Combustor nozzle, combustor and gas turbine including same

Abstract

To provide a nozzle for a combustor, the combustor, and a gas turbine including the same, capable of effectively cooling a central tube to minimize attachment of flame to the central tube and back-fire of the flame.SOLUTION: A nozzle for a combustor has a nozzle module including: a central tube having an air flow path through which air flows from a front part to a rear part and having an opening hole at a rear end; a shroud into which at least a part of the central tube is inserted and which has a mixing flow channel formed with the central tube to allow the air and injected fuel to flow therein and has an air inlet at a front end thereof; and a plurality of cooling channels respectively extending rearward from an inlet communicating with the air flow path to an outlet communicating with the mixing flow path while passing through the inside of a sidewall portion of the central tube.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present invention relates to a combustor nozzle, a combustor, and a gas turbine including the same, and more particularly to a combustor nozzle including a cooling channel, a combustor, and a gas turbine including the same. [Background technology]

[0002] A gas turbine is a power plant that rotates a turbine using the high-temperature gas generated by mixing compressed air and fuel, which is compressed by a compressor. Gas turbines are used to drive generators, aircraft, ships, trains, etc.

[0003] Generally, a gas turbine includes a compressor, a combustor, and a turbine. The compressor takes in external air, compresses it, and then sends it to the combustor. The air compressed by the compressor is in a high-pressure, high-temperature state. The combustor mixes the compressed air from the compressor with fuel and burns it. The combustion gas generated by the combustion is discharged to the turbine. The combustion gas rotates turbine blades inside the turbine, thereby generating power. The generated power is used in a variety of applications, such as generating electricity and driving mechanical devices.

[0004] Fuel is injected through nozzles in each combustor, which can inject both gaseous and liquid fuels. In recent years, the use of hydrogen fuel or fuels containing hydrogen has been encouraged to reduce carbon dioxide emissions.

[0005] However, because hydrogen has a high burning speed, when this fuel is burned in a gas turbine combustor, the flame formed in the gas turbine combustor approaches the structures of the gas turbine combustor and heats them, which may cause problems in terms of reliability of the gas turbine combustor. Summary of the Invention [Problem to be solved by the invention]

[0006] In view of the above technical background, an object of the present invention is to provide a combustor nozzle, a combustor, and a gas turbine including the same, which can effectively cool a central tube and minimize flame attachment to the central tube and flame flashback. [Means for solving the problem]

[0007] A combustor nozzle according to an embodiment of the present invention includes a central tube, a shroud, and a plurality of cooling channels. The central tube has an air flow passage formed therein through which air moves from front to rear, and an open hole formed at its rear end. At least a portion of the central tube is inserted into the shroud, and a mixed flow passage through which air and injected fuel move is formed between the shroud and the central tube, and an air inlet is formed at its front end. The cooling channels extend rearward from an inlet communicating with the air flow passage to an outlet communicating with the mixed flow passage, and are formed penetrating the inside of a sidewall portion of the central tube.

[0008] In one embodiment of the combustor nozzle according to the present invention, a cooling channel has an exit formed at an aft end of a center tube.

[0009] In a combustor nozzle according to one embodiment of the present invention, a first annular flow passage that connects all of a plurality of cooling channels is formed inside a side wall portion of a central tube.

[0010] In one embodiment of the combustor nozzle, a first annular passage is disposed between an inlet and an outlet of a cooling channel.

[0011] In a combustor nozzle according to one embodiment of the present invention, an air swirler that swirls the flow of air is disposed in an air passage.

[0012] SUMMARY OF THE PRESENTLY PREFERRED EMBODIMENT In a combustor nozzle according to an embodiment of the present invention, an air swirler is disposed spaced apart from an aft end portion of a center tube.

[0013] In one embodiment of the combustor nozzle according to the present invention, the air swirler is positioned aft of the inlet of the cooling channel.

[0014] In a combustor nozzle according to one embodiment of the present invention, a turbulence creating member that creates turbulence in the flow of air is disposed in an air flow passage.

[0015] In a combustor nozzle according to one embodiment of the present invention, a turbulence creating member is disposed spaced apart from an aft end portion of a center tube.

