KR20210133023A - Nozzle for combustor, and combustor including the same - Google Patents

Abstract

The present invention relates to a nozzle for a combustor and the combustor including the same. The nozzle for a combustor according to one aspect of the present invention comprises: a main cylinder in which a fuel passage through which a fuel moves is formed; a nozzle shroud which surrounds the main cylinder; and a nozzle vane which is formed between the main cylinder and the nozzle shroud to inject the fuel and guide a flow. A cavity connected to the fuel passage is formed inside the nozzle vane. An injection hole for injecting the fuel into a space between the main cylinder and the nozzle shroud is formed in the cavity. The inclined surface for guiding the flow of the fuel may be formed at a portion where the cavity and the fuel passage are connected. An objective of the present invention is to provide the nozzle for a combustor, capable of uniformly injecting the fuel through the nozzle vane, and the combustor.

Description

Nozzle for combustor and combustor including same

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

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 and fuel introduced from the compressor. The combustion gases generated by the combustion are discharged to the turbine. The combustion gas causes the turbine blades inside the turbine to rotate, which in turn generates power. The generated power is used in various fields such as power generation and driving of mechanical devices.

The compressed air from the compressor is supplied to the combustor, and the air entering the combustor moves along the inside of the nozzle casing and flows into the nozzle. The fuel is supplied to the nozzle and mixed with air, and the premixed air mixed with the fuel is supplied to the tip of the nozzle to form a flame. Nitrogen oxide can be reduced only when fuel and air are uniformly mixed.

Fuel is injected into the space between the main cylinder and the nozzle shroud through a hole formed in the wing-shaped nozzle vane. There is a problem that prevents the uniform injection of If the fuel is not uniformly supplied, not only combustion efficiency is lowered, but also a problem of increasing nitrogen oxide may occur.

Based on the technical background as described above, an object of the present invention is to provide a combustor and a nozzle for a combustor capable of uniformly injecting fuel through a nozzle vane.

A nozzle for a combustor according to an aspect of the present invention is formed between a main cylinder having a fuel passage through which fuel moves, a nozzle shroud surrounding the main cylinder, and the main cylinder and a nozzle shroud, injecting fuel and guiding the flow and a nozzle vane that injects fuel into a space between the main cylinder and the nozzle shroud in the cavity, wherein a cavity connected to the fuel passage is formed in the nozzle vane, and the cavity and An inclined surface for guiding the flow of fuel may be formed at a portion to which the fuel passage is connected.

The nozzle vane according to an aspect of the present invention may include a leading edge and a trailing edge, and a protrusion protruding in a direction in which air is introduced may be formed under the leading edge.

The trailing edge according to an aspect of the present invention may be formed to stand upright with respect to the outer circumferential surface of the main cylinder, and the protrusion may protrude obliquely with respect to the outer circumferential surface of the main cylinder.

The cavity according to an aspect of the present invention may include an expansion area in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area connected to the expansion area and having a uniform height.

A guide rib for guiding the movement of fuel flowing into the expanded area may be protruded from the expanded area according to an aspect of the present invention.

A plurality of guide ribs may be formed in the expansion area according to an aspect of the present invention, and a distance between the guide ribs may gradually increase toward the rear.

The guide rib according to an aspect of the present invention may include a first guide rib extending from the expanded area to the main area and a second guide rib located between the first guide rib and extending from the fuel passage to the expanded area. can

A guide block blocking the expansion area may be installed in the expansion area according to an aspect of the present invention, and a plurality of guide passages may be formed in the guide block.

The guide passage according to an aspect of the present invention may be formed to be inclined with respect to the outer surface of the main cylinder.

The guide passage according to an aspect of the present invention may be formed to gradually increase the cross-sectional area from the inlet to the outlet.

A base block attached to the outer circumferential surface of the main cylinder may be installed in the cavity according to an aspect of the present invention, and the base block may be formed to gradually increase in height toward the rear.

The base block according to an aspect of the present invention is formed extending from the expansion area to the main area, and the rear end of the base block may be located further inside the injection hole formed at the innermost side.

A guide rib extending from the fuel passage to the main area may be formed on the outside of the base block according to an aspect of the present invention to guide the movement of fuel.

The outer end of the base block according to an aspect of the present invention may be located more outside than the height center line of the nozzle vane, and the rear end of the base block may be located more forward than the injection hole.

A plurality of flow passages passing through the base block may be formed in the base block according to an aspect of the present invention, and a cross-sectional area of the flow passage may be formed to gradually increase toward the rear.

A combustor according to an aspect of the present invention 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 burned inside, 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 nozzle vane formed between the main cylinder and the nozzle shroud to inject fuel and guide the flow. a cavity connected to the fuel passage is formed in the nozzle vane, and an injection hole for injecting fuel into a space between the main cylinder and the nozzle shroud is formed in the cavity, the cavity and the fuel passage An inclined surface for guiding the flow of fuel may be formed in the connected portion.

The cavity according to an aspect of the present invention may include an expansion area in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area connected to the expansion area and having a uniform height.

