KR102343002B1 - Nozzle for combustor, combustor, and gas turbine including the same - Google Patents

Abstract

The present invention relates to a nozzle for a combustor, a combustor comprising the same, and a gas turbine. The nozzle for the combustor according to one aspect of the present invention comprises: a main cylinder having a fuel passage through which the fuel moves; a nozzle shroud surrounding the main cylinder; and a fuel spraying module disposed between the main cylinder and the nozzle shroud to spray a fuel. The fuel spraying module includes: a plurality of first pegs protruding from the main cylinder and having peg spraying holes for injecting the fuel; and a first support pipe coupled to outer ends of the first pegs. A plurality of intermediate spraying holes for spraying the fuel may be formed in the first support pipe. An objective of the present invention is to provide the nozzle capable of uniformly spraying the fuel, the combustor comprising the same, and the gas turbine.

Description

Nozzle for combustor, combustor comprising same, and gas turbine

The present invention relates to a nozzle for a combustor, a combustor comprising the same, and a gas turbine.

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

A gas turbine generally includes a compressor, a combustor and a turbine. The compressor sucks in the outside air, compresses it, and delivers it to the combustor. The compressed air in the compressor is in a state of high pressure and high temperature. The combustor mixes and combusts the compressed air introduced from the compressor and fuel. The combustion gases generated by the combustion are discharged to the turbine. The turbine blades inside the turbine are rotated by the combustion gas, and power is generated through this. The generated power is used in various fields such as power generation and driving of mechanical devices.

Fuel is injected through a nozzle installed in each combustor, and gaseous fuel may be pre-mixed and injected inside the nozzle. To reduce NOx, fuel and gas must be uniformly mixed. However, the conventional combustor nozzle has a problem in that fuel and air cannot be uniformly mixed.

Based on the technical background as described above, the present invention is to provide a nozzle capable of uniformly injecting fuel, a combustor including the same, and a gas turbine.

A nozzle for a combustor according to an aspect of the present invention includes a main cylinder having a fuel passage through which fuel moves, a nozzle shroud surrounding the main cylinder, and a fuel injection disposed between the main cylinder and the nozzle shroud to inject fuel a module, wherein the fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs, , A plurality of intermediate injection holes for injecting fuel may be formed in the first support pipe.

An intermediate transmission passage extending in a circumferential direction may be formed inside the first support tube according to an aspect of the present invention, and the intermediate transmission passage may be connected to a peg passage formed inside the first peg.

The fuel injection module according to an aspect of the present invention may include a plurality of more second pegs protruding from the first support pipe and having peg injection holes for injecting fuel.

A peg passage connected to the peg injection hole may be formed in the second peg according to an aspect of the present invention, and the peg passage may be connected to the intermediate transfer passage.

The fuel injection module according to an aspect of the present invention may further include a second support pipe connecting the outside of the second pegs and a plurality of third pegs protruding from the second support pipe.

In the nozzle shroud according to an aspect of the present invention, an outer transmission passage connected to the third pegs and extending in a circumferential direction of the nozzle shroud may be formed.

In the nozzle shroud according to an aspect of the present invention, a plurality of outer injection holes connected to the outer transmission passage and injecting fuel into the inner surface of the nozzle shroud may be formed.

The main cylinder according to an aspect of the present invention includes an inner tube and an outer tube surrounding the inner tube, and an inner vane is installed between the inner tube and the outer tube, and the fuel injection module is installed inside the inner vane. A connection passage for supplying fuel and an injection passage for supplying fuel to the injection hole formed in the inner vane may be formed, and the connection passage and the injection passage may be separated.

The main cylinder according to an aspect of the present invention further includes a distribution member for supplying fuel to the fuel injection module, wherein the distribution member is a first guide pipe fitted to the inner tube, spaced apart from the first guide pipe, A second guide tube fitted to the outer tube, and the inner vane positioned between the first guide tube and the second guide tube, the interior of the first guide tube is a first fuel tank connected to the connection passage A second fuel passage connected to the furnace and the injection passage may be formed.

A distribution passage extending in a circumferential direction of the second guide tube may be formed on an outer circumferential surface of the second guide tube according to an aspect of the present invention, and a plurality of connection passages may be connected to the distribution passage.

An outer swirler that forms a vortex may be installed in front of the injection module according to an aspect of the present invention.

The thickness of the first support tube according to an aspect of the present invention may be formed to gradually increase from the outside in the width direction of the first support tube to the center.

The first peg according to an aspect of the present invention further includes a guide plate protruding backward to guide the flow, and the guide plate is formed to protrude more rearward from the center in the height direction of the first peg to the outside. Nozzle for combustor.

The height of the first peg according to an aspect of the present invention may be formed to be greater than the height of the second peg.

