Combustor nozzles and gas turbines including them

Abstract

The present invention provides a combustor nozzle and a gas turbine incorporating the same, which can enhance flame stability and improve the performance of the combustor. [Solution] The combustor nozzle of the present invention includes a nozzle assembly, the nozzle assembly including a central nozzle module formed in a cylindrical shape with a plurality of tubes arranged in parallel, a plurality of outer nozzle modules arranged around the central nozzle module with a plurality of tubes arranged in parallel, a local cavity formed so as to allow gas to flow into the front central interior of the central nozzle module, and a local cavity formed so as to allow gas to flow into the front central interior of the plurality of outer nozzle modules.

Description

Technical Field

[0001] The present invention relates to a nozzle for a combustor and a gas turbine including the same, and more particularly, to a nozzle for a combustor in which local cavities are formed in a central nozzle module and a central portion of a plurality of outer nozzle modules, and a gas turbine including the same.

Background Art

[0002] A gas turbine is a power generation engine that mixes and burns compressed air compressed by a compressor and fuel, and rotates a turbine with the high-temperature gas generated by the combustion. Gas turbines are used to drive generators, aircraft, ships, trains, and the like.

[0003] Generally, a gas turbine includes a compressor, a combustor, and a turbine. The compressor inhales and compresses external air and then transfers it to the combustor. The air compressed by the compressor becomes in a high-pressure and high-temperature state. The combustor mixes and burns the compressed air flowing in from the compressor and the fuel. The combustion gas generated by the combustion is discharged to the turbine. The turbine blades inside the turbine are rotated by the combustion gas, and thereby power is generated. The generated power is used in various fields such as power generation and driving of mechanical devices.

[0004] Fuel is injected through a nozzle provided in each combustor, and the nozzle can inject gaseous fuel and liquid fuel. Recently, in order to suppress carbon dioxide emissions, the use of hydrogen fuel or fuel containing hydrogen is recommended.

[0005] However, since hydrogen has a high combustion speed, when these fuels are burned in a gas turbine combustor, the flame formed in the gas turbine combustor approaches and heats the structure of the gas turbine combustor, which may cause problems in the reliability of the gas turbine combustor.

Summary of the Invention

Problems to be Solved by the Invention

[0006] The present invention aims to provide a combustor nozzle and a gas turbine including the same, which can improve flame stability and combustor performance by forming local cavities in the center of a central nozzle module and in the center of a plurality of outer nozzle modules. [Means for solving the problem]

[0007] To achieve the above objective, the combustor nozzle of the present invention includes a nozzle assembly, the nozzle assembly including a central nozzle module formed in a cylindrical shape with a plurality of tubes arranged in parallel, a plurality of outer nozzle modules arranged around the central nozzle module with a plurality of tubes arranged in parallel, a local cavity formed so as to allow gas to flow into the front central interior of the central nozzle module, and a local cavity formed so as to allow gas to flow into the front central interior of the plurality of outer nozzle modules.

[0008] The nozzle assembly may further include a circumferential groove formed recessed between the central nozzle module and a plurality of outer nozzle modules, and radial grooves formed recessed between the plurality of outer nozzle modules.

[0009] The local cavity of the central nozzle module may include a cavity wall formed in a conical groove shape at the front center.

[0010] The local cavity of the central nozzle module may further include a central channel connected to the rear surface of the cavity wall.

[0011] The local cavity of the central nozzle module may further include a cavity formed behind the cavity wall and the front wall of the central nozzle module, communicating with the space between the multiple tubes.

[0012] The cavity can communicate with the space between the tubes through multiple communication holes formed at the front end of the central channel.

[0013] The local cavity of the outer nozzle module may include a cavity wall formed in the shape of a triangular pyramidal groove at the center of the front surface.

[0014] The local cavity of the outer nozzle module may further include a central channel connected to the rear surface of the cavity wall.

[0015] The local cavity of the outer nozzle module may further include a cavity formed behind the cavity wall and the front wall of the outer nozzle module, communicating with the space between the multiple tubes.

[0016] The cavity is formed so as to be separated by a predetermined distance from the cavity wall and the rear side of the front wall of the outer nozzle module, and may include an impact wall through which a plurality of impact holes are formed.

[0017] The local cavity of the outer nozzle module may further include a first fuel cavity formed outside the front end sidewall of the central flow path, and a second fuel cavity formed around the sidewall of the central flow path and partitioned by an inclined wall that constitutes the rear sidewall of the first fuel cavity.

[0018] Multiple slots may be formed through the front end side wall of the central flow channel, connecting the central flow channel to the first fuel cavity.

[0019] The gas turbine of the present invention includes a compressor for compressing air flowing in from the outside, a combustor for mixing and burning the compressed air compressed by the compressor with fuel, and a turbine including a plurality of turbine blades that are rotated by the combustion gas burned in the combustor. The combustor includes a combustor nozzle including a nozzle assembly, and a duct assembly coupled to one side of the nozzle, in which compressed air and fuel are burned and the burned combustion gas is transmitted to the turbine. The nozzle assembly is formed in a cylindrical shape and includes a central nozzle module with a plurality of tubes arranged in parallel, a plurality of outer nozzle modules arranged around the central nozzle module with a plurality of tubes arranged in parallel, a local cavity formed to allow gas to flow into the front center of the central nozzle module, and a local cavity formed to allow gas to flow into the front center of the plurality of outer nozzle modules.