[0016] In one embodiment of the combustor nozzle, the turbulence creating member is positioned aft of the inlet of the cooling channel.

[0017] In one embodiment of the combustor nozzle, a plurality of cooling channels are positioned side-by-side within a sidewall of a center tube.

[0018] In one embodiment of the combustor nozzle, a plurality of cooling channels are arranged in a spiral configuration within a sidewall of a center tube.

[0019] In a combustor nozzle according to an embodiment of the present invention, an expansion portion is formed in an opening hole of a central tube, the flow cross-sectional area of ​​which increases toward the rear.

[0020] In a combustor nozzle according to one embodiment of the present invention, the outlet of the cooling channel is formed at the aft end of the central tube and is inclined axially and radially from the periphery of the extension section.

[0021] In one embodiment of the combustor nozzle according to the present invention, a second annular passage is formed around the rear end of the central tube and the expansion portion, the second annular passage having one end communicating with all of the outlets of the cooling channels and the other end communicating with the mixing passage.

[0022] A combustor according to an embodiment of the present invention includes a combustor nozzle and a duct assembly. The duct assembly is coupled to one side of the nozzle, and combusts fuel and air therein and transmits the combusted gas to a turbine. The nozzle includes a central tube, a shroud, and a plurality of cooling channels. The central tube has an air passage formed therein through which air moves from front to rear, and an opening hole formed at its rear end. The shroud has at least a portion of the central tube inserted therein, and a mixed passage formed between the central tube and the shroud through which air and injected fuel move, and an air inlet formed at its front end. The cooling channel extends rearward from an inlet communicating with the air passage to an outlet communicating with the mixed passage, and is formed penetrating the inside of a sidewall portion of the central tube.

[0023] A combustor according to one embodiment of the present invention has a turbulence creating member disposed in an air passage for creating turbulence in a fuel flow.

[0024] SUMMARY OF THE PRESENT EMBODIMENT In one embodiment of the combustor, a plurality of cooling channels are arranged helically within a sidewall of a center tube.

[0025] In the combustor according to an embodiment of the present invention, an expansion part is formed in an opening hole of a central tube, the flow cross-sectional area of ​​which increases toward the rear.

[0026] A gas turbine according to an embodiment of the present invention includes a compressor, a combustor, and a turbine. The compressor compresses air flowing in from the outside. The combustor mixes the compressed air compressed by the compressor with fuel and burns the mixture. The turbine includes a plurality of turbine blades that rotate by combustion gas combusted in the combustor. The combustor includes a combustor nozzle and a duct assembly. The duct assembly is coupled to one side of the nozzle, combusts the compressed air and fuel inside, and transmits the combusted combustion gas to the turbine. The nozzle includes a central tube, a shroud, and a plurality of cooling channels. The central tube has an air flow path formed therein through which air moves from the front to the rear, and an opening hole is formed at the rear end. At least a portion of the central tube is inserted into the shroud, and a mixed flow path through which air and injected fuel move between the central tube and the shroud is formed, and an air inlet is formed at the front end. The shroud extends rearward from an inlet communicating with the air flow path to an outlet communicating with the mixed flow path, and is formed penetrating the inside of a side wall portion of the central tube. Effect of the Invention

[0027] The combustor nozzle, combustor, and gas turbine including the same according to the present invention have an advantage in that a cooling channel is formed in the central tube, thereby effectively cooling the central tube and minimizing flame attachment to the central tube and flame flashback. [Brief description of the drawings]