A combustor according to another aspect of the present invention, a burner having a plurality of nozzles for injecting fuel and air, is coupled to one side of the burner, the fuel and the air are burned inside, and a duct assembly for delivering the combusted gas to the turbine The nozzle includes a main cylinder having a fuel passage through which fuel moves therein, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel and a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs, A plurality of intermediate injection holes for injecting fuel may be formed in the first support pipe.

An intermediate transmission passage extending in a circumferential direction is formed inside the first support tube according to another aspect of the present invention, and the intermediate transmission passage may be connected to a peg passage formed in the first peg.

The fuel injection module according to another aspect of the present invention may include a plurality of second pegs protruding from the first support pipe and having peg injection holes for injecting fuel.

A peg passage connected to the peg injection hole may be formed in the second peg according to another aspect of the present invention, and the peg passage may be connected to the intermediate transfer passage.

The main cylinder according to another aspect of the present invention includes an inner tube and an outer tube surrounding the inner tube, and an inner vane is installed between the inner tube and the outer tube, and the fuel injection module is installed inside the inner vane. A connection passage for supplying fuel and an injection passage for supplying fuel to the injection hole formed in the inner vane may be formed, and the connection passage and the injection passage may be separated.

The main cylinder according to another aspect of the present invention further comprises a distribution member for supplying fuel to the fuel injection module, the distribution member is a first guide pipe fitted to the inner tube, spaced apart from the first guide pipe, A second guide tube fitted to the outer tube, and the inner vane positioned between the first guide tube and the second guide tube, the interior of the first guide tube is a first fuel tank connected to the connection passage A second fuel passage connected to the furnace and the injection passage may be formed.

A gas turbine according to another aspect of the present invention includes a compressor that compresses air introduced from the outside, a combustor that mixes fuel with compressed air compressed in the compressor, and a plurality of rotating by the combustion gas burned in the combustor. A turbine including a turbine blade, wherein the combustor includes a burner having a plurality of nozzles for injecting fuel and air, coupled to one side of the burner, the fuel and the air are burned inside, and the combusted gas is converted into a turbine a duct assembly for delivering, wherein the nozzle includes a main cylinder having a fuel passage through which fuel moves therein, a nozzle shroud surrounding the main cylinder, and a fuel disposed between the main cylinder and the nozzle shroud to inject fuel an injection module, wherein the fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs and a plurality of intermediate injection holes for injecting fuel may be formed in the first support pipe.

In the nozzle for a combustor according to an aspect of the present invention, fuel is injected through the first peg and the support pipe, so that the fuel can be more uniformly injected.

1 is a view showing the inside of a gas turbine according to a first embodiment of the present invention.
FIG. 2 is a view showing the combustor of FIG. 1 .
3 is a cross-sectional view taken along the longitudinal direction of the nozzle according to the first embodiment of the present invention.
FIG. 4 is an enlarged view of area A1 in FIG. 4 .
5 is a cutaway perspective view of the distribution member according to the first embodiment of the present invention.
6 is a perspective view illustrating a fuel injection module according to a first embodiment of the present invention.
7 is a perspective view illustrating a first peg according to a first embodiment of the present invention.
8 is a cross-sectional view illustrating a first support pipe according to a second embodiment of the present invention.
9 is a cross-sectional view showing a first support pipe according to a third embodiment of the present invention.
10 is a cross-sectional view illustrating a fuel injection module according to a fourth embodiment of the present invention.

Since the present invention can apply various transformations and can have various embodiments, 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, and should be understood to include all modifications, equivalents, and substitutes included in the spirit and scope of the present invention.

The terms used in the present invention are only used to describe specific embodiments, and are not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly dictates otherwise. In the present invention, terms such as 'comprising' or 'having' are intended to designate that the features, numbers, steps, operations, components, parts, or combinations thereof described in the specification exist, and one or more other features It should be understood that this does not preclude the existence or addition of numbers, steps, operations, components, parts, or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this case, it should be noted that in the accompanying drawings, the same components are denoted by the same reference numerals 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 are exaggerated, omitted, or schematically illustrated in the accompanying drawings.

Hereinafter, a gas turbine according to a first embodiment of the present invention will be described.

FIG. 1 is a view showing the inside of a gas turbine according to an embodiment of the present invention, and FIG. 2 is a view showing the combustor of FIG. 1 .

The thermodynamic cycle of the gas turbine 1000 according to the present embodiment may ideally follow the Brayton cycle. The Brayton cycle can consist of four processes leading to isentropic compression (adiabatic compression), static pressure rapid heat, isentropic expansion (adiabatic expansion), and static pressure dissipation. That is, after sucking in air from the atmosphere, compressing it to high pressure, burning fuel in a static pressure environment to release heat energy, expanding this high-temperature combustion gas to convert it into kinetic energy, and then releasing the exhaust gas containing the remaining energy into the atmosphere. can That is, a cycle may be made in four processes of compression, heating, expansion, and heat dissipation.