[0020] The local cavity of the central nozzle module may include a cavity wall formed in a conical groove shape at the front center.

[0021] The local cavity of the central nozzle module may further include a central channel connected to the rear surface of the cavity wall.

[0022] The local cavity of the central nozzle module may further include a cavity formed behind the cavity wall and the front wall of the central nozzle module, communicating with the space between the multiple tubes.

[0023] The local cavity of the outer nozzle module may include a cavity wall formed in the shape of a triangular pyramidal groove in the center of the front surface, a central flow path connected to the rear surface of the cavity wall, and a cavity formed behind the cavity wall and the front surface of the outer nozzle module, communicating with the space between the multiple tubes.

[0024] The cavity can be formed at a predetermined distance behind the cavity wall and the front wall of the outer nozzle module, and can include a collision wall through which a plurality of collision holes are formed.

[0025] The local cavity of the outer nozzle module can further include a first fuel cavity formed outside the front end side wall of the central flow path, and a second fuel cavity formed around the side wall of the central flow path and partitioned by an inclined wall constituting the rear side wall of the first fuel cavity.

[0026] A plurality of slots for communicating the central flow path and the first fuel cavity may be formed through the front end side wall of the central flow path.

Advantages of the Invention

[0027] According to the nozzle for a combustor of the present invention and the gas turbine including the same, by forming local cavities at the centers of the central nozzle module and the plurality of outer nozzle modules, the stability of the flame can be enhanced and the performance of the combustor can be improved.

Brief Description of the Drawings

[0028] [Figure 1] It is a partially cut-away perspective view of a gas turbine according to an embodiment of the present invention. [Figure 2] It is a cross-sectional view showing the combustor of FIG. 1. [Figure 3] It is a front perspective view showing a nozzle assembly according to an embodiment of the present invention. [Figure 4] It is a rear perspective view showing the nozzle assembly of FIG. 3. [Figure 5] It is a perspective view showing the central nozzle module of FIG. 3. [Figure 6] It is a view showing the tube inlet portion of the central nozzle module. [Figure 7] It is a cross-sectional view showing the tube inlet portion of FIG. 6. [Figure 8] It is a cut-away perspective view of the central nozzle module along a plane perpendicular to the center from near the outlet portion. [Figure 9] Figure 8 is a partially cut perspective view showing the tube in which the pilot channel has been formed. [Figure 10] This is a cross-sectional view showing gas flowing inside a tube in which a swirling channel and a pilot channel are formed. [Figure 11] This is a cross-sectional perspective view of the central nozzle module and one outer nozzle module along a plane passing through their centers. [Figure 12] Figure 11 is a front perspective view. [Figure 13] This figure shows a magnified view of the local cavity area of ​​the central nozzle module in Figure 12. [Figure 14] This is a perspective view showing the outer nozzle module. [Figure 15] Figure 14 is a rear perspective view showing the outer nozzle module. [Figure 16] Figure 14 is a cross-sectional perspective view of the outer nozzle module along a plane passing through its center. [Figure 17] This is a cross-sectional perspective view of the outer nozzle module, taken from near the outlet along a plane perpendicular to the center. [Figure 18] Figure 17 is a partially cut perspective view showing the tube in which the pilot channel was formed. [Figure 19] This is a partially cutaway perspective view showing the impact wall and hole formed near the tube outlet of the outer nozzle module. [Figure 20] This is a cross-sectional view showing gas flowing inside a tube in which a swirling channel and a pilot channel are formed. [Figure 21] This diagram shows a plane for measuring the gas flow velocity around a circumferential groove. [Figure 22] Figure 21 shows an image illustrating the flow velocity of a gas flowing on a plane. [Figure 23] This figure shows a plane for measuring the gas flow velocity around a radial groove. [Figure 24] Figure 23 shows an image illustrating the flow velocity of a gas flowing on a plane. [Figure 25] This diagram shows a plane for measuring the gas flow velocity around the local cavity of the central nozzle module. [Figure 26] Figure 25 shows an image illustrating the flow velocity of a gas flowing on a plane. [Figure 27] This figure shows a plane for measuring the gas flow velocity around the local cavity of the outer nozzle module. [Figure 28] Figure 27 shows an image illustrating the flow velocity of a gas flowing on a plane. [Modes for carrying out the invention]

[0029] While the present invention can have various embodiments through diverse transformations, specific embodiments will be illustrated and described in detail in the detailed description. However, it should be understood that this is not intended to limit the present invention to specific embodiments, but rather to include all transformations, equivalents, or substitutions that fall within the spirit and technical scope of the present invention.

[0030] The terms used in this invention are used solely to describe specific embodiments and are not intended to limit the invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this invention, terms such as “includes” or “having” are intended to specify the existence of features, figures, stages, operations, components, parts, or combinations thereof described in the specification, and should be understood not to preemptively exclude the possibility of the existence or addition of one or more other features, figures, stages, operations, components, parts, or combinations thereof.