[0028] [Figure 1] 1 is a diagram showing the inside of a gas turbine according to a first embodiment of the present invention. [Diagram 2] FIG. 2 is a diagram showing the combustor of FIG. [Diagram 3] 1 is a vertical cross-sectional view showing an overall appearance of a nozzle module according to a first embodiment of the present invention. [Figure 4] FIG. 4 is a separate enlarged view of the cooling channel portion in FIG. 3. [Diagram 5] 5A and 5B are diagrams illustrating flow velocity and temperature distribution at the rear end of the central tube of the nozzle module according to the first embodiment of the present invention. [Figure 6]FIG. 11 is an enlarged view of a cooling channel of a nozzle module according to a second embodiment of the present invention. [Figure 7] FIG. 11 is an enlarged view of a cooling channel of a nozzle module according to a third embodiment of the present invention. [Figure 8] FIG. 13 is an enlarged view of a cooling channel of a nozzle module according to a fourth embodiment of the present invention. [Figure 9] FIG. 9 is a diagram showing a modification of FIG. 8. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0029] Although the present invention can be implemented in various ways, specific examples are 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 the specific embodiments, but includes any modifications, equivalents, or alternatives that fall within the spirit and technical scope of the present invention.

[0030] The terms used in the present invention are merely used to describe specific embodiments and are not intended to limit the present invention. A singular expression includes a plural expression unless the context clearly indicates otherwise. In the present invention, the terms "include" or "have" are intended to specify the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, and should be understood not to preclude the presence or addition of one or more other features, numbers, steps, operations, components, parts, or combinations thereof.

[0031] Hereinafter, a preferred embodiment 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 represented by the same reference numerals as much as possible. Also, detailed description of known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components are exaggerated or omitted, or shown in a schematic manner in the accompanying drawings.

[0032] Hereinafter, a combustor nozzle, a combustor, and a gas turbine including the same according to the present invention will be described.

[0033] FIG. 1 is a diagram showing the inside of a gas turbine according to a first embodiment of the present invention, and FIG. 2 is a diagram showing a combustor of FIG.

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

[0035] A gas turbine 1000 that realizes such a Brayton cycle can include a compressor 1100, a combustor 1200, and a turbine 1300, as shown in Fig. 1. The following description will refer to Fig. 1, but the description of the present invention can be widely applied to turbine engines having a configuration equivalent to that of the gas turbine 1000 illustrated as an example in Fig. 1.

[0036] 1, a compressor 1100 of a gas turbine 1000 can take in air from the outside and compress it. The compressor 1100 can supply compressed air compressed by compressor blades 1130 to a combustor 1200 and can also supply cooling air to a high-temperature area that needs to be cooled in the gas turbine 1000. At this time, the taken-in air undergoes an adiabatic compression process in the compressor 1100, so that the pressure and temperature of the air passing through the compressor 1100 increase.

[0037] The compressor 1100 is designed as a centrifugal compressor or an axial compressor, but while a centrifugal compressor is applied to a small gas turbine, a multi-stage axial compressor is generally applied to a large gas turbine 1000 as shown in Fig. 1 because a large amount of air must be compressed. In this case, in a multi-stage axial compressor, the compressor blades 1130 of the compressor 1100 rotate with the rotation of the rotor disk, compressing the incoming air and moving the compressed air to the compressor vanes 1140 in the subsequent stage. The air is gradually compressed to higher pressure as it passes through the compressor blades 1130 formed in multiple stages.

[0038] The compressor vanes 1140 are mounted inside the housing 1150, and the multiple compressor vanes 1140 are mounted to form stages. The compressor vanes 1140 guide the compressed air transferred from the compressor blades 1130 of the previous stage to the compressor blades 1130 of the subsequent stage. In one embodiment, at least a portion of the multiple compressor vanes 1140 are mounted rotatably within a set range to adjust the amount of inflow of air, etc.

[0039] The compressor 1100 can be driven by a part of the power output from the turbine 1300. For this purpose, as shown in Fig. 1, the rotating shaft of the compressor 1100 and the rotating shaft of the turbine 1300 can be directly connected. In the case of a large-scale gas turbine 1000, approximately half of the output generated by the turbine 1300 may be consumed to drive the compressor 1100. Therefore, improving the efficiency of the compressor 1100 has a direct effect on improving the overall efficiency of the gas turbine 1000.

[0040] The turbine 1300 includes a rotor disk 1310 and a number of turbine blades and turbine vanes arranged radially on the rotor disk 1310. The rotor disk 1310 has a generally circular plate shape, and a number of grooves are formed on its outer periphery. 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 gas that has passed through the turbine blades. The turbine blades generate rotational force as they rotate due to the combustion gas.