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

Referring to FIG. 1 , a compressor 1100 of a gas turbine 1000 may suck air from the outside and compress it. The compressor 1100 may supply compressed air compressed by the compressor blade 1130 to the combustor 1200 , and may also supply cooling air to a high temperature region requiring cooling in the gas turbine 1000 . At this time, since the sucked air undergoes an adiabatic compression process in the compressor 1100 , the pressure and temperature of the air passing through the compressor 1100 are increased.

The compressor 1100 is designed as centrifugal compressors or axial compressors. In a small gas turbine, a centrifugal compressor is applied, whereas a large gas turbine 1000 as shown in FIG. 1 has a large amount of air. Since it is necessary to compress the multi-stage axial flow compressor 1100 is generally applied. At this time, in the multi-stage axial flow compressor 1100 , the blade 1130 of the compressor 1100 rotates according to the rotation of the rotor disk and moves the compressed air to the compressor vane 1140 of the rear stage while compressing the introduced air. As the air passes through the blades 1130 formed in multiple stages, it is compressed at a higher pressure.

The compressor vane 1140 is mounted inside the housing 1150 , and a plurality of compressor vanes 1140 may be mounted to form a stage. The compressor vane 1140 guides the compressed air moved from the compressor blade 1130 of the front end toward the blade 1130 of the rear end. In an embodiment, at least some of the plurality of compressor vanes 1140 may be mounted to be rotatable within a predetermined range for controlling an inflow amount of air.

The compressor 1100 may be driven using a portion of power output from the turbine 1300 . To this end, as shown in FIG. 1 , the rotation shaft of the compressor 1100 and the rotation shaft of the turbine 1300 may be directly connected. In the case of the large gas turbine 1000 , almost half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100 . Accordingly, improving the efficiency of the compressor 1100 has a direct effect on improving the overall efficiency of the gas turbine 1000 .

The turbine 1300 includes a rotor disk 1310 and a plurality of turbine blades 1320 and turbine vanes 1330 radially disposed on the rotor disk 1310 . The rotor disk 1310 has a substantially disk shape, and a plurality of grooves are formed on the outer periphery thereof. The groove is formed to have a curved surface, and the turbine blade 1320 and the turbine vane 1330 are inserted into the groove. The turbine blade 1320 may be coupled to the rotor disk 1310 in a dovetail or the like manner. The turbine vane 1330 is fixed to not rotate and guides the flow direction of the combustion gas passing through the turbine blade 1320 . The turbine blade 1320 generates rotational force while rotating by the combustion gas.

On the other hand, the combustor 1200 may mix the compressed air supplied from the outlet of the compressor 1100 with the fuel and perform isostatic combustion to produce combustion gas of high energy.

2 shows an example of a combustor 1200 applied to the gas turbine 1000 . The combustor 1200 may include a combustor casing 1210 , a burner 1220 , and a duct assembly 1250 .

The combustor casing 1210 surrounds the plurality of burners 1220 and may have a substantially cylindrical shape. The burner 1220 is disposed downstream of the compressor 1100 , and may be disposed along the combustor casing 1210 forming an annular shape. Each burner 1220 is provided with a plurality of nozzles 1400, and fuel injected from the nozzles 1400 is mixed with air in an appropriate ratio to achieve a state suitable for combustion.

In the gas turbine 1000 , gas fuel and liquid fuel, or a combination fuel thereof may be used. It is important to create a combustion environment to reduce the amount of exhaust gases such as carbon monoxide and nitrogen oxides, which are subject to legal regulation. Although combustion control is relatively difficult, it has the advantage of reducing exhaust gases by lowering the combustion temperature and creating uniform combustion. In recent years, premixed combustion is widely applied.

In the case of premixed combustion, compressed air is mixed with the fuel pre-injected from the nozzle 1400 and then enters the combustion chamber 1240 . The initial ignition of the premixed gas is performed using an igniter, and then, when the combustion is stabilized, the combustion is maintained by supplying fuel and air.

Referring to FIG. 2 , compressed air flows along the outer surface of the duct assembly 1250 through which the high-temperature combustion gas flows by connecting between the burner 1220 and the turbine 1300 and is supplied toward the nozzle 1400, in this process The duct assembly 1250 heated by the hot combustion gas is properly cooled.

Duct assembly 1250 can 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 flows into the cooling passage 1257 formed inside the flow sleeve 1253 . Penetrates to cool the liner 1251 and the transition piece 1252 .

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

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

A nozzle casing 1260 is coupled to an end of the duct assembly 1250 , and a head plate 1270 supporting the nozzles 1400 is coupled to the nozzle casing 1260 .

The nozzle casing 1260 is made of a substantially circular tube, and is installed to surround the plurality of nozzles 1400 . One end of the nozzle casing 1260 is coupled to the duct assembly 1250 , and the other end of the nozzle casing 1260 is coupled to the head plate 1270 installed at the rear of the nozzle casing 1260 . A plurality of nozzles 1400 may be installed inside the nozzle casing 1260 , and the nozzles 1400 may be arranged to be spaced apart from each other in a circumferential direction of the nozzle casing 1260 .