[0031] Preferred embodiments of the present invention will be described in detail below with reference to the attached drawings. Note that, in the attached drawings, identical components are represented by the same reference numerals whenever possible. Furthermore, detailed descriptions of known functions and configurations that may obscure the gist of the present invention will be omitted. For similar reasons, some components in the attached drawings are exaggerated, omitted, or shown schematically.

[0032] The following describes the combustor nozzle, combustor, and gas turbine including the same according to the present invention.

[0033] Figure 1 is a partially cut-out perspective view of a gas turbine according to one embodiment of the present invention, and Figure 2 is a cross-sectional view showing the combustor of Figure 1.

[0034] The gas turbine according to the first embodiment of the present invention will be described below with reference to Figures 1 and 2. The thermodynamic cycle of the gas turbine 1000 according to this embodiment can ideally be a Brayton cycle. The Brayton cycle can consist of four processes: isentropic compression (adiabatic compression), constant-pressure heat supply, isentropic expansion (adiabatic expansion), and constant-pressure heat dissipation. That is, atmospheric air is drawn in and compressed to high pressure, then fuel is burned in a constant-pressure environment to release thermal energy, and after this high-temperature combustion gas is expanded and converted into kinetic energy, exhaust gas containing residual energy can be released into the atmosphere. In other words, the cycle is carried out in four processes: compression, heating, expansion, and heat dissipation.

[0035] A gas turbine 1000 that implements such a Brayton cycle may include a compressor 1100, a combustor 1200, and a turbine 1300, as shown in Figure 1. The following description will refer to Figure 1, but the description of the present invention is also broadly applicable to turbine engines having a configuration equivalent to the gas turbine 1000 shown as an example in Figure 1.

[0036] Referring to Figure 1, the compressor 1100 of the gas turbine 1000 can draw in air from the outside and compress it. The compressor 1100 supplies compressed air, compressed by the compressor blades 1130, to the combustor 1200, and can also supply cooling air to high-temperature regions of the gas turbine 1000 that require cooling. At this time, the inhaled air undergoes an adiabatic compression process in the compressor 1100, so the pressure and temperature of the air that has passed through the compressor 1100 increase.

[0037] The compressor 1100 can be designed as either a centrifugal compressor or an axial compressor. While centrifugal compressors are used in small gas turbines, large gas turbines like the one shown in Figure 1, which must compress a large volume of air, generally use multi-stage axial compressors. In this case, the compressor blades 1130 of the compressor 1100 rotate due to the rotation of the rotor disk, compressing the incoming air and moving the compressed air to the subsequent compressor vanes 1140. The air is compressed to increasingly higher pressures as it passes through the multi-stage compressor blades 1130.

[0038] The compressor vanes 1140 are mounted inside the housing 1150, and multiple compressor vanes 1140 can be mounted in a stepped configuration. The compressor vanes 1140 guide the compressed air that has moved from the preceding compressor blade 1130 toward the subsequent compressor blade 1130. In one embodiment, at least some of the multiple compressor vanes 1140 can be mounted so as to be rotatable within a defined range for purposes such as adjusting the amount of air inflow.

[0039] The compressor 1100 can be driven using a portion of the power output from the turbine 1300. For this reason, the rotating shaft of the compressor 1100 and the rotating shaft of the turbine 1300 can be directly connected, as shown in Figure 1. In the case of a large gas turbine 1000, approximately half of the power produced by the turbine 1300 may be consumed in driving the compressor 1100. Therefore, improving the efficiency of the compressor 1100 has a direct impact on improving the overall efficiency of the gas turbine 1000.

[0040] The turbine 1300 includes a rotor disk 1310 and a plurality of turbine blades and turbine vanes arranged radially on the rotor disk 1310. The rotor disk 1310 has a substantially disc shape, and a plurality of grooves are formed on its outer circumference. The grooves are formed to have curved surfaces, and the turbine blades and turbine vanes are inserted into the grooves. The turbine vanes are fixed so as not to rotate and guide the flow direction of the combustion gases that have passed through the turbine blades. The turbine blades generate rotational force as they rotate due to the combustion gases.

[0041] On the other hand, the combustor 1200 can mix compressed air supplied from the outlet of the compressor 1100 with fuel and perform isobaric combustion to produce high-energy combustion gases. Figure 2 shows an example of a combustor 1200 applied to a gas turbine 1000. The combustor 1200 may include a combustor casing 1210, a nozzle 1220, and a duct assembly 1240.

[0042] The combustor casing 1210 surrounds the nozzle 1220 and may have a substantially circular cylindrical shape. The nozzle 1220 is located downstream of the compressor 1100 and can be positioned along the annular combustor casing 1210. The nozzle 1220 is provided with at least one nozzle module 1400, in which fuel and air are mixed in an appropriate ratio and then injected to a state suitable for combustion.

[0043] Gas turbine 1000 can use gaseous fuel, and in particular, fuel containing hydrogen can be used. The fuel may consist of hydrogen fuel alone, or a fuel containing hydrogen and natural gas.