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

[0042] The combustor casing 1210 may be of a generally circular cylindrical shape and surrounds the nozzle 1220. The nozzle 1220 is disposed downstream of the compressor 1100 and is disposed along the annular combustor casing 1210. The nozzle 1220 includes at least one nozzle module 1400 where fuel and air are mixed in the proper ratio and then injected to provide conditions suitable for combustion.

[0043] The gas turbine 1000 may be gas fueled, and in particular may be fueled with hydrogen, and the fuel may consist of hydrogen alone or a combination of hydrogen and natural gas.

[0044] The duct assembly 1240 connects the nozzle 1220 and the turbine 1300, through which high-temperature combustion gas flows, and compressed air flows from the outer surface of the duct assembly 1240 and is supplied to the nozzle 1220 side. In the process, the duct assembly 1240, which is heated by the high-temperature combustion gas, is appropriately cooled.

[0045] The duct assembly 1240 may include a liner 1241, a transition piece 1242, and a flow sleeve 1243. The duct assembly 1240 has a double structure in which the flow sleeve 1243 surrounds the outside of the liner 1241 and the transition piece 1242, and the compressed air enters the annular space inside the flow 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 internal space of the liner 1241 forms the combustion chamber 1230. One end of the liner 1241 in the longitudinal direction is connected to the nozzle 1220, and the other end of the liner 1241 in the longitudinal direction is connected to the transition piece 1242.

[0047] The transition piece 1242 is connected to an inlet of the turbine 1300 to guide high-temperature combustion gas to 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 flow sleeve 1243 protects the liner 1241 and the transition piece 1242, while preventing high-temperature air from being directly discharged to the outside.

[0048] FIG. 3 is a longitudinal cross-sectional view showing the overall appearance of the nozzle module according to the first embodiment of the present invention, FIG. 4 is a separate enlarged view of the cooling channel portion in FIG. 3, and FIG. 5 is a view showing the flow velocity and temperature distribution at the rear end of the central tube of the nozzle module according to the first embodiment of the present invention.

[0049] Hereinafter, a combustor nozzle 1220 according to a first embodiment of the present invention will be described in detail with reference to Fig. 3 to Fig. 5. The combustor nozzle 1220 according to the first embodiment of the present invention includes at least one nozzle module 1400, and the nozzle module 1400 includes a central tube 1420, a shroud 1430, and a cooling channel 1450.

[0050] The central tube 1420 is a tubular member. The central tube 1420 may include a side wall portion 1421 having a predetermined thickness. A flange 1410 is disposed at the front end of the central tube 1420. Fuel may be supplied to the flange 1410. An air passage 1423 through which air moves from the front to the rear is formed inside the central tube 1420 or inside the side wall portion 1421. An opening hole 1424 is formed at the rear end 1422 of the central tube 1420. Thus, air in the air passage 1423 is discharged to the outside through the opening hole 1424. An air inflow port 1425 is formed in the central tube 1420. The air inflow port 1425 may pass through the central tube 1420 to communicate the inside and outside of the central tube 1420. The air inflow port 1425 is formed in the central tube 1420 immediately behind the flange 1410 or at a position slightly separated from the flange 1410. Air flowing in through air inlet port 1425 flows through air flow passage 1423 of central tube 1420 .

[0051] At least a portion of the central tube 1420 is inserted into the shroud 1430. The central tube 1420 is inserted into the shroud 1430 except for the flange 1410. At this time, the portion where the air inlet port 1425 is formed is not inserted into the shroud 1430, and the air inlet port 1425 is disposed in front of the shroud 1430.

[0052] Air inlets 1451 and 1432 are formed at the front end of the shroud 1430. Air flows in from the air inlets 1451 and 1432. A bell mouth 1431 is formed at the front end of the shroud 1430 to guide the inflow of air and reduce flow resistance. The shroud 1430 surrounds the central tube 1420 and is disposed at a distance from the central tube 1420. As a result, a space is formed between the shroud 1430 and the central tube 1420. In the space, the air flowing in from the air inlets 1451 and 1432 and the separately injected fuel flow together. Therefore, the space is called a mixing flow passage 1433.