The head plate 1270 has a disk shape and is coupled to the nozzle casing 1260 to support the nozzles 1400 . A plurality of nozzles 1400 and a fuel injector for supplying fuel to the nozzles 1400 may be installed in the head plate 1270 . A nozzle flange 1470 supporting the nozzle may be fixed to the head plate 1270 .

3 is a cross-sectional view of the nozzle according to the first embodiment of the present invention cut in the longitudinal direction, and FIG. 4 is an enlarged view of the area A1 in FIG. 4 . 5 is a cutaway perspective view of the distribution member according to the first embodiment of the present invention.

3 to 5, the nozzle 1400 is installed between the main cylinder 1410 and the nozzle shroud 1420 surrounding the main cylinder 1410, the main cylinder 1410 and the nozzle shroud 1420. It may include an outer swirler 1460 for injecting fuel, a fuel injection module 1600 for injecting fuel between the main cylinder 1410 and the nozzle shroud 1420 , and a nozzle flange 1470 for supplying fuel. .

The main cylinder 1410 and the nozzle shroud 1420 have a coaxial structure, and fuel and air are supplied to the inside of the main cylinder 1410 . A first premixing passage 1451 through which air moves is formed in a space between the nozzle shroud 1420 and the main cylinder 1410 , and fuel may be injected into the first premixing passage 1451 . The main cylinder 1410 is coupled to the inner tube 1411 and the outer tube 1412 surrounding the inner tube 1411 , and the inner tube 1411 and the outer tube 1412 to supply fuel to the fuel injection module 1600 . It may include a distribution member 1500 that does.

A second premix passage 1452 is formed between the inner tube 1411 and the outer tube 1412, and an inner vane 1530 for injecting fuel is installed between the inner tube 1411 and the outer tube 1412. can The inner vanes 1530 may guide flow and inject fuel. Meanwhile, a main fuel passage 1453 through which fuel moves may be formed inside the inner tube 1411 . Liquid fuel may be injected into the main fuel passage 1453 , but the present invention is not limited thereto.

Air is introduced into the first premixing passage 1451 formed between the nozzle shroud 1420 and the main cylinder 1410 , and an inlet through which air is introduced may be formed at the rear end of the nozzle shroud 1420 . The distribution member 1500 is coupled to the main cylinder 1410 .

The distribution member 1500 is a first guide tube 1510 fitted to the inner tube 1411, a second guide tube 1520 spaced apart from the first guide tube 1510 and fitted to the outer tube 1412, and a second An inner vane 1530 positioned between the first guide tube 1510 and the second guide tube 1520 may be included. The first guide tube 1510 constitutes the inner tube 1411 , and the second guide tube 1520 constitutes the outer tube 1412 .

The rear end of the first guide pipe 1510 is connected to the nozzle flange 1470 to receive fuel from the nozzle flange 1470 . A first fuel passage 1541 for supplying fuel to the fuel injection module 1600 and a second fuel passage 1543 for supplying fuel to the inside of the inner vane 1530 are formed in the first guide tube 1510 . can

A first fuel inlet 1542 is formed at a rear end of the first fuel passage 1541 , and a second fuel inlet 1545 is formed at a rear end of the second fuel passage 1543 . The second fuel inlet 1545 may be located more rearward than the first fuel inlet 1542 . A plurality of first fuel passages 1541 and second fuel passages 1543 may be formed inside the first guide pipe 1510 , and the first fuel passage 1541 and the second fuel passage 1543 are 1 is disposed to be spaced apart in the circumferential direction of the guide tube (1510).

The inner vane 1530 is positioned between the inner tube 1411 and the outer tube 1412 to inject fuel into the space between the inner tube 1411 and the outer tube 1412, and forms a swirl. A connection passage 1531 for supplying fuel to the fuel injection module 1600 and an injection passage 1532 for supplying fuel to the vane injection hole 1533 formed in the inner vane 1530 are formed inside the inner vane 1530 . do. The connection passage 1531 and the injection passage 1532 are separated, so that the fuel in the connection passage 1531 and the fuel in the injection passage 1532 do not mix. The injection passage 1532 may be located further forward than the connection passage 1531 .

A distribution passage 1651 extending in the circumferential direction of the second guide tube 1520 is formed on the outer peripheral surface of the second guide tube 1520 , and a plurality of connection passages 1531 are connected to the distribution passage 1651 . The distribution passage 1651 is formed by the inner surface of the fuel injection module 1600 and the outer surface of the second guide tube 1520 .

As such, the distribution member 1500 according to the present embodiment injects some fuel into the first premixing passage 1451 through the inner vane 1530, and injects the remaining fuel into the second example through the fuel injection module 1600. It may be injected into the mixing passage 1452 . In addition, since movement and injection of fuel is performed by the inner vane 1530, fuel can be easily distributed and moved through a simple structure.

