KR102460000B1 - Nozzle for combustor, combustor, and gas turbine including the same - Google Patents

Abstract

A nozzle for a combustor for burning fuel containing hydrogen according to an aspect of the present invention is formed between a plurality of injection tubes through which air and fuel move, and the injection tube, and includes a fuel passage through which fuel moves; and a mixing plate spaced apart from the front end of the multi-tube and having a plurality of mixing holes to mix fuel and air injected from the multi-tube.

Description

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

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

A gas turbine is a power engine that mixes 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 nozzles installed in each combustor, and the nozzles can inject gaseous fuel and liquid fuel. In recent years, in order to suppress the emission of carbon dioxide, the use of hydrogen fuel or a fuel containing hydrogen is recommended.

However, since hydrogen has a high combustion rate, when its fuel is burned with a gas turbine combustor, the flame formed in the gas turbine combustor approaches and heats the structure of the gas turbine combustor, and the reliability of the gas turbine combustor is reduced. is likely to cause

In order to solve this problem, a combustor nozzle having a multi-tube has been proposed in Korean Patent Laid-Open No. 10-2020-0027894, etc., but the nozzle having a multi-tube does not have a swirler, so it is difficult to uniformly mix fuel and air. there is a problem.

Based on the technical background as described above, an object of the present invention is to provide a combustor nozzle, combustor, and gas turbine capable of uniformly mixing fuel and air.

A nozzle for a combustor for burning fuel containing hydrogen according to an aspect of the present invention is formed between a plurality of injection tubes through which air and fuel move, and the injection tube, and includes a fuel passage through which fuel moves; and a mixing plate spaced apart from the front end of the multi-tube and having a plurality of mixing holes to mix fuel and air injected from the multi-tube.

The mixing hole according to an aspect of the present invention may be arranged to face the injection hole formed in the injection tube at a distance, and the blocked part of the mixing plate may be arranged to face the blocking plate installed at the front end of the multi-tube.

The mixing hole according to an aspect of the present invention may be formed such that the inner diameter gradually decreases toward the front.

The mixing hole according to an aspect of the present invention may include a constricted portion whose inner diameter is gradually reduced toward the front and a front end of the constricted portion and a progressively expanded portion with an inner diameter toward the front.

The mixing hole according to an aspect of the present invention may be disposed to face a blocking plate installed at the front end of the multi-tube.

The mixing hole according to an aspect of the present invention is formed such that the inner diameter gradually decreases toward the tip, and a fallopian tube extending outward toward the front may be installed at the tip of the injection tube.

The mixing hole according to an aspect of the present invention may include a constricted portion whose inner diameter is gradually reduced toward the front end, and a cylindrical portion connected to the front end of the constricted portion and maintaining a uniform inner diameter.

The mixing hole according to an aspect of the present invention includes a first mixing hole facing at a distance from the injection hole formed in the injection tube and a second mixing hole facing the blocking plate installed at the front end of the multi-tube, An inner diameter of the first mixing hole may be smaller than an inner diameter of the second mixing hole.

A plurality of fuel inlet holes connected to the fuel passage and through which fuel flows into the injection tube are formed in the injection tube according to an aspect of the present invention, and a plurality of distribution holes through which air passes are formed in the rear of the fuel inlet hole. A dispersion plate may be installed.

The dispersion plate according to an aspect of the present invention may be formed to be curved in an arc shape toward the front, and may be installed to be inclined toward the front so as to partially cover the fuel inlet hole from the rear of the fuel inlet hole.

The dispersion plate according to an aspect of the present invention may be formed to gradually decrease in width from the center to both side ends.

A plurality of vortex forming protrusions protruding toward the center of the injection tube may be formed on the inner end of the dispersion plate according to an aspect of the present invention.

The plurality of dispersion holes according to an aspect of the present invention may be formed to extend in a radial direction of the injection tube.

The plurality of dispersion holes according to an aspect of the present invention may be formed to extend in a circumferential direction of the injection tube.

A plurality of fuel inlet holes connected to the fuel passage and through which fuel flows into the injection tube are formed in the injection tube according to an aspect of the present invention, and a fuel guide plate having a plurality of guide holes formed in front of the fuel inlet hole is installed can be

A combustor according to another 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 the combusted gas is delivered to the turbine. wherein the nozzle is formed between a plurality of injection tubes through which air and fuel move and the injection tube and includes a fuel passage through which fuel moves, and is spaced apart from the front of the multi-tube, and a plurality of It may include a mixing plate having a mixing hole to mix the fuel and air injected from the multi-tube.