A guide rib for guiding the movement of fuel flowing into the expanded area may be protruded from the expanded area according to an aspect of the present invention.

A base block attached to the outer circumferential surface of the main cylinder may be installed in the cavity according to an aspect of the present invention, and the base block may be formed to gradually increase in height toward the rear.

A plurality of flow passages passing through the base block may be formed in the base block according to an aspect of the present invention, and a cross-sectional area of the flow passage may be formed to gradually increase toward the rear.

As described above, in the combustor nozzle and combustor according to an aspect of the present invention, the flow of fuel flowing into the nozzle vane is made into a laminar flow to uniformly inject fuel through the nozzle vane.

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 perspective view illustrating a nozzle according to a first embodiment of the present invention.
4 is a perspective view illustrating a nozzle vane according to a first embodiment of the present invention.
5 is a longitudinal cross-sectional view of the nozzle vane taken along the line V-V in FIG. 4 .
6 is a longitudinal cross-sectional view of a nozzle vane according to a second embodiment of the present invention.
7 is a longitudinal cross-sectional view of a nozzle vane according to a third embodiment of the present invention.
8 is a longitudinal cross-sectional view of a nozzle vane according to a fourth embodiment of the present invention.
9 is a longitudinal cross-sectional view of a nozzle vane according to a fifth embodiment of the present invention.
10 is a longitudinal cross-sectional view of a nozzle vane according to a sixth embodiment of the present invention.
11 is a longitudinal cross-sectional view of a nozzle vane according to a seventh embodiment of the present invention.
12 is a longitudinal cross-sectional view of a nozzle vane according to an eighth embodiment of the present invention.
13 is a longitudinal cross-sectional view of a nozzle vane according to a ninth 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 it 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, but 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 be composed 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 a 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 residual energy into the atmosphere. can That is, the cycle can 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 , the compressor 1100 of the 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, the air 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 one embodiment, at least some of the plurality of compressor vanes 1140 may be mounted to be rotatable within a predetermined range for adjusting the amount of air inflow.

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 , approximately 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 .

On the other hand, the combustor 1200 may mix 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 1230, and fuel injected from the nozzles 1230 is mixed with air in an appropriate ratio to achieve a state suitable for combustion.

The gas turbine 1000 may use a gas fuel, a liquid fuel, or a combination fuel of a combination thereof. 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 regulations. 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 1230 and then enters the combustion chamber 1240 . The initial ignition of the premixed gas is made 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 high-temperature combustion gas flows by connecting between the burner 1220 and the turbine 1300 and is supplied to the nozzle 1230, in this process. The duct assembly 1250 heated by the hot combustion gas is properly cooled.

The duct assembly 1250 may include a liner 1251 , a transition piece 1252 , and a flow sleeve 1253 . The duct assembly 1250 has a double structure in which a 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 1230 is coupled to the nozzle casing 1260 .

3 is a perspective view illustrating a nozzle according to a first embodiment of the present invention.

Referring to FIGS. 2 and 3 , the nozzle casing 1260 is formed of a substantially circular tube, and is installed to surround the plurality of nozzles 1230 . 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 1230 may be installed inside the nozzle casing 1260 , and the nozzles 1230 may 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 1230 . A plurality of nozzles 1230 and a fuel injector for supplying fuel to the nozzles 1230 may be installed in the head plate 1270 . A nozzle flange 1233 supporting the nozzle is fixed to the head plate 1270 , and an air inlet 1234 may be formed in the nozzle flange 1233 .

The nozzle 1230 is installed between the main cylinder 1231 and the nozzle shroud 1232 surrounding the main cylinder 1231, the main cylinder 1231 and the nozzle shroud 1232, and includes a nozzle vane 1400 for injecting fuel. can do.

The main cylinder 1231 and the nozzle shroud 1232 have a coaxial structure, and fuel and air are supplied to the inside of the main cylinder 1231 . A passage through which air moves is formed in the space between the nozzle shroud 1232 and the main cylinder 1231 , and fuel may be injected.

Air is introduced into the gap formed between the nozzle shroud 1232 and the main cylinder 1231 , and an inlet through which air is introduced may be formed at the rear end of the nozzle shroud 1232 . The nozzle vane 1400 induces a swirl in the passage formed between the main cylinder 1231 and the nozzle shroud 1232, and a plurality of injection holes 1460 may be formed in the nozzle vane 1400 to inject fuel. have. Also, a fuel passage 1236 (shown in FIG. 5 ) for supplying fuel to the nozzle vane 1400 may be formed in the main cylinder 1231 .

4 is a perspective view illustrating a nozzle vane according to a first embodiment of the present invention, and FIG. 5 is a longitudinal cross-sectional view of the nozzle vane taken along the line V-V in FIG. 4 .

3 to 5 , the nozzle vane 1400 may have a wing shape and be fixed to the outer circumferential surface of the main cylinder 1231 . However, the present invention is not limited thereto, and the plurality of nozzle vanes 1400 may be fixed to a separate tube, and the tube and the main cylinder 1231 may be combined.