[0044] The duct assembly 1240 connects the nozzle 1220 and the turbine 1300, through which high-temperature combustion gases flow. Compressed air flows over the outer surface of the duct assembly 1240 and is supplied to the nozzle 1220, and in this process the duct assembly 1240, which has been heated by the high-temperature combustion gases, is properly cooled.

[0045] The duct assembly 1240 may include a liner 1241, a transition piece 1242, and a fluid sleeve 1243. The duct assembly 1240 has a double structure in which the fluid sleeve 1243 surrounds the liner 1241 and the transition piece 1242, and compressed air permeates into the annular space inside the fluid sleeve 1243 to cool the liner 1241 and the transition piece 1242.

[0046] The liner 1241 is a tubular member connected to the nozzle 1220 of the combustor 1200, and the space inside the liner 1241 forms the combustion chamber 1230. One longitudinal end of the liner 1241 is connected to the nozzle 1220, and the other longitudinal end of the liner 1241 is connected to the transition piece 1242.

[0047] The transition piece 1242 is connected to the inlet of the turbine 1300 and serves to guide the hot combustion gases into the turbine 1300. One longitudinal end of the transition piece 1242 is connected to the liner 1241, and the other longitudinal end of the transition piece 1242 is connected to the turbine 1300. The fluid sleeve 1243 protects the liner 1241 and the transition piece 1242, while preventing the hot air from being directly released to the outside.

[0048] Figure 3 is a front perspective view showing a nozzle assembly according to one embodiment of the present invention, and Figure 4 is a rear perspective view showing the nozzle assembly of Figure 3.

[0049] Figure 5 is a perspective view showing the central nozzle module of Figure 3, Figure 6 is a diagram showing the tube inlet of the central nozzle module, Figure 7 is a cross-sectional view showing the tube inlet of Figure 6, Figure 8 is a dissected perspective view of the central nozzle module from near the outlet along a plane perpendicular to the center, Figure 9 is a partially dissected perspective view showing the tube in Figure 8 in which the pilot channel is formed, Figure 10 is a cross-sectional view showing the flow of gas inside the tube in which the swara and pilot channel are formed, Figure 11 is a dissected perspective view of the central nozzle module and one outer nozzle module along a plane passing through their centers, Figure 12 is a front perspective view of Figure 11, and Figure 13 is a magnified view showing the local cavity portion of the central nozzle module in Figure 12.

[0050] Figure 14 is a perspective view showing the outer nozzle module; Figure 15 is a rear perspective view showing the outer nozzle module of Figure 14; Figure 16 is a dissected perspective view of the outer nozzle module of Figure 14 along a plane passing through its center; Figure 17 is a dissected perspective view of the outer nozzle module along a plane perpendicular to the center, starting near the outlet; Figure 18 is a partially dissected perspective view showing the tube in Figure 17 in which the pilot channel is formed; Figure 19 is a partially dissected perspective view showing the impact wall and hole formed near the tube outlet of the outer nozzle module; and Figure 20 is a cross-sectional view showing the flow of gas inside the tube in which the swara and pilot channel are formed.

[0051] The combustor nozzle 1220 according to the first embodiment of the present invention will be described in detail below with reference to Figures 3 to 20. The combustor nozzle 1220 according to the first embodiment of the present invention includes a nozzle assembly 1400 composed of a plurality of nozzle modules.

[0052] The nozzle assembly 1400 may include a central nozzle module 1500 formed in a cylindrical shape with a plurality of tubes 1530 arranged in parallel, and a plurality of outer nozzle modules 1600 arranged around the central nozzle module with a plurality of tubes 1630 arranged in parallel.

[0053] As shown in Figures 3 to 5, the central nozzle module 1500 is composed of a shell body portion 1510 whose outer casing is formed in a substantially cylindrical shell shape, and a plurality of tubes 1530 may be arranged parallel to each other and spaced apart inside the shell body portion 1510.

[0054] The central nozzle module 1500 may be provided with chamfered sections 1520 consisting of multiple inclined planes at the front and rear corners. The multiple inclined planes of the chamfered section 1520 may consist of six inclined planes with a relatively large circumferential width and six inclined planes with a relatively small circumferential width.

[0055] As shown in Figures 3, 4, 14, and 15, the outer nozzle module 1600 may have a fan-shaped cross-section. Inside the outer nozzle module 1600, a plurality of tubes 1630 may be arranged parallel to each other and spaced apart.

[0056] The outer nozzle module 1600 is composed of a fan-shaped pyloric shell body portion 1610, and may include a plurality of chamfered portions 1620 formed at the front corners of the shell body portion 1610.

[0057] Multiple chamfered sections 1620 may be formed as inclined planes at the linear corners on both sides in the circumferential direction of the front corner of the fan-shaped trapezoid, and as inclined curved surfaces at the radially outer and inner arc-shaped corners.

[0058] The nozzle assembly 1400 may include a circumferential groove 1525 recessed between the central nozzle module 1500 and a plurality of outer nozzle modules 1600, and radial grooves 1625 recessed between the plurality of outer nozzle modules 1600.

[0059] The circumferential groove 1525 may be formed by the chamfered portion 1520 of the central nozzle module 1500 and the multiple chamfered portions 1620 formed on the inclined curved surfaces inside the multiple outer nozzle modules 1600.