The mixing hole according to another aspect of the present invention may be arranged to face the injection hole formed in the injection tube at a distance from each other, and the blocked part of the mixing plate may be arranged to face the blocking plate installed at the front end of the multi-tube.

In the injection tube according to another aspect of the present invention, a plurality of fuel inlet holes connected to the fuel passage and through which fuel flows into the injection tube are formed, and a plurality of distribution holes through which air passes are formed in the rear of the fuel inlet hole. A dispersion plate may be installed.

In the injection tube according to another aspect of the present invention, a plurality of fuel inlet holes connected to the fuel passage and through which fuel flows into the injection tube are formed, and a fuel guide plate having a plurality of guide holes formed in front of the fuel inlet hole is installed. can be

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 duct assembly including a turbine blade, wherein the combustor is coupled to a burner having a plurality of nozzles for injecting fuel and air, and one side of the burner, the fuel and the air are burned inside, and the combusted gas is delivered to the turbine Including, wherein the nozzles are formed between a plurality of injection tubes through which air and fuel move and the injection tubes and including a fuel passage through which fuel moves, and are spaced apart from each other in front of the multi-tube, and a plurality of It may include a mixing plate having a mixing hole for mixing the fuel and air injected from the multi-tube.

As described above, according to the combustor nozzle, the combustor, and the gas turbine according to an aspect of the present invention, the mixing plate is installed in front of the multi-tube so that fuel and air can be uniformly mixed.

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 front view of a burner according to a first embodiment of the present invention.
4 is a cross-sectional view taken along the longitudinal direction of the nozzle according to the first embodiment of the present invention.
FIG. 5 is a cross-sectional view taken along line V-V in FIG. 4 .
6 is a cross-sectional view illustrating a part of a nozzle according to a second embodiment of the present invention.
7 is a cross-sectional view illustrating a part of a nozzle according to a third embodiment of the present invention.
8 is a cross-sectional view showing a part of a nozzle according to a fourth embodiment of the present invention.
9 is a cross-sectional view showing a part of a nozzle according to a fifth embodiment of the present invention.
10 is a cross-sectional view showing a part of a nozzle according to a sixth embodiment of the present invention.
11 is a cross-sectional view illustrating a part of a nozzle according to a seventh embodiment of the present invention.
12 is a partial cross-sectional view of the injection tube according to the eighth embodiment of the present invention taken in the longitudinal direction.
13 is a partial cross-sectional view of a spray tube according to an eighth embodiment of the present invention, taken in a radial direction.
14 is a partial cross-sectional view of an injection tube according to a modification of the eighth embodiment of the present invention, as viewed in a radial direction.
15 is a partial cross-sectional view of an injection tube according to another modified example of the eighth embodiment of the present invention, cut in a radial direction.
16 is a partial cross-sectional view of a spray tube according to a ninth embodiment of the present invention taken in a radial direction.
17 is a partial cross-sectional view of the injection tube according to the tenth embodiment of the present invention taken in the longitudinal direction.

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 'comprise' or 'have' 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 is to be understood that this does not preclude the possibility of the presence 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. At this time, 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. In other words, it sucks air from the atmosphere, compresses it to a high pressure, burns fuel in a static pressure environment to release heat energy, expands this high-temperature combustion gas to convert it into kinetic energy, and then releases 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 for 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. It is common to use a multi-stage axial flow compressor because it has to compress the At this time, in the multi-stage axial flow compressor, the compressor 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. The air is compressed to a higher pressure while passing through the compressor blades 1130 formed in multiple stages.

The compressor vane 1140 is mounted inside the housing 1150 , and a plurality of compressor vanes 1140 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 compressor 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 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 , 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 .

The turbine 1300 includes a rotor disk 1310 and a plurality of turbine blades and turbine vanes 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 a turbine blade and a turbine vane are inserted into the groove. The turbine vanes are fixed against rotation and direct the flow of combustion gases through the turbine blades. Turbine blades are rotated by combustion gas to generate rotational force.

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 , a nozzle 1400 , and a duct assembly 1250 .

The combustor casing 1210 surrounds the plurality of burners 1220 and may have a substantially circular 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.