A cavity 1410 into which fuel is introduced is formed inside the nozzle vane 1400 , and injection holes 1460 connected to the cavity 1410 and injecting fuel are formed on both sides of the nozzle vane 1400 . A plurality of injection holes 1460 may be disposed to be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 1400 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may include a protrusion 1420 inclined with respect to the outer circumferential surface of the main cylinder 1231 . .

The protrusion 1420 may have a triangular longitudinal cross-section, protrude in a direction in which air is introduced, and may be formed to gradually decrease in height as it moves away from the leading edge LE. The protrusion 1420 is formed on the inside of the nozzle vane 1400 , and may be formed extending from a portion connected to the main cylinder 1231 to a preset height. The protrusion 1420 may be formed at a lower portion of the nozzle vane 1400 and extend from the lower end of the nozzle vane 1400 to 1/4 to 3/4 of the height of the nozzle vane 1400 . The protrusion 1420 may guide the flow of air flowing adjacent to the main cylinder 1231 as well as forming a space therein.

Meanwhile, an inclined surface 1421 guiding the flow of fuel is formed at a portion where the cavity 1410 and the fuel passage 1236 are connected, and the inclined surface 1421 may be formed inside the protrusion 1420 . Accordingly, the cavity 1410 includes an expansion area 1411 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 1412 connected to the expansion area 1411 and having a uniform height. can do. The extended region 1411 is formed inside the protrusion 1420 , and may be formed by the inclined surface 1421 of the extended region 1411 and the outer peripheral surface of the main cylinder 1231 .

The extended region 1411 is connected to the fuel passage 1236 to deliver fuel flowing in from the fuel passage 1236 to the main region 1412 . When the inclined surface 1421 is formed in the cavity 1410 as described above, the fuel flowing into the cavity 1410 from the fuel passage 1236 gradually spreads in the expansion region 1411, so that the occurrence of swirl can be significantly reduced.

On the other hand, a guide rib 1450 for guiding the movement of the incoming fuel is formed to protrude in the expansion region 1411 , and the guide rib 1450 may protrude in the thickness direction of the nozzle vane 1400 . The guide rib 1450 has a plate shape, and a plurality of guide ribs 1450 may be formed in the expansion area 1411 . The guide rib 1450 is inclined with respect to the outer surface direction of the main cylinder 1231, and the guide rib 1450 located on the outside is relative to the outer surface of the main cylinder 1231 compared to the guide rib 1450 located on the inside. It may have a larger inclination angle. Accordingly, the distance between the guide ribs 1450 may gradually increase toward the rear with respect to the moving direction of the fuel.

When the guide rib 1450 is formed in the expansion region 1411 as in the first embodiment, the flow of fuel is uniformed to minimize the occurrence of swirl and turbulence, and a uniform amount of fuel can be supplied to the injection hole 1460 . .

Hereinafter, a combustor according to a second embodiment of the present invention will be described. 6 is a longitudinal cross-sectional view of a nozzle vane according to a second embodiment of the present invention.

Referring to FIG. 6 , the combustor according to the second embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 1500 , and thus a redundant description of the same configuration will be omitted. .

The nozzle vane 1500 according to the second embodiment has a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 1510 into which fuel is introduced is formed inside the nozzle vane 1500 , and injection holes 1560 connected to the cavity 1510 to inject fuel are formed on both sides of the nozzle vane 1500 . A plurality of injection holes 1560 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 1500 may be formed of an airfoil including a leading edge LE facing a direction in which air is introduced and a trailing edge TE facing a direction in which air is discharged. The leading edge LE may be formed to have a greater thickness than the trailing edge TE.

An inclined surface 1521 for guiding the flow of fuel is formed at a portion where the cavity 1510 and the fuel passage 1236 are connected. The inclined surface 1521 may be formed below the inner wall of the leading edge LE.

The cavity 1510 by the inclined surface 1521 is connected to the expansion area 1511, in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and the expansion area 1511, and is connected to the main area having a uniform height ( 1512) may be included. It may be formed by the inclined surface 1521 of the extension area 1511 and the outer peripheral surface of the main cylinder 1231 .

The extended region 1511 is connected to the fuel passage 1236 to deliver fuel flowing in from the fuel passage 1236 to the main region 1512 . When the inclined surface 1521 is formed in the cavity 1510 as described above, the fuel flowing into the cavity 1510 from the fuel passage 1236 gradually spreads in the expansion region 1511, so that the occurrence of swirl can be significantly reduced.

Meanwhile, a guide rib 1550 for guiding the movement of the incoming fuel is formed in the expanded area 1511 , and the guide rib 1550 is formed extending from the expanded area 1511 to the main area 1512 . The guide rib 1550 may protrude in the thickness direction of the nozzle vane 1500 . The guide rib 1550 has a plate shape, and a plurality of guide ribs 1550 may be formed in the expansion area. The distance between the guide ribs 1550 may gradually increase toward the rear with respect to the moving direction of the fuel.

When the guide ribs 1550 are formed as in the second embodiment and the guide ribs 1550 extend from the extended area 1511 to the main area 1512, fuel can be uniformly supplied to each injection hole 1560. have.