[0053] A fuel port 1428 is formed in the central tube 1420. The fuel port 1428 is configured to inject fuel into the mixing flow passage 1433. Fuel flows in from the flange 1410 side, and the fuel port 1428 can communicate with the flange 1410 side. A fuel plenum 1427 filled with fuel is formed in the side wall portion 1421 of the central tube 1420. The fuel plenum 1427 can extend in the circumferential direction from the side wall portion 1421 to form an annular space. The fuel plenum 1427 communicates with the flange 1410 side, and the fuel plenum 1427 can communicate with the fuel port 1428. As a result, the fuel flowing in from the flange 1410 side is injected to the outside from the fuel port 1428 via the fuel plenum 1427.

[0054] A swirler 1440 is disposed between the central tube 1420 and the shroud 1430. The swirler 1440 may be formed on the inner peripheral surface of the shroud 1430 or on the outer peripheral surface of the central tube 1420, or may be provided separately and coupled between the shroud 1430 and the central tube 1420. The swirler 1440 is configured to swirl air or air and fuel. The swirler 1440 is preferably disposed near the front end of the shroud 1430 or immediately aft of the bellmouth 1431. The fuel port 1428 is disposed in the swirler 1440. If the swirler 1440 is formed integrally with the central tube 1420, the fuel port 1428 is formed penetrating all of the central tube 1420 and the swirler 1440. If the fuel ports 1428 are located in the swirler 1440, the fuel can be injected directly into the swirling air improving air and fuel mixing and the fuel ports 1428 can be located away from the combustion chamber minimizing flashback.

[0055] A cooling channel 1450 is formed in the central tube 1420. A plurality of cooling channels 1450 are provided. The cooling channel 1450 includes an inlet 1451 and an outlet 1452. The inlet 1451 of the cooling channel 1450 communicates with the air flow path 1423, and the outlet 1452 communicates with the mixing flow path 1433. The cooling channel 1450 is formed penetrating the inside of the sidewall portion and extending rearward. That is, when viewed from a vertical cross section, the cooling channel 1450 is formed extending left and right and surrounded by the sidewall portion 1421 from above and below. The plurality of cooling channels 1450 are arranged to surround the air flow path 1423 with a part of the sidewall portion 1421 in between. At this time, the plurality of cooling channels 1450 are arranged side by side on the sidewall portion 1421. Air flows through the cooling channel 1450. Air from the air passage 1423 flows into the cooling channel 1450 and is discharged into the mixing passage 1433. In the process, the central tube 1420 is cooled.

[0056] The cooling channels 1450 are formed at the rear end 1422 of the central tube 1420. The rear end 1422 of the central tube 1420 is close to the combustion chamber and may be exposed to high heat. The rear end 1422 of the central tube 1420 may be subject to backfire and flame attachment from the combustion chamber, and even if not, is exposed to relatively high heat due to its proximity to the combustion chamber. Therefore, the cooling channels 1450 are preferably formed at the rear end 1422 of the central tube 1420.

[0057] A first annular flow passage 1453 is formed in the side wall portion 1421. The first annular flow passage 1453 is formed in an annular shape extending along the circumferential direction of the central tube 1420 inside the side wall portion 1421. That is, in the first annular flow passage 1453, the side wall portion 1421 has a double-wall structure, and the side wall portion 1421 is disposed between the first annular flow passage 1453 and the air flow passage 1423, and the side wall portion 1421 is disposed between the first annular flow passage 1453 and the mixing flow passage 1433. The first annular flow passage 1453 communicates with all of the cooling channels 1450. The air flowing in the cooling channels 1450 flows into the first annular flow passage 1453. The first annular flow passage 1453 is formed between the inlet 1451 and the outlet 1452 of the cooling channel 1450. In this case, air flowing into the inlet 1451 flows into the first annular flow passage 1453, circulates in the circumferential direction in the side wall portion 1421, and is then discharged again to each of the outlets 1452. By forming the first annular flow passage 1453 in the side wall portion 1421, the air flow can be uniformly formed in the multiple cooling channels 1450.