A gas fuel may be used for the gas turbine 1000 , and in particular, a fuel including hydrogen may be used. The fuel may consist of hydrogen fuel alone or a fuel comprising hydrogen and natural gas.

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

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

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.

3 is a front view of a burner according to a first embodiment of the present invention, FIG. 4 is a longitudinal cross-sectional view of a nozzle according to the first embodiment of the present invention, and FIG. 5 is V- in FIG. It is a cross-sectional view taken along Ⅴ.

3 to 5, the nozzle 1400 is a multi tube 1410 including a plurality of injection tubes 1420 through which air and fuel move and a fuel passage 1431 through which fuel moves, and a multi A mixing plate 1450 installed in front of the tube 1410 to mix fuel and air may be included.

In addition, the nozzle 1400 may further include a fuel supply pipe 1430 for supplying fuel to the multi-tube 1410 . Here, the fuel may be a gas including hydrogen.

The multi-tube 1410 may include a plurality of injection tubes 1420 to form several small flames using hydrogen gas. The plurality of injection tubes 1420 are spaced apart from each other within the multi-tube 1410 and may be formed parallel to each other. The multi-tube 1410 may finely spray hydrogen and air.

A blocking plate 1415 is installed at the tip of the multi-tube 1410 to form a fuel passage through which fuel moves. The blocking plate 1415 blocks the space between the injection tubes 1420 to prevent fuel from leaking.

The fuel introduced into the multi-tube 1410 through the fuel supply pipe 1430 moves along the fuel passage 1431 , and the injection tube 1420 is installed to pass through the fuel passage 1431 , so that the fuel passage 1431 is It surrounds the spray tube 1420 .

A plurality of fuel inlet holes 1421 through which fuel is introduced may be formed in the injection tube 1420 , and the fuel inlet holes 1421 may be spaced apart from each other in a circumferential direction of the injection tube 1420 . The plurality of fuel inlet holes 1421 may be spaced apart from each other in the longitudinal direction of the injection tube 1420 . In addition, an injection hole 1425 through which air mixed with fuel is injected may be formed in the injection tube 1420 .

The mixing plate 1450 is spaced apart from the front end of the multi-tube 1410 and has a plurality of mixing holes 1451 to mix air and fuel injected from the multi-tube 1410 . The mixing plate 1450 is spaced apart from the multi-tube 1410 to form a mixing space MS in which air and fuel are mixed between the mixing plate 1450 and the multi-tube 1410 . Air and fuel injected from the injection tube 1420 may be mixed in the mixing space MS while forming a partial turbulence and discharged through the mixing plate 1450 .

The mixing hole 1451 is formed at a position corresponding to the position where the injection hole 1425 is formed and faces the injection hole 1425 , and the blocked part of the mixing plate 1450 is a blocking plate 1415 installed at the tip of the multi-tube 1410 . ) is placed to face the

Accordingly, according to the first embodiment, the fuel introduced through the fuel supply pipe 1430 moves to the fuel passage 1431 , then flows into the injection tube 1420 through the fuel inlet hole 1421 and enters the mixing space together with air. is sprayed After the air and fuel injected into the mixing space MS are mixed, they may be injected through the mixing hole 1451 and combusted. Accordingly, air and fuel are more uniformly mixed to form a stable flame.

Hereinafter, a mixing plate according to a second embodiment of the present invention will be described. 6 is a cross-sectional view illustrating a part of a nozzle according to a second embodiment of the present invention.

Referring to FIG. 6 , the nozzle 1402 according to the second embodiment is a multi-tube 1410 including a plurality of injection tubes 1420 through which air and fuel move and a fuel passage 1431 through which fuel moves. ), and may include a mixing plate 1460 installed in front of the multi-tube 1410 to mix fuel and air.

The mixing plate 1460 is spaced apart from the front end of the multi-tube 1410 and has a plurality of mixing holes 1461 to mix air and fuel injected from the multi-tube 1410 . Air and fuel injected from the injection tube 1420 may be mixed while forming a partial turbulence and discharged through the mixing plate 1460 .

The mixing hole 1461 is formed at a position corresponding to the position where the injection hole 1425 is formed and faces the injection hole 1425 , and the blocked part in the mixing plate 1460 is a blocking plate 1415 installed at the tip of the multi-tube 1410 . ) is placed to face the

The mixing hole 1461 is formed to have an inner diameter gradually decreasing toward the front, and may have a substantially truncated cone shape. Accordingly, the injection speed of the air and fuel passing through the mixing hole 1461 is increased. Accordingly, it is possible to prevent backfire of the flame by the fuel injected at a high speed.