Hereinafter, a combustor according to a third embodiment of the present invention will be described. 7 is a longitudinal cross-sectional view of a nozzle vane according to a third embodiment of the present invention.

Referring to FIG. 7 , the combustor according to the third embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 1600 , and thus a redundant description of the same configuration will be omitted. .

The nozzle vane 1600 is formed in a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 1610 into which fuel is introduced is formed inside the nozzle vane 1600 , and injection holes 1660 connected to the cavity 1610 to inject fuel are formed on both sides of the nozzle vane 1600 . A plurality of injection holes 1660 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 1600 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231, and the leading edge LE may include a protrusion 1620 inclined with respect to the outer circumferential surface of the main cylinder 1231. .

The protrusion 1620 may have a triangular longitudinal cross-section and may be formed to gradually decrease in height as it moves away from the leading edge LE. The protrusion 1620 is formed on the inside of the nozzle vane 1600 , and may be formed extending from a portion connected to the main cylinder 1231 to a preset height. The protrusion 1620 may be formed at a lower portion of the nozzle vane 1600 and may be formed extending from the lower end of the nozzle vane 1600 to 1/4 to 3/4 of the height of the nozzle vane 1600 . The protrusion 1620 may guide the flow of air flowing adjacent to the main cylinder 1231 as well as forming a space therein.

Meanwhile, an inclined surface 1621 guiding the flow of fuel is formed at a portion where the cavity 1610 and the fuel passage 1236 are connected, and the inclined surface 1621 may be formed inside the protrusion 1620 . Accordingly, the cavity 1610 includes an expansion area 1611 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 1612 connected to the expansion area 1611 and having a uniform height. can do. The extended region 1611 is formed inside the protrusion 1620 , and may be formed by the inclined surface 1621 of the extended region 1611 and the outer peripheral surface of the main cylinder 1231 .

The expansion region 1611 is connected to the fuel passage 1236 to deliver fuel flowing in from the fuel passage 1236 to the main region 1612 . When the inclined surface 1621 is formed in the cavity 1610 as described above, the fuel flowing into the cavity 1610 from the fuel passage 1236 gradually spreads in the expansion region 1611, so that the occurrence of swirl can be significantly reduced.

Meanwhile, a guide block 1650 blocking the expansion area 1611 may be installed in the extension area 1611 , and a plurality of guide passages 1651 may be formed in the guide block 1650 . The guide passage 1651 extends from the front end to the rear end of the guide block 1650 and passes through the guide block 1650 . The guide passage 1651 may be formed to be inclined with respect to the outer surface of the main cylinder 1231 , and accordingly, the distance between the guide passage 1651 may increase toward the rear end.

In addition, the guide passage 1651 may be formed to gradually increase in cross-sectional area from the inlet to the outlet. When the cross-sectional area of the guide passage 1651 is formed to gradually increase toward the rear, it is possible to prevent the occurrence of swirl due to a sharp increase in the cross-sectional area. In addition, the guide passage 1651 may provide directionality to fuel and supply it to the main region 1612 .

Meanwhile, the inlet TA1 of the guide passage 1651 located on the outside may be larger than the inlet TA2 of the guide passage 1651 located on the inside. Accordingly, more fuel is supplied to the outside, so that sufficient fuel can be supplied to the injection hole 1660 located outside.

Hereinafter, a combustor according to a fourth embodiment of the present invention will be described. 8 is a longitudinal cross-sectional view of a nozzle vane according to a fourth embodiment of the present invention.

Referring to FIG. 8 , since the combustor according to the fourth embodiment has the same structure as the combustor according to the first embodiment except for the nozzle vane 1700 , a redundant description of the same configuration will be omitted. .

The nozzle vane 1700 is formed in a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 1710 through which fuel is introduced is formed inside the nozzle vane 1700 , and injection holes 1760 connected to the cavity 1710 to inject fuel are formed on both sides of the nozzle vane 1700 . A plurality of injection holes 1760 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 1700 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 1721 for guiding the flow of fuel is formed at a portion where the cavity 1710 and the fuel passage 1236 are connected, and the inclined surface 1721 may be formed inside the leading edge LE. Accordingly, the cavity 1710 includes an expansion area 1711 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 1712 connected to the expansion area 1711 and having a uniform height. can do.

The extended region 1711 is connected to the fuel passage 1236 to deliver fuel flowing in from the fuel passage 1236 to the main region 1712 . When the inclined surface 1721 is formed in the cavity 1710 as described above, the fuel flowing into the cavity 1710 from the fuel passage 1236 gradually spreads in the expansion region 1711, so that the occurrence of swirl can be significantly reduced.

Meanwhile, a guide rib 1750 for guiding the movement of the inflowing fuel is protruded in the expansion region 1711 , and the guide rib 1750 may protrude in the thickness direction of the nozzle vane 1700 . The guide rib 1750 has a plate shape, and a plurality of guide ribs 1750 may be formed in the expansion region 1711 . The guide rib 1750 may be inclined with respect to the outer surface of the main cylinder 1231 .