[0060] The chamfered portion 1520 of the central nozzle module 1500 may be formed in multiple inclined planes at the front corner, and the inner chamfered portions 1620 of the multiple outer nozzle modules 1600 may be formed in an arc-shaped inclined curved surface. Therefore, the circumferential groove 1525 may be formed by the circumferential chamfered portion 1520 of the central nozzle module 1500 and the multiple chamfered portions 1620 formed on the radially inward arc-shaped inclined curved surfaces of the multiple outer nozzle modules 1600 and connected to each other.

[0061] The radial groove 1625 may be formed by a plurality of chamfered portions 1620 formed at the corners on both sides of the circumferential direction of a plurality of outer nozzle modules 1600.

[0062] A pair of chamfered portions 1620 formed at the circumferential corners of the outer nozzle module 1600 may be radially arranged and formed on an inclined plane. Thus, each chamfered portion 1620 of two outer nozzle modules 1600 arranged to be tangent in the circumferential direction can form a radial groove 1625 between the two outer nozzle modules 1600.

[0063] As shown in Figures 8 and 17, the nozzle assembly 1400 may include multiple pilot channels 1540, 1640 that communicate with the circumferential groove and radial groove from each of the tubes 1530, 1630 adjacent to the circumferential groove and radial groove.

[0064] Multiple pilot channels 1540 in the central nozzle module 1500 may be formed to connect to the chamfered portion 1520 on the front side of the tubes 1530 that are located on the outer side of the tubes 1530 that are closer to the chamfered portion 1520. The pilot channels 1540 may be arranged from the side walls of each tube 1530 toward the outer circumferential surface of the central nozzle module 1500.

[0065] As shown in Figures 9 and 18, the multiple pilot channels 1540 of the central nozzle module 1500 may be connected to the chamfered section 1520 from the inner surface of the tube 1530, which is positioned adjacent to the circumferential groove 1525.

[0066] The pilot channel 1540 may be formed to protrude from the inner circumferential surface of the tube 1530, with a flat inlet and a circular cross-section at the outlet. The pilot channel 1540 may be formed so as to have a flat inlet protruding from the inner circumferential surface of the tube 1530, to penetrate the side wall of the tube 1530, and to connect to an outlet having a circular cross-section. As shown in Figure 10, the line along the center of the pilot channel 1540 may be formed as a smoothly bent curve rather than a straight line.

[0067] Multiple pilot channels 1640 in the outer nozzle module 1600 may be formed to connect to the chamfered portion 1620 on the front side of the tubes 1630 that are located on the outer side of the tubes 1630 that are closer to the chamfered portion 1620. The pilot channels 1640 may be arranged from the side walls of each tube 1630 toward the outer circumferential surface of the central nozzle module 1600.

[0068] Multiple pilot channels 1640 of the outer nozzle module 1600 may be connected to chamfered sections 1620 from the inner surfaces of tubes 1630 positioned adjacent to circumferential grooves 1525 and radial grooves 1625. The chamfered sections 1620 to which the pilot channels 1640 are connected may include a pair of inclined planes formed on both sides of the outer nozzle module 1600 and an inclined curved surface formed radially inward of the outer nozzle module 1600.

[0069] The pilot channel 1640 may be formed to protrude from the inner circumferential surface of the tube 1630, with a flat inlet and a circular cross-section at the outlet. The pilot channel 1640 may be formed so that its flat inlet protrudes from the inner circumferential surface of the tube 1630, is integrally formed to penetrate the side wall of the tube 1630, and is connected to an outlet having a circular cross-section. As shown in Figure 20, the line along the center of the pilot channel 1640 may be formed as a smoothly bent curve rather than a straight line.

[0070] As shown in Figures 4, 6, 7, 10, and 20, the multiple tubes 1530, 1630 of the central nozzle module 1500 and the multiple outer nozzle modules 1600 may be equipped with multiple swaras 1535, 1635 that are spirally formed on the inside of the inlet.

[0071] As shown in Figures 6, 7, and 10, the swara 1535 can be integrally formed on the inner circumferential surface of the inlet of the tube 1530 of the central nozzle module 1500. Multiple swaras 1535 can be formed in a spiral shape, with three swaras spaced 120 degrees apart.

[0072] As shown in Figures 6 and 7, the tube 1530 may include a plurality of first fuel ports 1531 formed through the side wall between a plurality of swaras 1535, and a plurality of second fuel ports 1532 formed through the swaras 1535 from the outer circumferential surface of the side wall.

[0073] The first fuel port 1531 may be formed by penetrating the side wall of the tube 1530 at an angle toward the inlet side.

[0074] The second fuel port 1532 may be formed inclined to penetrate the side wall of the tube 1530 and the swirler 1535 toward the inlet side.

[0075] Fuel can flow into the interior of the tube 1530 from the outer circumference of the tube 1530 through multiple first fuel ports 1531 and multiple second fuel ports 1532.

[0076] As shown in Figures 12 and 20, the swara 1635 can be integrally formed on the inner circumferential surface of the inlet of the tube 1630 of the outer nozzle module 1600. Multiple swaras 1635 can be formed in a spiral shape, with three arranged at 120-degree intervals.