Hereinafter, a mixing plate according to a third embodiment of the present invention will be described. 7 is a cross-sectional view illustrating a part of a nozzle according to a third embodiment of the present invention.

Referring to FIG. 7 , the nozzle 1403 according to the third embodiment is a multi-tube 1410 including a plurality of injection tubes 1420 through which air and fuel move and a fuel passage 1431 through which fuel moves. ), and may include a mixing plate 1470 installed in front of the multi-tube 1410 to mix fuel and air.

The mixing plate 1470 is spaced apart from the front end of the multi-tube 1410 and has a plurality of mixing holes 1471 to mix air and fuel injected from the multi-tube 1410 . Air and fuel injected from the injection tube 1420 may be mixed while forming a partial turbulence and discharged through the mixing plate 1470 .

The mixing hole 1471 is formed at a position corresponding to the position where the injection hole 1425 is formed and faces the injection hole 1425 , and the blocked part of the mixing plate 1470 is a blocking plate 1415 installed at the tip of the multi-tube 1410 . ) is placed to face the

The mixing hole 1471 may include a constricted portion 1472 whose inner diameter is gradually reduced toward the front, and a tip of the constricted portion 1472 , and an expanded portion 1473 whose inner diameter is gradually reduced toward the front. Accordingly, the air and fuel passing through the mixing hole 1471 may have an increased injection speed while passing through the constriction unit 1472 , and may flow uniformly while passing through the expansion unit 1473 .

Hereinafter, a mixing plate according to a fourth embodiment of the present invention will be described. 8 is a cross-sectional view showing a part of a nozzle according to a fourth embodiment of the present invention.

Referring to FIG. 8 , the nozzle 1404 according to the fourth embodiment is a multi-tube 1410 including a plurality of injection tubes 1420 through which air and fuel move and a fuel passage 1431 through which fuel moves. ), and may include a mixing plate 1470 installed in front of the multi-tube 1410 to mix fuel and air.

The mixing plate 1480 is spaced apart from the front end of the multi-tube 1410 and includes a plurality of mixing holes 1481 to mix air and fuel injected from the multi-tube 1410 . Air and fuel injected from the injection tube 1420 may be mixed while forming a partial turbulence and discharged through the mixing plate 1480 .

The mixing hole 1481 is formed at a position corresponding to the blocking plate 1415 installed at the tip of the multi-tube 1410 to face the blocking plate 1415 . Also, the clogged portion of the mixing plate 1480 may face the injection hole 1425 .

Accordingly, the air and fuel injected from the injection hole 1425 may not move forward, but may be mixed while dispersed and moved in the lateral direction and may be injected through the mixing hole 1481 .

Hereinafter, a mixing plate according to a fifth embodiment of the present invention will be described. 9 is a cross-sectional view showing a part of a nozzle according to a fifth embodiment of the present invention.

Referring to FIG. 9 , the nozzle 1405 according to the fifth embodiment is a multi-tube 1410 including a plurality of injection tubes 1420 through which air and fuel move and a fuel passage 1431 through which fuel moves. ), and may include a mixing plate 1490 installed in front of the multi-tube 1410 to mix fuel and air.

The mixing plate 1490 is spaced apart from the front end of the multi-tube 1410 and has a plurality of mixing holes 1491 to mix air and fuel injected from the multi-tube 1410 . Air and fuel injected from the injection tube 1420 may be mixed while forming a partial turbulence and discharged through the mixing plate 1490 .

The mixing hole 1491 is formed at a position corresponding to the blocking plate 1415 installed at the tip of the multi-tube 1410 to face the blocking plate 1415 . In addition, the clogged portion of the mixing plate 1490 may face the injection hole 1425 .

The mixing hole 1491 may include a constricted portion 1492 whose inner diameter is gradually reduced toward the distal end, and a cylindrical portion 1493 connected to the distal end of the constricted portion 1492 and having a uniform inner diameter. Accordingly, the fuel and air may have an increased injection speed while passing through the constriction portion 1492 , and may flow uniformly while passing through the cylindrical portion 1493 .

Hereinafter, a mixing plate according to a sixth embodiment of the present invention will be described. 10 is a cross-sectional view showing a part of a nozzle according to a sixth embodiment of the present invention.