[0058] An air swirler 1460 is disposed in the air passage 1423. The air swirler 1460 is a component for swirling the air flow in the air passage 1423 of the central tube 1420. The air swirler 1460 may include a plurality of swirling vanes (not shown). The air flow that passes through the air swirler 1460 swirls, and the swirled air flow can be brought into close contact with the inner circumferential surface of the side wall portion 1421 of the central tube 1420 by centrifugal force. This can further improve the cooling performance of the central tube 1420.

[0059] The air swirler 1460 is disposed away from the rear end 1422 of the central tube 1420. If the air swirler 1460 is located at the end of the rear end 1422 of the central tube 1420, there is almost no swirling air flow inside the central tube 1420, and therefore, the cooling performance may be reduced. Therefore, it is preferable that the air swirler 1460 is disposed away from the rear end 1422 of the central tube 1420.

[0060] However, if the air swirler 1460 is too far away from the rear end 1422 of the central tube 1420, the cooling performance of the air swirler 1460 may decrease. The swirled air gradually becomes more rectilinear as the flow progresses, and therefore, if the air swirler 1460 is too far away, the swirling air flow hardly reaches the rear end 1422 of the central tube 1420, and the cooling performance may decrease. Therefore, it is preferable to arrange the air swirler 1460 near the rear end 1422 of the central tube 1420.

[0061] However, even in this case, if the air swirler 1460 is positioned forward of the inlet 1451 of the cooling channel 1450, air may not flow smoothly into the cooling channel 1450, so it is preferable that the air swirler 1460 be positioned rearward of the inlet 1451 of the cooling channel 1450.

[0062] FIG. 6 is an enlarged view of a cooling channel of a nozzle module according to a second embodiment of the present invention.

[0063] Hereinafter, a combustor nozzle 1220 according to a second embodiment of the present invention will be described in detail with reference to Fig. 6. The combustor nozzle 1220 according to the second embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention, except for an air swirler 1460 and a turbulence forming member 1470, and therefore a duplicated description will be omitted.

[0064] In the combustor nozzle 1220 according to the second embodiment of the present invention, the air swirler 1460 can be replaced with a turbulence forming member 1470. The turbulence forming member 1470 is a component for forming turbulence in the air flow in the air passage of the central tube 1420. The turbulence forming member 1470 is formed in the shape of a protrusion on the inner circumferential surface of the side wall portion 1421, and may be composed of a plurality of protrusions. When the air passes through the turbulence forming member 1470, turbulence is formed in the air flow, and thus the flow rate of the air supplied to the inner circumferential surface of the side wall portion 1421 can be increased. This can further improve the cooling performance of the central tube 1420.

[0065] The turbulence forming member 1470 is disposed at a distance from the rear end 1422 of the central tube 1420. If the turbulence forming member 1470 is located at the end of the rear end 1422 of the central tube 1420, the turbulent flow of air is hardly formed inside the central tube 1420, and the cooling performance may be deteriorated. Therefore, it is preferable that the turbulence forming member 1470 is disposed at a distance from the rear end 1422 of the central tube 1420.

[0066] However, if the turbulence forming member 1470 is too far away from the rear end 1422 of the central tube 1420, the cooling performance of the turbulence forming member 1470 may be reduced. The air flow formed as a turbulent flow may gradually change to a laminar flow as the flow progresses. Therefore, if the turbulence forming member 1470 is too far away from the rear end 1422 of the central tube 1420, laminar air flow flows at the rear end 1422 of the central tube 1420, and the cooling performance may be reduced. Therefore, it is preferable to arrange the turbulence forming member 1470 near the rear end 1422 of the central tube 1420.

[0067] However, even in this case, if the turbulence forming member 1470 is positioned forward of the inlet 1451 of the cooling channel 1450, air may not flow smoothly into the cooling channel 1450, so it is preferable that the turbulence forming member 1470 be positioned rearward of the inlet 1451 of the cooling channel 1450.