6 is a perspective view illustrating a fuel injection module according to a first embodiment of the present invention, and FIG. 7 is a perspective view illustrating a first peg according to the first embodiment of the present invention.

4, 6, and 7 , the fuel injection module 1600 is connected to the distribution member 1500 and injects fuel into the first premixing passage 1451 . The outer end of the fuel injection module 1600 is fitted into the nozzle shroud 1420 , and the inner end of the fuel injection module 1600 is fitted into the outer tube 1412 . The fuel injection module 1600 includes a first peg 1621 , a second peg 1622 , a third peg 1623 , an inner support tube 1611 , a first support tube 1612 , and a second support tube 1613 . , and an outer support tube 1614 .

The inner support pipe 1611 is coupled to the distribution member 1500 , and a plurality of inlets 1680 through which fuel is introduced may be formed in the inner support pipe 1611 . The inlet 1680 is spaced apart in the circumferential direction of the inner support pipe 1611 and is connected to the distribution passage 1651 .

A plurality of inner injection holes 1631 for injecting fuel are formed on the outer surface of the inner support pipe 1611 , and the inner injection holes 1631 are connected to the distribution passage 1651 . The inner support pipe 1611 constitutes the outer tube 1412 of the main cylinder 1410 , and accordingly, the main cylinder 1410 injects fuel into the first premixing passage 1451 through the inner support pipe 1611 . can do.

The first support pipe 1612 is coupled to the outer ends of the first pegs 1621 to support the first pegs 1621 . The inner support tube 1611 and the first support tube 1612 may have a circular annular shape and may be disposed in a coaxial structure.

An intermediate transmission passage 1652 extending in a circumferential direction is formed inside the first support tube 1612 , and the intermediate transmission passage 1652 is connected to the peg passage 1670 formed in the first peg 1621 to connect the first Fuel is delivered from the peg 1621 . In addition, the intermediate transmission passage 1652 is connected to the peg passage 1670 formed inside the second peg 1622 to deliver fuel to the second peg 1622 . A plurality of intermediate injection holes 1630 for injecting fuel are formed on the inner and outer surfaces of the first support pipe 1612 , and the intermediate injection holes 1630 are connected to the intermediate transmission passage 1652 .

The second support pipe 1613 is coupled to the outer ends of the second pegs 1622 to support the second pegs 1622 . The second support tube 1613 and the first support tube 1612 may have a circular annular shape and may be disposed in a coaxial structure.

An intermediate transmission passage 1653 extending in a circumferential direction is formed inside the second support pipe 1613 , and the intermediate transmission passage 1653 is connected to the peg passage 1670 formed inside the second peg 1622 to connect the second Fuel is delivered from the peg 1622 . In addition, the intermediate transmission passage 1653 is connected to the peg passage 1670 formed inside the third peg 1623 to deliver fuel to the third peg 1623 . A plurality of intermediate injection holes 1630 for injecting fuel are formed on the inner and outer surfaces of the second support pipe 1613 , and the intermediate injection holes 1630 are connected to the intermediate transmission passage 1653 .

The outer support pipe 1614 is coupled to the outer ends of the third pegs 1623 to support the third pegs 1623 . The outer support pipe 1614 has a circular annular shape and is inserted into the nozzle shroud 1420 to configure the nozzle shroud 1420 .

An outer transmission passage 1654 extending in a circumferential direction is formed inside the outer support tube 1614 , and the outer transmission passage 1654 is connected to the peg passage 1670 formed inside the third peg 1623 to connect the third peg (1623) receive fuel delivery. A plurality of outer injection holes 1632 for injecting fuel are formed on the inner surface of the outer support pipe 1614 , and the outer injection holes 1632 are connected to the outer transmission passage 1654 .

Since the outer support tube 1614 forms a part of the nozzle shroud 1420 , the outer delivery passage 1654 and the outer injection hole 1632 are formed in the nozzle shroud 1420 , and the nozzle passes through the outer support tube 1614 . The shroud 1420 may inject fuel into the first premixing passage 1451 .

The first peg 1621 protrudes from the main cylinder 1410 and has a peg injection hole 1640 for injecting fuel. In more detail, the first peg 1621 protrudes from the inner support pipe 1611 constituting the main cylinder 1410 . A peg passage 1670 is formed inside the first peg 1621 , and the peg passage 1670 is connected to the outer support tube 1614 and the first support tube 1612 , and the peg injection hole 1640 . The first peg 1621 is positioned between the inner support tube 1611 and the first support tube 1612 .

The first peg 1621 includes a first side 1661 having a width gradually increasing from the rear end to the center, and a second side side 1662 having a width gradually decreasing from the center to the front end. The length of the first side 1661 is formed to be shorter than the length of the second side 1662 .

