring in the nozzle assembly 1000 . Processing and inspection can be made easily. The eighth fuel injection hole 302 of the outer nozzle tube 300 is also provided on the radially inner surface of the outer nozzle tube 300 , and may be formed close to the rear end of the nozzle assembly 1000 , of course. am.

Next, looking at the process of assembling the nozzle assembly 1000 of the present invention, the central nozzle tube 100, the inner nozzle tube 200 and the outer nozzle tube 300, the fuel distributor shown in FIG. A main swirler 700 is installed, and if necessary, a flange 120 is installed at the front end of the central nozzle pipe 100 to configure the nozzle assembly 1000 , and it is attached to the end plate 38 . Thus, it can be installed in the combustor 30 . According to another embodiment, the outer nozzle tube 300 in which the main swirler 700 is installed is installed on the cover of the combustion chamber 31, and the remaining components are inserted into the outer nozzle tube 300 and assembled Accordingly, the nozzle assembly 1000 can be easily installed in the combustor 30 . That is, the center nozzle tube 100, the inner nozzle tube 200, the pilot fuel injection unit 400 and the main fuel injection into the inside of the outer nozzle tube 300 in which the main swirler 700 is installed. As the master part 500 is inserted in an assembled state, the final nozzle assembly 1000 is assembled.

The present invention is not limited to the specific embodiments and descriptions described above, and various modifications can be made by anyone skilled in the art without departing from the gist of the present invention as claimed in the claims. and such modifications shall fall within the protection scope of the present invention.

10: casing 12: compressor casing
13: combustor casing 14: turbine casing
20: compressor 22: compressor blade
22a: compressor blade root part 24: compressor vane
30: combustor 31: combustion chamber
32: liner 34: transition piece
36: floating sleeve 38: end plate
40: turbine 42: turbine blade
42a: turbine blade root portion 44: turbine vane
50: rotor 52: compressor rotor disk
53: torque tube 54: turbine rotor disk
55: tie rod 56: fixing nut
100: center nozzle pipe 102: pilot fuel supply pipe
104: main fuel supply pipe 120: flange
122: pilot fuel injection pipe 124: main fuel injection pipe
200: inner nozzle pipe 201: sixth fuel channel
220: pilot flow path 240: first fuel supply strut
241: fifth fuel channel 300: outer nozzle pipe
301: eighth fuel channel 302: eighth fuel injection hole
320: main flow path 340: second fuel supply strut
341: seventh fuel channel 400: pilot fuel injection unit
420: pilot annular ring 421: first fuel channel
422: first fuel injection hole 440: pilot strut
441: second fuel channel 442: second fuel injection hole
500: main fuel injection unit 520: main annular ring
521: third fuel channel 522: third fuel injection hole
540: main strut 541: fourth fuel channel
542: fourth fuel injection hole 700: main swirler
1000: nozzle assembly

Claims (20)