[0077] The swirler 1635 of the outer nozzle module 1600 may also have multiple first fuel ports and multiple second fuel ports, similar to the swirler 1535 of the central nozzle module 1500.

[0078] By forming swaras 1535 and 1635 inside the inlet side of tubes 1530 and 1630, the air and fuel flowing into the tubes can be effectively mixed with each other while rotating.

[0079] As shown in Figure 3, the nozzle assembly 1400 may further include a local cavity 1550 formed to allow gas to flow into the front central interior of the central nozzle module 1500, and local cavities 1650 formed to allow gas to flow into the front central interiors of the multiple outer nozzle modules 1600.

[0080] As shown in Figures 5, 12, and 13, the local cavity 1550 of the central nozzle module 1500 may include a cavity wall 1552 formed in a conical groove shape at the front center.

[0081] The cavity wall 1552 may be formed in the shape of a recessed conical groove in the center of the outlet-side front wall of the central nozzle module 1500.

[0082] The local cavity 1550 of the central nozzle module 1500 may further include a central channel 1560 connected to the rear surface of the cavity wall 1552.

[0083] The central channel 1560 may be formed in a circular tubular shape with a larger diameter than the surrounding tubes 1530. The rear inlet of the central channel 1560 is not provided with a swirler. Fuel flows into the central channel 1560 through the rear inlet, and the front outlet is blocked by the cavity wall 1552 and the front wall of the shell body 1510, so that the incoming fuel does not flow out to the front end but flows only within the internal space.

[0084] As shown in Figures 11 to 13, the local cavity 1550 of the central nozzle module 1500 may further include a cavity 1554 formed behind the cavity wall 1552 and the front wall of the central nozzle module 1500, communicating with the space between the multiple tubes 1530.

[0085] The cavity 1554 may be formed in a space partitioned around the cavity wall 1552 at the front end of the central channel 1560. This cavity 1554 can also be formed in the space between the multiple tubes 1530 from the front end of the shell body 1510.

[0086] The cavity 1554 can communicate with the space between the multiple tubes 1530 from the central channel 1560 through a plurality of communication holes formed at the front end of the central channel 1560.

[0087] Multiple communication holes are formed through the side wall separating the central channel 1560 and the cavity 1554, allowing fuel flowing into the central channel 1560 to flow through these communication holes not only into the cavity 1554 surrounding the central channel 1560 but also into the spaces between the multiple tubes 1530.

[0088] As shown in Figures 14 to 17, the local cavity 1650 of the outer nozzle module 1600 may include a cavity wall 1651 formed in the shape of a triangular pyramidal groove at the center of the front surface.

[0089] The cavity wall 1651 may be formed in the shape of a recessed triangular pyramidal groove in the center of the outlet-side front wall of the outer nozzle module 1600. In this case, the triangle formed when the cavity wall 1651 meets the front end surface of the shell body 1610 may have its base positioned radially inward and its vertex positioned radially outward.

[0090] The local cavity 1650 of the outer nozzle module 1600 may further include a central channel 1660 connected to the rear surface of the cavity wall 1651.

[0091] The central channel 1660 may be formed in a circular tubular shape with a larger diameter than the surrounding tubes 1630. The rear inlet of the central channel 1660 is not provided with a swirler. Fuel flows into the central channel 1660 through the rear inlet, and the front outlet is blocked by the cavity wall 1651 and the front wall of the shell body 1610, so that the incoming fuel does not flow out to the front end but flows only within the internal space.

[0092] The local cavity 1650 of the outer nozzle module 1600 may further include a cavity wall 1651 and a cavity 1654 formed behind the front wall of the outer nozzle module 1600, which communicates with the space between the multiple tubes 1630.

[0093] The cavity 1654 may be formed in a space partitioned around the cavity wall 1651 at the front end of the central flow channel 1660. This cavity 1654 can also be formed in the space between the multiple tubes 1630 from the front end of the shell body 1610.

[0094] The cavity 1654 is formed at a predetermined distance from the cavity wall 1651 and the rear side of the front wall of the outer nozzle module 1600, and may include an impact wall 1652 through which a plurality of impact holes 1653 are formed.

[0095] The impact wall 1652 may be formed behind the cavity wall 1651 and the front wall of the shell body 1610, at a predetermined distance from them. Multiple impact holes 1653 may be formed through the impact wall 1652, arranged toward the cavity wall 1651 and the front wall of the shell body 1610. The fuel flowing into the central flow path 1660 can flow into the cavity 1654 through the multiple impact holes 1653, and as it flows, it can impact and cool the surrounding wall of the cavity 1654.

[0096] As shown in Figure 16, the local cavity 1650 of the outer nozzle module 1600 may further include a first fuel cavity 1655 formed outside the front end side wall of the central flow path 1660, and a second fuel cavity 1658 formed around the side wall of the central flow path 1660 and partitioned by an inclined wall 1657 that constitutes the rear side wall of the first fuel cavity 1655.

[0097] The first fuel cavity 1655 may be formed outside the front end side wall of the central flow channel 1660 in the space surrounding the central flow channel 1660, and in the space behind the impact wall 1652.