Referring to FIG. 10 , the nozzle 2401 according to the sixth embodiment is a multi-tube 2410 including a plurality of injection tubes 2420 through which air and fuel move and a fuel passage 2431 through which fuel moves. ), and may include a mixing plate 2430 installed in front of the multi-tube 2410 to mix fuel and air.

The mixing plate 2430 is spaced apart from the front end of the multi-tube 2410 and has a plurality of mixing holes 2431 to mix air and fuel injected from the multi-tube 2410 . Air and fuel injected from the injection tube 2420 may be mixed while forming a partial turbulence and discharged through the mixing plate 2430 .

The mixing hole 2431 is located between the injection holes 2425 formed in the injection tube 2420 , and a portion corresponding to the injection hole 2425 in the mixing plate 2430 is blocked. In front of the injection tube 2420, a fallopian tube 2426 having an inner diameter gradually increasing toward the tip is installed. Accordingly, the fuel injected from the injection tube 2420 may more easily move sideways. The mixing hole 2431 is formed to gradually decrease in cross-sectional area toward the tip. Accordingly, the fuel injected from the injection hole 2425 is divided and introduced into the mixing hole 2431 , and the mixing hole 2431 increases the injection speed of the fuel to prevent backfire.

Hereinafter, a mixing plate according to a seventh embodiment of the present invention will be described. 11 is a cross-sectional view illustrating a part of a nozzle according to a seventh embodiment of the present invention.

Referring to FIG. 11 , the nozzle 2402 according to the seventh embodiment is a multi-tube 2410 including a plurality of injection tubes 2420 through which air and fuel move and a fuel passage 2431 through which fuel moves. ), and may include a mixing plate 2440 installed in front of the multi-tube 2410 to mix fuel and air.

The mixing plate 2440 is spaced apart from the front end of the multi-tube 2410 and has a plurality of mixing holes 2441 to mix air and fuel injected from the multi-tube 2410 . Air and fuel injected from the injection tube 2420 may be mixed while forming a partial turbulence and discharged through the mixing plate 2440 .

In front of the injection tube 2420, a fallopian tube 2426 having an inner diameter gradually increasing toward the tip is installed. Accordingly, the fuel injected from the injection tube 2420 may move laterally more easily while spreading in the fallopian tube.

The mixing hole 2441 is a first mixing hole 2442 facing the injection hole 2425 formed in the injection tube 2420 at a distance from each other and a blocking plate 2415 installed at the front end of the multi-tube 2410 and a second facing each other. A mixing hole 2443 may be included. A second mixing hole 2443 is disposed between the first mixing holes 2442 , and the first inner diameter D11 of the first mixing hole 2442 is the second inner diameter D12 of the second mixing hole 2443 . It can be formed smaller.

Accordingly, a portion of the fuel injected from the injection hole 2425 may be discharged through the first mixing hole 2442 , and the remaining fuel may be discharged through the second mixing hole 2443 . In addition, since the second inner diameter D12 is larger, more fuel is injected through the second mixing hole 2443 located between the injection holes 2425 , and the fuel can be uniformly mixed in this process. In addition, the number of mixing holes 2441 may be made twice as large as the number of injection holes 2425 . Accordingly, fuel may be more finely injected to form a stable flame.

Hereinafter, a nozzle according to an eighth embodiment of the present invention will be described.

12 is a partial cross-sectional view of the injection tube according to the eighth embodiment of the present invention, taken in the longitudinal direction, and FIG.

12 and 13 , a plurality of fuel inlet holes 3421 connected to the fuel passage and through which fuel flows into the injection tube 3420 are formed in the injection tube 3420 , and the fuel inlet hole 3421 is formed. A dispersion plate 3430 having a plurality of dispersion holes 3431 through which air passes is installed at the rear of the . Here, the term “rear” refers to the rear side with respect to the moving direction of the fuel.

The dispersion plate 3430 may include a first side surface 3435 attached to the inner wall of the injection tube 3420 and a second side surface 3436 connected to the first side surface 3435 and protruding in an arc shape. Accordingly, the dispersion plate 3430 is formed to gradually decrease in width from the center toward both side ends.

In addition, the distribution plate 3430 is curved in an arc shape, and is installed to be inclined toward the front so as to partially cover the fuel inlet hole 3421 at the rear of the fuel inlet hole 3421 . The distribution hole 3431 may have a circular shape, and a plurality of distribution holes 3431 may be evenly disposed on the distribution plate 3430 .