[0068] FIG. 7 shows an enlarged view of a cooling channel of a nozzle module according to a third embodiment of the present invention.

[0069] Hereinafter, a combustor nozzle 1220 according to a third embodiment of the present invention will be described in detail with reference to Fig. 7. The combustor nozzle 1220 according to the third embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention except for the cooling channel 1450, and therefore, a duplicated description will be omitted.

[0070] In the combustor nozzle 1220 according to the third embodiment of the present invention, a plurality of cooling channels 1450 are formed in a spiral shape. The plurality of cooling channels 1450 are formed in a spiral shape from an inlet 1451 to an outlet 1452 inside a side wall portion 1421 of a central tube 1420. That is, the plurality of cooling channels 1450 are formed in a multiple spiral shape.

[0071] In this case, the cooling channel 1450 is formed extending from the side wall portion 1421 along the circumferential direction and the axial direction of the side wall portion 1421. The cooling channel 1450 having a spiral structure has an advantage that the air used for cooling flows more uniformly in the side wall portion 1421, so that the cooling performance of the central tube 1420 can be further improved.

[0072] FIG. 8 is an enlarged view showing a cooling channel of a nozzle module according to a fourth embodiment of the present invention, and FIG. 9 is a view showing a modification of FIG.

[0073] Hereinafter, a combustor nozzle 1220 according to a fourth embodiment of the present invention will be described in detail with reference to Figures 8 and 9. The combustor nozzle 1220 according to the fourth embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention except for the extension portion 1426, and therefore, a duplicated description will be omitted.

[0074] The combustor nozzle 1220 according to the fourth embodiment of the present invention further includes an expansion portion 1426. The expansion portion 1426 is formed at a rear end 1422 of the central tube 1420, and the expansion portion 1426 is formed at an opening hole 1424 of the central tube 1420. The expansion portion 1426 is a portion in which a flow cross-sectional area increases toward the rear or from upstream to downstream. When the expansion portion 1426 is formed at the opening hole 1424 located at the rear end of the central tube 1420, air can expand in a radial direction while being discharged from the central tube 1420, and the cooling performance of the central tube 1420 can be further improved.

[0075] When the extension portion 1426 is formed in the central tube 1420, the outlet 1452 of the cooling channel 1450 is formed to be inclined from the periphery of the extension portion 1426 along the axial and radial directions of the central tube 1420. Specifically, the outlet 1452 of the cooling channel 1450 is formed to extend parallel to the cross section of the extension portion 1426 in accordance with the shape of the expanded flow path of the extension portion 1426. In this case, the air discharged from the cooling channel 1450 extends not only in the axial direction but also in the radial direction, thereby further improving the cooling performance.

[0076] When the expansion portion 1426 is formed in the central tube 1420, a second annular flow passage 1454 is formed around the expansion portion 1426. The second annular flow passage 1454 is a flow passage that is connected in an annular shape from the side wall portion 1421 of the central tube 1420 along the circumferential direction. The cross section of the second annular flow passage 1454 is formed corresponding to the cross section of the expansion portion 1426. As a result, the portion of the side wall portion 1421 where the second annular flow passage 1454 is formed is formed into a double-wall structure. The second annular flow passage 1454 is connected to all of the outlets 1452 of the multiple cooling channels 1450. As a result, all of the air discharged from the outlets 1452 of the cooling channels 1450 flows into the second annular flow passage 1454, circulates, and is then discharged to the outside from the rear end portion 1422 of the central tube 1420. By forming the second annular flow passage 1454, the flow of air discharged from the cooling channel 1450 can be made more uniform, which is advantageous in that higher cooling performance in the central tube 1420 can be expected.