[0098] The second fuel cavity 1658 is a space formed around the side wall of the central flow path 1660 and may be formed by being partitioned by the inclined wall 1657 that constitutes the rear side wall of the first fuel cavity 1655.

[0099] Multiple slots 1656 that connect the central flow path 1660 to the first fuel cavity 1655 may be formed through the front end side wall of the central flow path 1660.

[0100] Multiple slots 1656 may be formed to penetrate the side wall of the central flow channel 1660 in a longitudinal direction near the rear surface of the collision wall 1652.

[0101] A portion of the fuel flowing into the central flow path 1660 can flow into the first fuel cavity 1655 through a plurality of slots 1656. The fuel that has flowed into the first fuel cavity 1655 can flow into cavity 1654 through a plurality of impact holes 1653 formed in the impact wall 1652 in front of it, and can be cooled by impact. A plurality of communication holes are also formed in the outer wall of cavity 1654, and the fuel that has flowed into cavity 1654 can flow into the second fuel cavity 1658 through a plurality of communication holes.

[0102] In this way, the fuel flowing into the central flow path 1660 flows into the cavity 1654, undergoing collision cooling, and circulates to the second fuel cavity 1658, cooling the nozzle tip portion of the outer nozzle module 1600. Subsequently, the fuel flowing into the second fuel cavity 1658 flows into the tube 1630 through a plurality of fuel ports formed in the side wall of the inlet of the tube 1630, where it can be mixed with air.

[0103] Figure 21 shows a plane for measuring the gas flow velocity around a circumferential groove, Figure 22 is an image illustrating the gas flow velocity on the plane shown in Figure 21, Figure 23 shows a plane for measuring the gas flow velocity around a radial groove, and Figure 24 is an image illustrating the gas flow velocity on the plane shown in Figure 23.

[0104] As shown in Figures 21 and 22, the nozzle assembly 1400 of the present invention allows a portion of the air-fuel mixture gas, mixed in a plurality of tubes 1530, 1630, to flow out into the circumferential groove 1525 through a plurality of pilot passages 1540, 1640.

[0105] This creates a recirculation zone around the outlet circumferential groove of the nozzle assembly 1400, improving flame stability, which can lead to improvements in the combustor's dynamics and turndown performance.

[0106] As shown in Figures 23 and 24, the nozzle assembly 1400 of the present invention allows a portion of the air-fuel mixture gas, mixed in a plurality of tubes 1630, to flow out into the radial groove 1625 through a plurality of pilot passages 1640.

[0107] This creates a recirculation zone around the outlet-side radial groove of the nozzle assembly 1400, improving flame stability, which can lead to improvements in the combustor's dynamics and turndown performance.

[0108] Figure 25 shows a plane for measuring the gas flow velocity around the local cavity of the central nozzle module, Figure 26 is an image showing the gas flow velocity on the plane shown in Figure 25, Figure 27 shows a plane for measuring the gas flow velocity around the local cavity of the outer nozzle module, and Figure 28 is an image showing the gas flow velocity on the plane shown in Figure 27.

[0109] As shown in Figures 25 and 26, the nozzle assembly 1400 of the present invention provides a local cavity 1550 in the center of the central nozzle module 1500, thereby forming a recirculation zone around it, which improves flame stability, and can lead to improvements in combustor dynamics and turndown performance.

[0110] As shown in Figures 27 and 28, the nozzle assembly 1400 of the present invention provides a local cavity 1650 in the center of the outer nozzle module 1600, thereby forming a recirculation zone around it, which improves flame stability, and can lead to improvements in combustor dynamics and turndown performance.

[0111] According to the combustor nozzle, combustor, and gas turbine including the same of the present invention, flame stability can be enhanced and the interaction between nozzles can be improved by forming pilot channels in a central nozzle module and a plurality of outer nozzle modules with circumferential grooves or radial grooves from a plurality of tubes.

[0112] Although one embodiment of the present invention has been described above, any person with ordinary skill in the art can modify and change the present invention in various ways, such as by adding, changing, deleting, or adding components, without departing from the spirit of the invention as described in the claims, and this is also included within the scope of the rights of the present invention. [Explanation of Symbols]

[0113] 1000: Gas Turbine 1100: Compressor, 1130: Compressor blade 1140: Compressor vanes, 1150: Housing 1200: Combustor, 1210: Combustor casing 1220: Nozzle, 1230: Combustion chamber 1240: Duct assembly, 1241: Liner 1242: Transition piece, 1243: Fluid sleeve 1300: Turbine, 1310: Rotor Disc 1400: Nozzle assembly 1500: Central nozzle module, 1510: Shell body 1520: Changhwa section, 1525: Circumferential groove 1530: Tube, 1531: First fuel port 1532: Second fuel port, 1535: Swara 1540: Pilot channel, 1550: Local cavity 1552: Cavity wall, 1554: Cavity 1560: Central channel 1600: Outer nozzle module, 1610: Shell body 1620: Champha section, 1625: Radius groove 1630: Tube, 1635: Swara 1640: Pilot channel, 1650: Local cavity 1651: Cavity wall, 1652: Collision wall 1653: Hole, 1654: Cavity 1655: Fuel cavity 1, 1656: Slot 1657: Inclined wall, 1658: Second fuel cavity 1660: Central channel

Claims

1. In a combustor nozzle including a nozzle assembly, The nozzle assembly is A central nozzle module formed in a cylindrical shape, with multiple tubes arranged in parallel, A plurality of outer nozzle modules are arranged around the central nozzle module, with a plurality of tubes arranged in parallel, A local cavity formed inside the front central part of the central nozzle module so that gas flows through it, A combustor nozzle comprising a local cavity formed inside the front central part of the plurality of outer nozzle modules so that gas flows through it.