However, the present invention is not limited thereto, and as shown in FIG. 14 , the dispersion holes 3441 formed in the dispersion plate 3440 are formed extending in the radial direction of the spray tube 3420 , or as shown in FIG. 15 . Similarly, the dispersion holes 3451 formed in the dispersion plate 3450 may be formed extending in a circumferential direction of the injection tube 3420 .

When the dispersion plate 3430 is installed at the rear of the fuel inlet hole 3421 as in the eighth embodiment, the air passing through the dispersion plate 3430 forms a turbulent flow, so that fuel and air can be more uniformly mixed.

Hereinafter, a nozzle according to a ninth embodiment of the present invention will be described. 16 is a partial cross-sectional view of a spray tube according to a ninth embodiment of the present invention taken in a radial direction.

Referring to FIG. 16 , a plurality of fuel inlet holes are formed in the injection tube 3420 , which are connected to the fuel passage and through which fuel flows into the injection tube 3420 , and a plurality of dispersions through which air passes through the rear of the fuel inlet hole. A dispersion plate 3460 having holes 3461 formed therein is installed.

The dispersion plate 3460 is connected to the first side surface 3465 and the first side 3465 attached to the inner wall of the injection tube 3420, and the second side 3466 protrudes toward the center of the injection tube 3420. may include The dispersion hole 3461 may be formed to extend in a circumferential direction of the injection tube 3420 .

A vortex forming protrusion 3462 protruding toward the center of the injection tube 3420 may be formed on the inner end of the dispersion plate 3460 , that is, the second side surface 3466 . The second side surface 3466 may be formed in a wave pattern shape by the vortex forming protrusion 3462 . Accordingly, a vortex is induced by the vortex-forming protrusion 3462 so that air and fuel can be more uniformly mixed.

Hereinafter, a nozzle according to a tenth embodiment of the present invention will be described.

17 is a partial cross-sectional view of the injection tube according to the tenth embodiment of the present invention taken in the longitudinal direction.

A plurality of fuel inlet holes 3421 connected to the fuel passage and through which fuel flows into the injection tube 3420 are formed in the injection tube 3420 , and a plurality of induction holes 3471 are formed in front of the fuel inlet hole 3421 . The formed fuel guide plate 3470 is installed. Here, "front" means the front in the direction of fuel movement.

The fuel guide plate 3470 is curved in an arc shape and is installed to be inclined toward the front. The guide hole 3471 may have a circular shape, and a plurality of guide holes 3471 may be evenly disposed on the fuel guide plate 3470 .

As described above, according to the present embodiment, the fuel guide plate 3470 is installed so that not only fuel can be dispersed, but also fuel can be prevented from being concentrated in a portion adjacent to the wall surface of the injection tube 3420 . When fuel is introduced from the fuel inlet hole 3421 , it may not be uniformly spread into the injection tube 3420 , and a large amount of fuel may move along the wall surface of the injection tube 3420 . However, according to the tenth embodiment, fuel may be uniformly distributed by the fuel guide plate 3470 .

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 such as, and it will be said that it is also 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
1240: combustion chamber
1400, 1402, 1403, 1404, 1405, 2401, 2402: Nozzle
1410: multi tube 1415, 2415: blocking plate
1420, 2420, 3420: injection tube 1421, 3421: fuel inlet hole
1425, 2425: nozzle 1430: fuel supply pipe
1450, 1460, 1470, 1480, 1490, 2430, 2440: mixing plate
1451, 1461, 1471, 1481, 1491, 2431, 2441: mixing hall
1472, 1492: constricted portion 1473: expanded portion
1493: cylindrical part 2426: fallopian tube
2442: first mixing hole 2443: second mixing hole
3430, 3440, 3450, 3460: dispersion plate 3431, 3441, 3451, 3461: dispersion hole
3470: fuel guide plate 3471: guide hole

Claims (20)