A guide plate 1663 protruding backward to guide the flow is formed at the rear end of the first peg 1621 , and the guide plate 1663 guides air flowing into the first peg 1621 . The guide plate 1663 is formed to protrude more rearward from the center in the height direction of the first peg 1621 to the outside. The guide plate 1663 may be formed of two triangular plates. When the guide plate is formed in this way, it is possible to more stably guide the flow of air. In addition, when the guide plate 1663 protrudes further from the center toward the outside, it is possible to more stably induce the flow of the upper end and the lower end with severe friction.

The second peg 1622 protrudes from the first support pipe 1612 and has a peg injection hole 1640 for injecting fuel. A peg passage 1670 is formed inside the second peg 1622 , and the peg passage 1670 is connected to the first support tube 1612 and the second support tube 1613 , and the peg injection hole 1640 . . The second peg 1622 is positioned between the first support tube 1612 and the second support tube 1613 .

The third peg 1623 protrudes from the second support pipe 1613 and has a peg injection hole 1640 for injecting fuel. A peg passage 1670 is formed inside the third peg 1623 , and the peg passage 1670 is connected to the second support tube 1613 , the outer support tube 1614 , and the peg injection hole 1640 . The second peg 1622 and the third peg 1623 have the same structure as the first peg 1621 . The third peg 1623 is positioned between the second support tube 1613 and the outer support tube 1614 . The second peg 1622 is positioned more outward than the first peg 1621 , and the third peg 1623 is positioned more outward than the second peg 1622 .

Meanwhile, as shown in FIG. 3 , an outer swirler 1460 that forms a vortex is installed in front of the fuel injection module 1600 . The outer swirler 1460 includes a plurality of swirler vanes, and mixes air and fuel injected from the fuel injection module 1600 . However, the outer swirler 1460 does not inject fuel.

When the outer swirler 1460 is installed in front of the fuel injection module 1600 as in the first embodiment, the outer swirler 1460 mixes the injected fuel, so that fuel and air can be more uniformly mixed. In addition, the fuel injection module 1600 includes a plurality of pegs 1621 , 1622 , 1623 and support pipes 1611 , 1612 , 1613 , 1614 , and the pegs 1621 , 1622 , 1623 and the support pipes Since fuel is injected through 1611 , 1612 , 1613 , and 1614 , fuel can be uniformly injected into the first premixing passage 1451 . In particular, since the volume of the first premixing passage 1451 increases in proportion to the square of the radius, there is a problem that fuel is relatively scarce in the outer portion of the first premixing passage 1451, but according to the first embodiment, the pegs A sufficient amount of fuel can also be injected into the outer portion through the 1621 , 1622 , 1623 and the support pipes 1611 , 1612 , 1613 , and 1614 .

Hereinafter, a gas turbine according to a second embodiment of the present invention will be described. 8 is a cross-sectional view illustrating a first support pipe according to a second embodiment of the present invention.

Referring to FIG. 8 , the gas turbine according to the second embodiment has the same structure as the gas turbine according to the first embodiment, except for the first support pipe 2620 , and thus overlaps with the same configuration. A description is omitted.

The first support tube 2620 is formed of a circular tube and includes a front protrusion 2625 , a rear protrusion 2624 , and a convex portion 2626 . The front protrusion 2625 and the rear protrusion 2624 may be formed in a plate shape, and the convex part 2626 is positioned between the front protrusion 2625 and the rear protrusion 2624 . The front projection 2625 projects forward from the convex portion 2626 , and the rear projection 2624 projects rearward from the projection 2626 . The convex portion 2626 may have a structure in which an outer surface is convexly curved.

The first support pipe 2620 is formed such that the thickness T1 gradually increases from the outside in the width direction to the center by the convex portion 2626 . An intermediate transmission passage 2621 extending in a circumferential direction is formed inside the first support pipe 2620 , and a peg injection hole 2623 for injecting fuel is connected to the intermediate transmission passage 2621 . The second support tube and the third support tube according to the second embodiment have the same structure as the first support tube 2620 .

As described above, according to the second embodiment, even if the intermediate transmission passage 2621 is formed inside the ring-shaped first support tube 2620, it is possible to minimize the first support tube 2620 from interfering with the flow. have. In addition, air is pressurized in the convex portion 2626 to stabilize the flow of air.

Hereinafter, a gas turbine according to a third embodiment of the present invention will be described. 9 is a cross-sectional view showing a first support pipe according to a third embodiment of the present invention.

Referring to FIG. 9 , the gas turbine according to the third embodiment has the same structure as the gas turbine according to the first embodiment, except for the first support pipe 3620 , and thus overlaps with respect to the same configuration. A description is omitted.

The first support tube 3620 is formed as a circular tube and gradually increases in thickness from the outside in the width direction to the center. A cross-section in the width direction of the plate constituting the first support pipe 3620 may be formed in a rhombus shape.

An intermediate transmission passage 3621 extending in a circumferential direction is formed inside the first support pipe 3620 , and a peg injection hole 3623 for injecting fuel is connected to the intermediate transmission passage 3621 . The second support tube and the third support tube according to the third embodiment have the same structure as the first support tube 3620 .