The guide rib 1750 may be formed to gradually decrease in thickness from the center toward both side ends. The guide rib 1750 may have four inclined surfaces inclined with respect to the longitudinal direction of the guide rib 1750 . In addition, the gap between the guide ribs 1750 may be formed to be wider at the outlet side than at the inlet side. Accordingly, the width of the passage may be expanded in multiple stages on the outside of the guide rib 1750 , and the guide passage 1751 formed between the guide ribs 1750 may have a structure in which the width is gradually narrowed and then widened.

The flow of fuel is accelerated in the section in which the width is narrowed and the speed is slowed in the section in which the width is widened. The flow of fuel is made into laminar flow by the guide rib 1750 so that the flow and flow rate can be uniform.

In addition, according to the fourth embodiment, since the leading edge LE has a structure inclined from the inner end to the outer end, the cavity 1710 of the nozzle vane 1700 is gradually expanded to further reduce swirl.

Hereinafter, a combustor according to a fifth embodiment of the present invention will be described. 9 is a longitudinal cross-sectional view of a nozzle vane according to a fifth embodiment of the present invention.

Referring to FIG. 9 , the combustor according to the fifth embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 1800 , and thus a redundant description of the same configuration will be omitted. .

The nozzle vane 1800 is formed in a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 1810 through which fuel is introduced is formed inside the nozzle vane 1800 , and injection holes 1860 connected to the cavity 1810 to inject fuel are formed on both sides of the nozzle vane 1800 . A plurality of injection holes 1860 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 1800 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 1821 for guiding the flow of fuel is formed at a portion where the cavity 1810 and the fuel passage 1236 are connected, and the inclined surface 1821 may be formed inside the leading edge LE. Accordingly, the cavity 1810 includes an expansion area 1811 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 1812 connected to the expansion area 1811 and having a uniform height. can do.

The extended region 1811 is connected to the fuel passage 1236 to transfer fuel flowing in from the fuel passage 1236 to the main region 1812 . When the inclined surface 1821 is formed in the cavity 1810 as described above, the fuel flowing into the cavity 1810 from the fuel passage 1236 gradually spreads in the expansion region 1811, so that the occurrence of swirl can be significantly reduced.

On the other hand, a plurality of guide ribs 1850 for guiding the movement of the incoming fuel are formed to protrude in the expansion region 1811 , and the guide ribs 1850 may protrude in the thickness direction of the nozzle vane 1800 .

The guide rib is located between the first guide rib 1852 and the first guide ribs 1852 running from the expanded area 1811 to the main area 1812 , and from the fuel passage 1236 to the expanded area 1811 . 2 guide ribs 1851 may be included. The first guide rib 1852 and the second guide rib 1851 may be formed in a straight line or a curved line.

As such, when the nozzle vane 1800 includes the first guide rib 1852 and the second guide rib 1851 , the second guide rib 1851 moves the fuel from the fuel passage 1236 to the expansion region 1811 . In a wide area, the first guide rib 1852 guides the flow of fuel, thereby reducing swirl more efficiently.

Hereinafter, a combustor according to a sixth embodiment of the present invention will be described. 10 is a longitudinal cross-sectional view of a nozzle vane according to a sixth embodiment of the present invention.

Referring to FIG. 10 , since the combustor according to the sixth embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 1900 , a redundant description of the same configuration will be omitted. .

The nozzle vane 1900 has a wing shape and may be fixed to the outer peripheral surface of the main cylinder 1231 . A cavity 1910 into which fuel is introduced is formed inside the nozzle vane 1900 , and injection holes 1960 connected to the cavity 1910 to inject fuel are formed on both sides of the nozzle vane 1900 . A plurality of injection holes 1960 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The spacing HG1 between the injection holes 1960 positioned on the outside may be smaller than the spacing HG2 between the injection holes 1960 positioned on the inside. The nozzle vane 1900 is formed to protrude in the radial direction, and the space between the main cylinder 1231 and the nozzle shroud increases in proportion to the square of the radius toward the outside. Accordingly, when the distance HG1 between the injection holes 1960 located on the outside is smaller than the distance HG2 on the inside, more fuel is injected to the outside to induce uniform premixing.

The nozzle vane 1900 may be formed as an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 1921 guiding the flow of fuel is formed at a portion where the cavity 1910 and the fuel passage 1236 are connected, and the inclined surface 1921 may be formed inside the leading edge LE. Accordingly, the cavity 1910 includes an expansion area 1911 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 1912 connected to the expansion area 1911 and having a uniform height. can do.

The expansion region 1911 is connected to the fuel passage 1236 to deliver fuel flowing in from the fuel passage 1236 to the main region 1912 . When the inclined surface 1921 is formed in the cavity 1910 as described above, the fuel flowing into the cavity 1910 from the fuel passage 1236 gradually spreads in the expansion region 1911, so that the occurrence of swirl can be significantly reduced.

Meanwhile, a guide rib 1950 for guiding the movement of the inflowing fuel is protruded in the expansion region 1911 , and the guide rib 1950 may protrude in the thickness direction of the nozzle vane 1900 .