center nozzle tube;
an inner nozzle tube surrounding the center nozzle tube in a spaced apart state;
an outer nozzle tube surrounding the inner nozzle tube in a spaced apart state;
a pilot fuel injection unit provided between the central nozzle pipe and the inner nozzle pipe;
a main fuel injection unit provided between the inner nozzle tube and the outer nozzle tube;
a pilot fuel supply pipe provided to extend along the longitudinal direction inside the central nozzle pipe to supply fuel to the pilot fuel injection part;
a main fuel supply pipe provided to extend along the longitudinal direction inside the central nozzle pipe to supply fuel to the main fuel injection part; and
and a plurality of first fuel supply struts extending radially from the central nozzle tube to the inner nozzle tube.
According to claim 1,
The pilot fuel injection unit,
a pilot annular ring disposed between the center nozzle tube and the inner nozzle tube; and
a plurality of pilot struts extending radially from the central nozzle tube toward the pilot annular ring;
A nozzle assembly for a combustor, characterized in that a first fuel channel is provided inside the pilot annular ring, and a second fuel channel is provided inside each of the pilot struts.
3. The method of claim 2,
and each second fuel channel communicates with the first fuel channel.
4. The method of claim 3,
The pilot fuel supply pipe is formed in plurality, and the plurality of pilot fuel supply pipes are arranged to be spaced apart from each other in a circumferential direction of the center nozzle pipe,
and each pilot fuel supply pipe communicates with each of the second fuel channels.
5. The method of claim 4,
The pilot annular ring is provided with a plurality of first fuel injection holes along the circumferential direction,
The plurality of first fuel injection holes communicate with the first fuel channel, the combustor nozzle assembly.
5. The method of claim 4,
At least one second fuel injection hole is provided in each of the plurality of pilot struts,
The plurality of second fuel injection holes communicate with the second fuel channel, the combustor nozzle assembly.
According to claim 1,
The main fuel injection unit,
a main annular ring disposed between the inner nozzle tube and the outer nozzle tube; and
a plurality of main struts extending radially from the inner nozzle tube toward the main annular ring; and
A nozzle assembly for a combustor, characterized in that a third fuel channel is provided inside the main annular ring, and a fourth fuel channel is provided inside each of the main struts.
8. The method of claim 7,
and each of the fourth fuel channels communicates with the third fuel channel.
center nozzle tube;
an inner nozzle tube surrounding the center nozzle tube in a spaced apart state;
an outer nozzle tube surrounding the inner nozzle tube in a spaced apart state;
a pilot fuel injection unit provided between the central nozzle pipe and the inner nozzle pipe;
a main fuel injection unit provided between the inner nozzle tube and the outer nozzle tube;
a pilot fuel supply pipe provided to extend along the longitudinal direction inside the central nozzle pipe to supply fuel to the pilot fuel injection part; and
and a main fuel supply pipe provided to extend along the longitudinal direction inside the central nozzle pipe to supply fuel to the main fuel injection unit;
The pilot fuel supply pipe is formed in plurality, and the plurality of pilot fuel supply pipes are arranged to be spaced apart from each other in a circumferential direction of the center nozzle pipe,
The main fuel supply pipe is formed in plurality, and the plurality of main fuel supply pipes are arranged to be spaced apart from each other in the circumferential direction of the central nozzle pipe,
The nozzle assembly for a combustor, characterized in that the plurality of pilot fuel supply pipes and the plurality of main fuel supply pipes are alternately disposed in a circumferential direction inside the central nozzle pipe.
9. The method of claim 8,
A nozzle assembly for a combustor, characterized in that a fifth fuel channel is provided inside each of the first fuel supply struts.
3. The method of claim 2,
The plurality of first fuel supply struts are disposed to correspond to positions of the plurality of pilot struts,
wherein each of said first fueling struts is disposed downstream in the airstream of said respective pilot strut.
11. The method of claim 10,
The main fuel supply pipe is formed in plurality, and the plurality of main fuel supply pipes are arranged to be spaced apart from each other in the circumferential direction of the central nozzle pipe,
The nozzle assembly for a combustor, characterized in that each of the main fuel supply pipe communicates with the respective fifth fuel channel.
13. The method of claim 12,
A sixth fuel channel is provided inside the inner nozzle tube, and the sixth fuel channel communicates with the plurality of fifth fuel channels and the plurality of fourth fuel channels.
14. The method of claim 13,
The main annular ring is provided with a plurality of third fuel injection holes along the circumferential direction,
The plurality of third fuel injection holes communicate with the third fuel channel, the combustor nozzle assembly.
14. The method of claim 13,
At least one fourth fuel injection hole is provided in each of the plurality of main struts,
The plurality of fourth fuel injection holes communicate with the fourth fuel channel, the combustor nozzle assembly.
According to claim 1,
The pilot fuel supply pipe is formed in plurality, and the plurality of pilot fuel supply pipes are arranged to be spaced apart from each other in a circumferential direction of the center nozzle pipe,
The main fuel supply pipe is formed in plurality, and the plurality of main fuel supply pipes are arranged to be spaced apart from each other in the circumferential direction of the central nozzle pipe,
The nozzle assembly for a combustor, characterized in that the plurality of pilot fuel supply pipes and the plurality of main fuel supply pipes are alternately disposed in a circumferential direction inside the central nozzle pipe.
According to claim 1,
a flange installed at one end of the central nozzle pipe;
a pilot fuel injection pipe provided inside the flange and connected from an end surface of the flange to the pilot fuel supply pipe; and
The nozzle assembly for a combustor further comprising; a main fuel injection pipe provided inside the flange and connected from an end surface of the flange to the main fuel supply pipe.
According to claim 1,
A nozzle assembly for a combustor, characterized in that the plurality of first fuel supply struts are arranged at uniform intervals along a circumferential direction of the central nozzle tube.
a liner defining a combustion chamber therein;
a flow sleeve disposed to surround the liner to form an annular flow space therebetween;
an end plate coupled to the front of the flow sleeve; and
A gas turbine combustor comprising; a nozzle assembly according to any one of claims 1 to 18 supported by the end plate and coupled to the front of the liner.
a compressor that sucks in air and compresses it to a high pressure;
The combustor according to claim 19, which mixes and combusts the compressed air and fuel in the compressor to generate high-temperature, high-pressure combustion gas; and
A gas turbine comprising a; a turbine for generating electric power by obtaining rotational force by the combustion gas delivered from the combustor.

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