As described above, according to the third embodiment, even when the intermediate transmission passage 3621 is formed inside the first support tube 3620 , it is possible to minimize the obstruction of the flow of the first support tube 3620 . In addition, the air may be pressurized at the convex portion to stabilize the air flow.

Hereinafter, a gas turbine according to a fourth embodiment of the present invention will be described. 10 is a cross-sectional view illustrating a fuel injection module according to a fourth embodiment of the present invention.

Referring to FIG. 10 , since the gas turbine according to the fourth embodiment has the same structure as the gas turbine according to the first embodiment, except for the fuel injection module 4600 , redundant description of the same configuration is omitted.

The fuel injection module 4600 may include a first peg 4621 , a second peg 4622 , an inner support tube 4611 , a first support tube 4612 , and an outer support tube 4614 .

The inner support pipe 4611 is coupled to the distribution member 4500, and an inner circumferential surface forms a distribution passage 4651 between the inner circumferential surface and the distribution member. The first support pipe 4612 is coupled to the outer ends of the first pegs 4621 to support the first pegs 4621 . An intermediate transmission passage 4652 extending in the circumferential direction is formed inside the first support tube 4612 .

The outer support pipe 4614 is coupled to the outer ends of the second pegs 4622 to support the second pegs 4622 . The outer support pipe 4614 has a circular annular shape and is inserted into the nozzle shroud to configure the nozzle shroud. An intermediate transmission passage 4653 extending in the circumferential direction is formed inside the outer support tube 4614 .

The first peg 4621 protrudes from the inner support pipe 4611 , and a peg injection hole 4630 is formed in the first peg 4621 . The first peg 4621 is positioned between the inner support tube and the first support tube 4612 . The second peg 4622 protrudes from the first support pipe, and a peg injection hole 4630 is formed in the second peg 4622 . The second peg 4622 is positioned between the first support tube 4612 and the outer support tube 4614 . The first peg 4621 is located more inward than the second peg 4622 .

The height H1 of the first peg 4621 is formed to be greater than the height H2 of the second peg 4622 . Here, the first peg 4621 and the second peg 4622 may inject the same amount of fuel. As the volume increases in proportion to the square of the radius from the inside to the outside, the fuel in the outer region becomes relatively lean. However, according to the present embodiment, a sufficient amount of fuel may be supplied to the outer region in which the fuel is relatively thin, thereby supplying a uniform fuel as a whole.

In the above, an embodiment of the present invention has been described, but those of ordinary skill in the art can add, change, delete or add components within the scope that does not depart from the spirit of the present invention described in the claims. The present invention may be variously modified and changed by, etc., and this will also be included within the scope of the present invention.

1000: gas turbine 1100: compressor
1130 compressor blade 1140 compressor vane
1150: housing 1200: combustor
1210: combustor casing 1220: burner
1240: combustion chamber 1250: duct assembly
1251: liner 1252: transition piece
1253: floating sleeve 1260: nozzle casing
1270: head plate 1300: turbine
1310: rotor disk 1320: turbine blades
1330: turbine vane 1400: nozzle
1410: main cylinder 1411: inner tube
1412: outer tube 1420: nozzle shroud
1451: first pre-mixing passage 1452: second pre-mixing passage
1460: outer swirler 1470: nozzle flange
1500: distribution member 1510: first guide tube
1520: second guide tube 1530: inner vane
1541: first fuel passage 1543: second fuel passage
1531: connecting passage 1532): injection passage
1533: vane injection hole 1600, 4600: fuel injection module
1621, 4621: first peg 1622, 4622: second peg
1623: third peg 1611, 4611: inner support tube
1612, 2620, 3620, 4612: first support tube
1613: second support tube 1614, 4614: outer support tube
1630: intermediate injection hole 1631: inner injection hole
1632: outer injection hole 1640, 2623, 3623: peg injection hole
1651: distribution passageway 1654: outer delivery passageway
1652, 1653, 2621, 3621: intermediate transmission passage
1661: first side 1662: second side
1663: information board 1670: peg passage
2625: front protrusion 2624: rear protrusion
2626: convex part