2. The nozzle assembly is A circumferential groove is formed recessed between the central nozzle module and the plurality of outer nozzle modules, The combustor nozzle according to claim 1, further comprising a radial groove formed recessed between the plurality of outer nozzle modules.

3. The combustor nozzle according to claim 2, wherein the local cavity of the central nozzle module includes a cavity wall formed in the shape of a cone groove at the center of the front surface.

4. The combustor nozzle according to claim 3, wherein the local cavity of the central nozzle module further includes a central flow path connected to the rear surface of the cavity wall.

5. The combustor nozzle according to claim 4, wherein the local cavity of the central nozzle module further includes a cavity formed behind the cavity wall and the front wall of the central nozzle module, and communicating with the space between the plurality of tubes.

6. The combustor nozzle according to claim 5, wherein the cavity is connected to the space between the plurality of tubes by a plurality of communication holes formed at the front end of the central flow path.

7. The combustor nozzle according to claim 3, wherein the local cavity of the outer nozzle module includes a cavity wall formed in the shape of a triangular pyramidal groove in the center of the front surface.

8. The combustor nozzle according to claim 7, wherein the local cavity of the outer nozzle module further includes a central flow path connected to the rear surface of the cavity wall.

9. The combustor nozzle according to claim 8, wherein the local cavity of the outer nozzle module further includes a cavity formed behind the cavity wall and the front wall of the outer nozzle module, and communicating with the space between the plurality of tubes.

10. The combustor nozzle according to claim 9, wherein the cavity is formed such that it is separated by a predetermined distance from the cavity wall and the rear side of the front wall of the outer nozzle module, and comprises an impact wall through which a plurality of impact holes are formed.

11. The local cavity of the aforementioned outer nozzle module is A first fuel cavity formed on the outside of the front end side wall of the central flow channel, The combustor nozzle according to claim 10, further comprising a second fuel cavity formed around the side wall of the central flow path and partitioned by an inclined wall constituting the rear side wall of the first fuel cavity.

12. The combustor nozzle according to claim 11, wherein a plurality of slots are formed through the front end side wall of the central flow path, connecting the central flow path and the first fuel cavity.

13. A gas turbine comprising a compressor for compressing air flowing in from the outside, a combustor for mixing and burning the compressed air compressed by the compressor with fuel, and a turbine including a plurality of turbine blades that rotate using the combustion gases burned in the combustor, The combustor includes a combustor nozzle including a nozzle assembly, and a duct assembly coupled to one side of the nozzle, in which the compressed air and fuel are burned and the burned combustion gas is transmitted to the turbine. The nozzle assembly is A central nozzle module formed in a cylindrical shape, with multiple tubes arranged in parallel, A plurality of outer nozzle modules are arranged around the central nozzle module, with a plurality of tubes arranged in parallel, A local cavity formed inside the front central part of the central nozzle module so that gas flows through it, A gas turbine including a local cavity formed inside the front central part of the plurality of outer nozzle modules so that gas flows through it.

14. The gas turbine according to claim 13, wherein the local cavity of the central nozzle module includes a cavity wall formed in the shape of a cone groove at the center of the front surface.

15. The gas turbine according to claim 14, wherein the local cavity of the central nozzle module further includes a central flow path connected to the rear surface of the cavity wall.

16. The gas turbine according to claim 15, wherein the local cavity of the central nozzle module further comprises a cavity formed behind the cavity wall and the front wall of the central nozzle module, and communicating with the space between the plurality of tubes.

17. The local cavity of the aforementioned outer nozzle module is A cavity wall formed in the shape of a triangular pyramidal groove in the center of the front, A central channel connected to the rear surface of the cavity wall, The gas turbine according to claim 13, wherein the local cavity of the outer nozzle module includes the cavity wall and a cavity formed behind the front wall of the outer nozzle module and communicating with the space between the plurality of tubes.

18. The gas turbine according to claim 17, wherein the cavity is formed such that it is separated by a predetermined distance from the cavity wall and the rear side of the front wall of the outer nozzle module, and comprises an impact wall through which a plurality of impact holes are formed.

19. The local cavity of the aforementioned outer nozzle module is A first fuel cavity formed on the outside of the front end side wall of the central flow channel, The gas turbine according to claim 18, further comprising a second fuel cavity formed around the side wall of the central flow path and partitioned by an inclined wall constituting the rear side wall of the first fuel cavity.

20. The gas turbine according to claim 19, wherein a plurality of slots are formed through the front end side wall of the central flow path, connecting the central flow path and the first fuel cavity.

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