The guide rib 1950 may be formed extending from the fuel passage 1236 to the main region 1912 through the expansion region 1911 . At this time, the gap FG1 between the guide rib 1950 and the outer surface of the fuel passage 1236 may be formed to be larger than the gap FG2 between the guide rib 1950 and the inner surface of the fuel passage 1236. . Accordingly, more fuel may be supplied to the outside of the nozzle vane 1900 .

Meanwhile, the guide rib 1950 may be formed in a curved line, and may be formed in a gentle S-shape having an inflection point. Here, the inner side of the guide rib 1950 may be formed to be convex downward, and the outer side of the guide rib 1950 may be formed to be convex upward.

A plurality of discharge guide protrusions 1970 spaced apart from each other in the height direction of the nozzle vane 1900 are formed between the injection holes 1960, and the discharge guide protrusion 1970 may have a structure in which the center portion is thicker than both side ends. The discharge guide protrusion 1970 may have a rhombic cross section. When the discharge guide protrusion 1970 is formed as described above, the fuel is pressurized and uniformed by the discharge guide protrusion 1970 , so that the discharge of fuel through the injection hole 1960 can be further stabilized. In addition, an upper end of the guide rib 1950 may be connected to any one of the discharge guide protrusions 1970 .

A base block 1980 attached to the outer circumferential surface of the main cylinder 1231 may be installed in the cavity 1910 , and the base block 1980 may be formed to gradually increase in height toward the rear. The base block 1980 is formed from the extended area 1911 to the main area, and the rear end of the base block 1980 is located more inside than the injection nozzle 1230 disposed at the innermost side, and located further back than the injection nozzle. can do.

In addition, the outer surface of the base block 1980 is made of a flat surface, it may be formed to be inclined with respect to the outer peripheral surface of the main cylinder (1231). In addition, the guide rib 1950 may be located outside the base block 1980 . In addition, the distance between the outer surface of the base block 1980 and the inclined surface 1921 may gradually increase toward the rear. When the base block 1980 is installed in this way, the flow of fuel may be induced to be inclined upward.

Hereinafter, a combustor according to a seventh embodiment of the present invention will be described. 11 is a longitudinal cross-sectional view of a nozzle vane according to a seventh embodiment of the present invention.

Referring to FIG. 11 , the combustor according to the seventh embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 2100 , and thus a redundant description of the same configuration will be omitted. .

The nozzle vane 2100 is formed in a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 2110 into which fuel is introduced is formed inside the nozzle vane 2100 , and injection holes 2160 connected to the cavity 2110 to inject fuel are formed on both sides of the nozzle vane 2100 . A plurality of injection holes 2160 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 2100 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 2121 guiding the flow of fuel is formed at a portion where the cavity 2110 and the fuel passage 1236 are connected, and the inclined surface 2121 may be formed inside the leading edge LE. Accordingly, the cavity 2110 includes an expansion area 2111 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 2112 connected to the expansion area 2111 and having a uniform height. can do.

The expansion region 2111 is connected to the fuel passage 1236 to transfer fuel flowing in from the fuel passage 1236 to the main region 2112 . When the inclined surface 2121 is formed in the cavity 2110 as described above, the fuel flowing into the cavity 2110 from the fuel passage 1236 gradually spreads in the expansion region 2111, so that the occurrence of swirl can be significantly reduced.

A base block 2180 attached to the outer circumferential surface of the main cylinder 1231 may be installed in the cavity 2110, and the base block 2180 may be formed to gradually increase in height toward the rear. The base block 2180 may be formed to extend from the fuel passage 1236 to the main area 2112 through the expansion area 2111 .

The rear end of the base block 2180 may be located more inside than the injection nozzle 1230 disposed at the innermost side. In addition, the outer surface of the base block 2180 may be formed of a curved surface, the outer surface of the base block 2180 may be formed to be convex outwardly. Accordingly, the interval between the inclined surface 2121 and the upper surface of the base block 2180 may be gradually increased. When the base block 2180 is installed in this way, the flow of fuel in the expansion region 2111 and the main region 2112 can be induced to be inclined upward, and the cross-sectional area of the flow path is gradually increased, thereby reducing the occurrence of swirl. can

Hereinafter, a combustor according to an eighth embodiment of the present invention will be described. 12 is a longitudinal cross-sectional view of a nozzle vane according to an eighth embodiment of the present invention.

Referring to FIG. 12 , the combustor according to the eighth embodiment has the same structure as the combustor according to the first embodiment except for the nozzle vane 2200, and thus a redundant description of the same configuration will be omitted. .

The nozzle vane 2200 has a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 2210 into which fuel is introduced is formed inside the nozzle vane 2200, and injection holes 2260 connected to the cavity 2210 to inject fuel are formed on both sides of the nozzle vane 2200. A plurality of injection holes 2260 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 2200 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 2221 guiding the flow of fuel is formed at a portion where the cavity 2210 and the fuel passage 1236 are connected, and the inclined surface 2221 may be formed inside the leading edge LE. Accordingly, the cavity 2210 includes an expansion area 2211 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 2212 connected to the expansion area 2211 and having a uniform height. can do.