In the combustor nozzle for burning fuel containing hydrogen,
a plurality of injection tubes through which air and fuel move and a multi-tube formed between the injection tubes and including a fuel passage through which fuel moves; and
a mixing plate spaced apart from the front end of the multi-tube and having a plurality of mixing holes to mix fuel and air injected from the multi-tube;
A nozzle for a combustor comprising a. The method of claim 1,
The mixing hole is disposed to face the injection hole formed in the injection tube at a distance, and the blocked part of the mixing plate is disposed to face the blocking plate installed at the tip of the multi-tube. 3. The method of claim 2,
The mixing hole is a nozzle for a combustor, characterized in that the inner diameter is formed to gradually decrease toward the front. 3. The method of claim 2,
The mixing hole is a nozzle for a combustor, characterized in that it includes a constricted portion whose inner diameter is gradually reduced toward the front, and a portion connected to the tip of the constricted portion and whose inner diameter is gradually expanded toward the front. The method of claim 1,
The mixing hole is a combustor nozzle, characterized in that it is disposed to face the blocking plate installed at the tip of the multi-tube. 6. The method of claim 5,
The mixing hole is formed such that the inner diameter gradually decreases toward the tip,
A nozzle for a combustor, characterized in that a fallopian tube extending outward toward the front is installed at the tip of the injection tube. 6. The method of claim 5,
The mixing hole is a nozzle for a combustor, characterized in that it comprises a constricted portion whose inner diameter is gradually reduced toward the front end, and a cylindrical portion connected to the front end of the constricted portion, the inner diameter of which is maintained uniformly. The method of claim 1,
The mixing hole includes a first mixing hole facing the injection hole formed in the injection tube at a distance from each other and a second mixing hole facing the blocking plate installed at the tip of the multi-tube, and the inner diameter of the first mixing hole is the first mixing hole. 2 A nozzle for a combustor, characterized in that it is formed smaller than the inner diameter of the mixing hole. The method of claim 1,
A plurality of fuel inlet holes connected to the fuel passage and through which fuel is introduced into the injection tube are formed in the injection tube,
A nozzle for a combustor, characterized in that a dispersion plate having a plurality of dispersion holes through which air passes is installed at the rear of the fuel inlet hole. 10. The method of claim 9,
wherein the dispersion plate is curved in an arc shape toward the front, and is installed to be inclined toward the front so as to partially cover the fuel inlet hole from the rear of the fuel inlet hole. 10. The method of claim 9,
The dispersion plate is a nozzle for a combustor, characterized in that it is formed to gradually decrease in width from the center toward both side ends. 10. The method of claim 9,
A nozzle for a combustor, characterized in that a plurality of vortex forming projections protruding toward the center of the injection tube are formed at the inner end of the dispersion plate. 10. The method of claim 9,
A plurality of the dispersion holes are nozzles for a combustor, characterized in that formed continuously in a radial direction of the injection tube. 10. The method of claim 9,
A plurality of the dispersion holes are nozzles for a combustor, characterized in that formed continuously in the circumferential direction of the injection tube. The method of claim 1,
A plurality of fuel inlet holes connected to the fuel passage and through which fuel is introduced into the injection tube are formed in the injection tube,
A nozzle for a combustor, characterized in that a fuel guide plate having a plurality of guide holes formed thereon is installed in front of the fuel inlet hole. 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 plurality of injection tubes through which air and fuel move and a multi-tube formed between the injection tubes and including a fuel passage through which fuel moves; and
a mixing plate spaced apart from the front of the multi-tube and having a plurality of mixing holes to mix fuel and air injected from the multi-tube;
A combustor comprising a. 17. The method of claim 16,
The mixing hole is disposed to face the injection hole formed in the injection tube at a distance, and the blocked part of the mixing plate is disposed to face the blocking plate installed at the tip of the multi-tube. 17. The method of claim 16,
A plurality of fuel inlet holes connected to the fuel passage and through which fuel is introduced into the injection tube are formed in the injection tube,
A combustor, characterized in that a dispersion plate having a plurality of dispersion holes through which air passes is installed at the rear of the fuel inlet hole. 17. The method of claim 16,
A plurality of fuel inlet holes connected to the fuel passage and through which fuel is introduced into the injection tube are formed in the injection tube,
A combustor characterized in that a fuel guide plate having a plurality of guide holes formed thereon is installed in front of the fuel inlet hole. A gas turbine including a compressor for compressing air introduced from the outside, a combustor that mixes the 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, and a duct assembly coupled to one side of the burner, the fuel and the air are combusted therein, and the combusted gas is delivered to the turbine,
The nozzle is formed between a plurality of injection tubes through which air and fuel move, and a multi-tube including a fuel passage through which fuel moves, and is spaced apart from the front of the multi-tube, and includes a plurality of mixing holes. Gas turbine comprising a mixing plate for mixing the fuel and air injected from the multi-tube provided.

Images