Claims (20)

a main cylinder having a fuel passage through which the fuel moves;
a nozzle shroud surrounding the main cylinder; and
a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel;
includes,
The fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs,
A plurality of intermediate injection holes for injecting fuel are formed in the first support pipe,
The thickness of the first support tube is a nozzle for a combustor, characterized in that it is formed to gradually increase from the outside in the width direction of the first support tube toward the center. According to claim 1,
An intermediate transmission passage extending in a circumferential direction is formed inside the first support pipe, and the intermediate transmission passage is connected to a peg passage formed inside the first peg. According to claim 1,
The fuel injection module may further include a plurality of second pegs protruding from the first support pipe and having peg injection holes for injecting fuel. 4. The method of claim 3,
A peg passage connected to the peg injection hole is formed in the second peg, and the peg passage is connected to the intermediate transfer passage. 5. The method of claim 4,
The fuel injection module further includes a second support pipe connecting the outside of the second pegs and a plurality of third pegs protruding from the second support pipe,
The nozzle for a combustor, characterized in that the nozzle shroud is connected to the third pegs and formed with an outer transmission passage extending in a circumferential direction of the nozzle shroud. 6. The method of claim 5,
A nozzle for a combustor, characterized in that the nozzle shroud has a plurality of outer injection holes connected to the outer transmission passage and injecting fuel into the inner surface of the nozzle shroud. According to claim 1,
The main cylinder includes an inner tube and an outer tube surrounding the inner tube, and an inner vane is installed between the inner tube and the outer tube,
A connection passage for supplying fuel to the fuel injection module and an injection passage for supplying fuel to an injection hole formed in the inner vane are formed inside the inner vane,
The nozzle for a combustor, characterized in that the connection passage and the injection passage are separated. 8. The method of claim 7,
The main cylinder further includes a distribution member for supplying fuel to the fuel injection module,
The distribution member includes a first guide tube fitted to the inner tube, a second guide tube spaced apart from the first guide tube and fitted into the outer tube, and positioned between the first guide tube and the second guide tube comprising the inner vane,
A first fuel passage connected to the connection passage and a second fuel passage connected to the injection passage are formed inside the first guide tube. 9. The method of claim 8,
A distribution passage extending in a circumferential direction of the second guide tube is formed on an outer peripheral surface of the second guide tube, and a plurality of connection passages are connected to the distribution passage. According to claim 1,
A nozzle for a combustor, characterized in that an outer swirler forming a vortex is installed in front of the injection module. delete a main cylinder having a fuel passage through which the fuel moves;
a nozzle shroud surrounding the main cylinder; and
a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel;
includes,
The fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs,
A plurality of intermediate injection holes for injecting fuel are formed in the first support pipe,
The first peg further includes a guide plate protruding backward to guide the flow, and the guide plate is formed to protrude more rearward from the center in the height direction of the first peg to the outside. 4. The method of claim 3,
A nozzle for a combustor, characterized in that the height of the first peg is formed to be greater than the height of the second peg. A burner having a plurality of nozzles for injecting fuel and air, coupled to one side of the burner, the fuel and the air are combusted therein, and a duct assembly for delivering the burned gas to the turbine,
The nozzle includes a main cylinder having a fuel passage through which fuel moves therein, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel,
The fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs, and the first support A plurality of intermediate injection holes for injecting fuel are formed in the tube,
A combustor, characterized in that the thickness of the first support tube is formed to gradually increase from the outside in the width direction of the first support tube toward the center. 15. The method of claim 14,
An intermediate transmission passage extending in a circumferential direction is formed inside the first support tube, and the intermediate transmission passage is connected to a peg passage formed inside the first peg. 15. The method of claim 14,
wherein the fuel injection module protrudes from the first support pipe and includes a plurality of second pegs in which peg injection holes for injecting fuel are formed. 17. The method of claim 16,
A peg passage connected to the peg injection hole is formed in the second peg, and the peg passage is connected to the intermediate transfer passage. 15. The method of claim 14,
The main cylinder includes an inner tube and an outer tube surrounding the inner tube, and an inner vane is installed between the inner tube and the outer tube,
A connection passage for supplying fuel to the fuel injection module and an injection passage for supplying fuel to an injection hole formed in the inner vane are formed inside the inner vane,
The combustor, characterized in that the connection passage and the injection passage are separated. 19. The method of claim 18,
The main cylinder further includes a distribution member for supplying fuel to the fuel injection module,
The distribution member includes a first guide tube fitted to the inner tube, a second guide tube spaced apart from the first guide tube and fitted into the outer tube, and positioned between the first guide tube and the second guide tube comprising the inner vane,
A first fuel passage connected to the connection passage and a second fuel passage connected to the injection passage are formed inside the first guide tube. A gas turbine including a compressor for compressing air introduced from the outside, a combustor for mixing and burning compressed air and fuel compressed in the compressor, and a turbine including a plurality of turbine blades rotated by the combustion gas burned in the combustor As,
The combustor includes a burner having a plurality of nozzles for injecting fuel and air, a duct assembly coupled to one side of the burner, the fuel and the air are combusted inside, and a duct assembly for delivering the combusted gas to a turbine,
The nozzle includes a main cylinder having a fuel passage through which fuel moves therein, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel,
The fuel injection module includes a plurality of first pegs protruding from the main cylinder and having peg injection holes for injecting fuel, and a first support pipe coupled to outer ends of the first pegs, and the first support A plurality of intermediate injection holes for injecting fuel are formed in the tube,
The thickness of the first support tube is a gas turbine, characterized in that it is formed to gradually increase from the outside to the center in the width direction of the first support tube.

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