The extended region 2211 is connected to the fuel passage 1236 to transfer fuel flowing in from the fuel passage 1236 to the main region 2212 . When the inclined surface 2221 is formed in the cavity 2210 as described above, the fuel flowing into the cavity 2210 from the fuel passage 1236 gradually spreads in the expansion region 2211, so that the occurrence of swirl can be significantly reduced.

A base block attached to the outer circumferential surface of the main cylinder may be installed in the cavity 2210 , and the base block 2280 may be formed to gradually increase in height toward the rear. The base block 2280 may be formed only in the extended area.

The rear end of the base block 2280 is located more radially outward than the injection nozzle 1230 disposed on the innermost side, but may be located more outward than the height centerline of the nozzle vane 2200 . In addition, the rear end of the base block 2280 may be located more forward than the spray nozzles 1230 . Here, the outer surface of the base block 2280 may have a curved surface, and a plurality of flow passages 2281 penetrating the base block 2280 are formed in the base block 2280 , and the flow passages 2281 have a uniform cross-sectional area. can have

Accordingly, some of the fuel may be supplied to the injection hole 2260 through the flow passage 2281 , and the other fuel may ride over the base block 2280 and move to the injection hole 2260 . When the base block 2280 in which the flow passage 2281 is formed as described above is installed in the expansion area, it is possible to more easily move fuel to the injection hole 2260 while preventing swirl.

Hereinafter, a combustor according to a ninth embodiment of the present invention will be described. 13 is a longitudinal cross-sectional view of a nozzle vane according to a ninth embodiment of the present invention.

Referring to FIG. 13 , since the combustor according to the eighth embodiment has the same structure as the combustor according to the first embodiment, except for the nozzle vane 2300 , a redundant description of the same configuration will be omitted. .

The nozzle vane 2300 is formed in a wing shape and may be fixed to the outer circumferential surface of the main cylinder 1231 . A cavity 2310 into which fuel is introduced is formed inside the nozzle vane 2300 , and injection holes 2360 connected to the cavity 2310 to inject fuel are formed on both sides of the nozzle vane 2300 . A plurality of injection holes 2360 may be spaced apart from each other in a direction from the inside to the outside of the nozzle 1230 .

The nozzle vane 2300 may be formed of an airfoil including a leading edge LE facing in a direction in which air is introduced and a trailing edge TE facing in a direction in which air is discharged. The trailing edge TE may be formed to stand perpendicular to the outer circumferential surface of the main cylinder 1231 , and the leading edge LE may be formed to be inclined with respect to the outer circumferential surface of the main cylinder 1231 .

The leading edge LE may be inclined from an inner end in contact with the main cylinder 1231 to an outer end. Meanwhile, an inclined surface 2321 guiding the flow of fuel is formed at a portion where the cavity 2310 and the fuel passage 1236 are connected, and the inclined surface 2321 may be formed inside the leading edge LE. Accordingly, the cavity 2310 includes an expansion area 2311 in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area 2312 connected to the expansion area 2311 and having a uniform height. can do.

The extended region 2311 is connected to the fuel passage 1236 to transfer fuel flowing in from the fuel passage 1236 to the main region 2312 . When the inclined surface 2321 is formed in the cavity 2310 as described above, the fuel flowing into the cavity 2310 from the fuel passage 1236 gradually spreads in the expansion region 2311, so that the occurrence of swirl can be significantly reduced.

A base block 2380 attached to the outer circumferential surface of the main cylinder 1231 may be installed in the cavity 2310 , and the base block 2380 may be formed to gradually increase in height toward the rear. The base block 2380 may be formed only in the extended area.

The rear end of the base block 2380 is located more radially outward than the injection nozzle 1230 disposed on the innermost side, but may be located more outward than the height center line of the nozzle vane 2300 . In addition, the rear end of the base block 2380 may be located more forward than the spray nozzles 1230 . Here, the outer surface of the base block 2380 may have a curved surface, and a plurality of flow passages 2381 penetrating the base block 2380 are formed in the base block 2380 , and the cross-sectional area of the flow passage 2381 is rearward. It can be formed to gradually increase as it goes. When the cross-sectional area of the flow passage 2381 is gradually increased toward the rear, the pressure and speed of the fuel decrease while passing through the flow passage 2381 , thereby reducing the occurrence of swirl.

Part of the fuel may be supplied to the injection hole 2360 through the flow passage 2381 , and other fuel may move to the injection hole 2360 along the outer surface of the base block 2380 . When the base block 2380 in which the flow passage 2381 is formed is installed in the expansion area as described above, it is possible to more easily move fuel to the injection hole 2360 while preventing swirl.