[0077] Although one embodiment of the present invention has been described above, a person having ordinary knowledge in the technical field can modify and change the present invention in various ways by adding, changing, deleting or adding components within the scope of the concept of the present invention described in the claims, and this is also included in the scope of the present invention. [Explanation of symbols]

[0078] 1000: Gas turbine 1100: Compressor 1200: Combustor 1210: Combustor casing 1220: Nozzle 1230: Combustion chamber 1240: Duct assembly 1300: Turbine 1310:Rotor disc 1400: Nozzle module 1410: Flange 1420: Central tube 1421: Side wall 1422: Rear end 1423: Air passage 1424: Opening hole 1425: Air inlet port 1426: Extension 1427: Fuel plenum 1428: Fuel port 1430: Shroud 1431: Bellmouth 1432: Air inlet 1433:Mixing channel 1440: Swara 1450: Cooling channel 1451: Cooling channel inlet 1452: Cooling channel outlet 1453: First annular channel 1454: Second annular channel 1460: Air Swirl 1470: Turbulence forming member

Claims

1. a central tube having an air passage formed therein through which air moves from the front to the rear and an opening hole formed at a rear end thereof; a shroud into which at least a portion of the central tube is inserted, forming a mixing passage between the central tube and the shroud, and an air inlet is formed at a front end of the shroud; a nozzle module including a plurality of cooling channels formed through an interior of a sidewall of the central tube, the cooling channels extending aft from an inlet communicating with the air passage to an outlet communicating with the mixing passage; The air flow path includes: An air swirler is provided to swirl the air flow, The air swirler is a nozzle for the combustor spaced apart from the aft end of the center tube;

2. The cooling channel comprises: The combustor nozzle of claim 1 , wherein the outlet is formed at the aft end of the center tube.

3. The inside of the side wall of the central tube is The nozzle for a combustor as recited in claim 1 , further comprising a first annular passage communicating all of said plurality of cooling channels.

4. The first annular flow path is The nozzle for a combustor as recited in claim 3 , disposed between the inlet and the outlet of the cooling channel.

5. The air swirler is The nozzle for a combustor as recited in claim 1 , disposed aft of the inlet of the cooling channel.

6. a central tube having an air passage formed therein through which air moves from the front to the rear and an opening hole formed at a rear end thereof; a shroud into which at least a portion of the central tube is inserted, forming a mixing passage between the central tube and the shroud, and an air inlet is formed at a front end of the shroud; a nozzle module including a plurality of cooling channels formed through an interior of a sidewall of the central tube, the cooling channels extending aft from an inlet communicating with the air passage to an outlet communicating with the mixing passage; The air flow path includes: A combustor nozzle, comprising a turbulence forming member disposed therein for forming turbulence in the flow of the air.

7. The turbulence creating member is The combustor nozzle of claim 6 , spaced apart from an aft end of the center tube.

8. The turbulence creating member is The nozzle for a combustor as recited in claim 6 , disposed aft of the inlet of the cooling channel.

9. The plurality of cooling channels include The combustor nozzle of claim 1 , wherein the nozzles are positioned side by side within the sidewall of the center tube.

10. The plurality of cooling channels include The combustor nozzle of claim 1 , wherein the nozzle is helically disposed within the sidewall of the center tube.

11. The opening hole of the central tube has:

2. The nozzle for a combustor according to claim 1, further comprising an expansion section having an increasing flow cross-sectional area toward the rear.

12. The outlet of the cooling channel is The combustor nozzle of claim 11 , wherein the extension is formed at the aft end of the center tube and is angled axially and radially from a periphery of the extension.

13. The rear end of the central tube and the periphery of the extension are The nozzle for a combustor as recited in claim 11 , further comprising a second annular passage defined therein, the second annular passage having one end in communication with all of the outlets of the cooling channels and an opposite end in communication with the mixing passage.

14. 14. A combustor comprising: a combustor nozzle according to any one of claims 1 to 13; and a duct assembly coupled to one side of the combustor nozzle, in which fuel and air are combusted and which transmits combusted gases to a turbine.

15. A gas turbine including a compressor that compresses air flowing in from the outside, a combustor that mixes the compressed air compressed by the compressor with fuel and burns the mixture, and a turbine including a plurality of turbine blades that are rotated by combustion gas combusted in the combustor, The combustor includes: a combustor nozzle according to any one of claims 1 to 13; and a duct assembly coupled to one side of the combustor nozzle, in which the compressed air and fuel are combusted, and which transmits the combusted combustion gas to the turbine. Gas turbine.

Images