In the above, although an embodiment of the present invention has been described, 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: vane
1150: housing 1200: combustor
1210: combustor casing 1220: burner
1230: nozzle 1231: main cylinder
1232: nozzle shroud 1233: nozzle flange
1240: combustion chamber 1250: duct assembly
1251: liner 1252: transition piece
1253 flow sleeve 1257 cooling passage
1260: nozzle casing 1270: head plate
1400, 1500, 1600, 1700, 1800, 1900, 2100, 2200, 2300: Nozzle vanes
1410, 1510, 1610, 1710, 1810, 1910, 2110, 2210, 2310: cavity
1411, 1511, 1611, 1711, 1811, 1911, 2111, 2211, 2311: extended area
1412, 1512, 1612, 1712, 1812, 1912, 2112, 2212, 2312: main area
1420, 1620: protrusion
1421, 1500, 1600, 1700, 1800, 1900, 2100, 2200, 2300: slope
1450, 1500, 1600, 1700, 1800, 1900: guide ribs
1650: guide block 1651: guide passage
1852: first guide rib 1851: second guide rib
1970: Exhaust guide projection
1980, 2180, 2280, 2380: base block 2281, 2381: flow passage

Claims (20)

In the combustor nozzle,
a main cylinder having a fuel passage through which fuel moves;
a nozzle shroud surrounding the main cylinder;
a nozzle vane formed between the main cylinder and the nozzle shroud to inject fuel and guide the flow;
including,
A cavity connected to the fuel passage is formed inside the nozzle vane, and an injection hole for injecting fuel into a space between the main cylinder and the nozzle shroud is formed in the cavity,
A nozzle for a combustor, characterized in that a slope for guiding the flow of fuel is formed at a portion where the cavity and the fuel passage are connected. The method of claim 1,
The nozzle vane includes a leading edge and a trailing edge, and a protrusion protruding in a direction in which air is introduced is formed at a lower portion of the leading edge. 3. The method of claim 2,
The trailing edge is formed to stand upright with respect to the outer circumferential surface of the main cylinder, and the protrusion is formed to protrude obliquely with respect to the outer circumferential surface of the main cylinder. The method of claim 1,
The nozzle for a combustor, characterized in that the cavity includes an extended area in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area connected to the expanded area and having a uniform height. 5. The method of claim 4,
The nozzle for a combustor, characterized in that the guide rib for guiding the movement of the fuel flowing into the expansion area is formed to protrude from the expansion area. 6. The method of claim 5,
A plurality of guide ribs are formed in the expanded area, and a distance between the guide ribs is gradually increased toward the rear. 6. The method of claim 5,
wherein the guide rib includes a first guide rib extending from the expanded area to the main area and a second guide rib located between the first guide rib and extending from the fuel passage to the expanded area. . 5. The method of claim 4,
A guide block blocking the expansion area is installed in the expansion area,
A nozzle for a combustor, characterized in that a plurality of guide passages are formed in the guide block. 9. The method of claim 8,
The guide passage is a combustor nozzle, characterized in that formed inclined with respect to the outer surface of the main cylinder. 9. The method of claim 8,
The guide passage is a combustor nozzle, characterized in that the cross-sectional area is gradually increased from the inlet to the outlet. 5. The method of claim 4,
A base block attached to the outer circumferential surface of the main cylinder is installed in the cavity, and the base block is formed to gradually increase in height toward the rear. 12. The method of claim 11,
The base block is formed extending from the extended area to the main area, and the rear end of the base block is located further inside the injection hole formed at the innermost side. 13. The method of claim 12,
The nozzle for a combustor, characterized in that the guide rib is formed on the outside of the base block from the fuel passage to the main area to guide the movement of the fuel. 12. The method of claim 11,
The outer end of the base block is located more outside than the height center line of the nozzle vane, and the rear end of the base block is located more forward than the injection hole. 15. The method of claim 14,
A plurality of flow passages passing through the base block are formed in the base block, and a cross-sectional area of the flow passages is formed to gradually increase toward the rear. A burner having a plurality of nozzles for injecting fuel and air, the combustor comprising a duct assembly coupled to one side of the burner, the fuel and the air are burned inside, and a duct assembly for delivering the burned gas to a turbine,
The nozzle is
a main cylinder having a fuel passage through which fuel moves;
a nozzle shroud surrounding the main cylinder;
a nozzle vane formed between the main cylinder and the nozzle shroud to inject fuel and guide the flow;
including,
A cavity connected to the fuel passage is formed inside the nozzle vane, and an injection hole for injecting fuel into a space between the main cylinder and the nozzle shroud is formed in the cavity,
A combustor, characterized in that at a portion where the cavity and the fuel passage are connected, an inclined surface for guiding the flow of fuel is formed. 17. The method of claim 16,
wherein the cavity includes an extended area in which the height of the flow path gradually increases toward the rear with respect to the air flow direction, and a main area connected to the expanded area and having a uniform height. 18. The method of claim 17,
The combustor, characterized in that the guide rib for guiding the movement of the fuel flowing into the expansion area is formed to protrude from the expansion area. 18. The method of claim 17,
A base block attached to the outer circumferential surface of the main cylinder is installed in the cavity, and the base block is formed to gradually increase in height toward the rear. 20. The method of claim 19,
A plurality of flow passages passing through the base block are formed in the base block, and a cross-sectional area of the flow passages is formed to gradually increase toward the rear.

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