Injection nozzle and combustion device

Abstract

An injection nozzle 100 comprises: an inner wall 101 that has a cylindrical shape; a first outer wall 102 that has a cylindrical shape and is formed as integrated with the inner wall 101 via a connection portion 107; a fuel passage 108 that has an annular shape and is formed between the inner wall 101 and the first outer wall 102; and an inner-side air passage 104 that is formed on the inner side of the inner wall 101.

Description

[Technical Field]

[0001] This application claims the benefit of priority from Japanese Patent Application No. 2022-17901, filed on February 8, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] Gas turbine systems are used to generate power by burning fuel in a combustor. For example, as disclosed in Patent Document 1, some gas turbine systems use a fuel injection nozzle that premixes fuel and air and injects the premixed mixture into the combustor. Premixing the fuel with sufficient air and performing lean combustion suppresses NOx emissions. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Patent No. 5472863 Summary of the Invention [Problem to be solved by the invention]

[0004] In the fuel injection nozzle described in Patent Document 1, the fuel passage through which fuel flows and the air passage through which air flows are formed by assembling multiple members. However, for example, when a fuel passage is formed by assembling multiple members, the fuel may flow unevenly within the fuel passage due to machining accuracy, assembly errors, etc., which may deteriorate combustibility within the combustor.

[0005] An object of the present disclosure is to provide an injection nozzle and a combustion device that can improve combustibility. [Means for solving the problem]

[0006] In order to solve the above problems, the injection nozzle of the present disclosure includes a cylindrical inner wall, a cylindrical outer wall integrally formed with the inner wall via a connecting portion, an annular fuel passage formed between the inner wall and the outer wall, an inner air passage formed inside the inner wall, and a swirler formed integrally with the inner wall and disposed in the inner air passage at an angle relative to the circumferential direction of the inner wall; a shaft portion disposed on the central axis of the inner air passage and formed integrally with the swirler; a distributor formed inside the shaft portion; and a fuel communication passage formed inside the swirler, communicating the distributor with the fuel passage. Equipped with. An injection nozzle according to another aspect of the present disclosure includes a cylindrical inner wall, a cylindrical outer wall integrally formed with the inner wall via a connecting portion, an annular fuel passage formed between the inner wall and the outer wall, an inner air passage formed inside the inner wall, an air supply passage connected to the inner air passage and extending in a tangential direction of the inner air passage, and a fuel communication passage formed circumferentially spaced from the air supply passage and communicating with the fuel passage.

[0007] The fuel passage may include a swirl portion that is integrally formed with at least one of the inner wall and the outer wall and is disposed inclined relative to the circumferential direction of the inner wall and the outer wall.

[0011] In order to solve the above problem, the combustion device of the present disclosure includes the above injection nozzle. [Effects of the Invention]

[0012] According to the present disclosure, flammability can be improved. [Brief explanation of the drawings]

[0013] [Figure 1] FIG. 1 is a schematic diagram showing the configuration of a gas turbine system according to this embodiment. [Figure 2] FIG. 2 is a schematic cross-sectional view showing the configuration of the injection nozzle according to this embodiment. [Figure 3] FIG. 3 is a schematic cross-sectional view showing the configuration of an injection nozzle according to a first modified example. [Figure 4] FIG. 4 is a schematic cross-sectional view showing the configuration of an injection nozzle according to a second modified example. [Figure 5] FIG. 5 is a schematic cross-sectional view of a plurality of air supply paths. DETAILED DESCRIPTION OF THE INVENTION

[0014] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. Dimensions, materials, and other specific numerical values ​​shown in the embodiments are merely examples for ease of understanding and, unless otherwise specified, do not limit the present disclosure. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to avoid redundant explanation, and elements not directly related to the present disclosure are not shown.

[0015] Fig. 1 is a schematic diagram showing the configuration of a gas turbine system 1 according to this embodiment. As shown in Fig. 1, the gas turbine system 1 includes a turbocharger 11, a generator 12, a combustor 13, an injection nozzle mechanism 14, a fuel tank 15, and a flow control valve 16.

[0016] Of the gas turbine system 1, the combustor 13, the injection nozzle mechanism 14, the fuel tank 15, and the flow control valve 16 are included in the combustion device 10.

[0017] The turbocharger 11 has a compressor 11a and a turbine 11b. The compressor 11a and the turbine 11b rotate as a unit. The compressor 11a and the turbine 11b are connected by a shaft.

[0018] The compressor 11a is provided in an intake air flow path 21 connected to the combustor 13. Air to be supplied to the combustor 13 flows through the intake air flow path 21. An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake air flow path 21. The air taken in through the intake port passes through the compressor 11a and is sent to the combustor 13. The compressor 11a compresses the air and discharges it downstream.

[0019] The turbine 11b is provided in an exhaust flow path 22 connected to the combustor 13. Exhaust gas discharged from the combustor 13 flows through the exhaust flow path 22. An exhaust port (not shown) through which the exhaust gas is discharged to the outside is provided at the downstream end of the exhaust flow path 22. The exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b is rotated by the exhaust gas to generate rotational power.

[0020] The generator 12 is connected to the turbocharger 11. The generator 12 generates electricity using the rotational power generated by the turbocharger 11.

[0021] The combustor 13 has a casing 13a, a liner 13b, and a combustion chamber 13c. The casing 13a has a generally cylindrical shape. The liner 13b is provided inside the casing 13a. The liner 13b also has a generally cylindrical shape. The liner 13b is arranged coaxially with the casing 13a. The combustion chamber 13c is formed inside the liner 13b. In other words, the internal space of the liner 13b corresponds to the combustion chamber 13c. The combustion chamber 13c is a generally cylindrical space. An exhaust flow path 22 is connected to the combustion chamber 13c.

[0022] As will be described later, fuel and air are supplied to the combustion chamber 13c. A mixture of fuel and air is combusted in the combustion chamber 13c. Exhaust gas generated by the combustion in the combustion chamber 13c is discharged to the exhaust passage 22. A space S is formed between the inner surface of the casing 13a and the outer surface of the liner 13b. An intake passage 21 is connected to the space S. Air is sent from the compressor 11a to the space S via the intake passage 21. An opening is formed at the end of the liner 13b on the side where air is sent from the compressor 11a (the left end in FIG. 1). A plate P is provided near the opening at the end of the liner 13b.

[0023] The plate P is provided with an injection nozzle mechanism 14. The plate P holds the injection nozzle mechanism 14. An opening is formed in the center of the plate P. The mixture of fuel and air injected from the injection nozzle mechanism 14 is introduced into the combustion chamber 13c through the opening in the plate P. The injection nozzle mechanism 14 has an injection nozzle 100 and a fuel supply pipe 150.

[0024] Fig. 2 is a schematic cross-sectional view showing the configuration of the injection nozzle 100 according to this embodiment. As shown in Fig. 2, the injection nozzle 100 includes an inner wall 101, a first outer wall 102, a second outer wall 103, an inner air passage 104, a shaft portion 105, an inner swirler vane 106, a connection portion 107, a fuel passage 108, a resistance portion 109, a swirler portion 110, an outer air passage 111, and an outer swirler vane 112.

[0025] The inner wall 101, the first outer wall 102, and the second outer wall 103 are formed in a cylindrical shape. However, without being limited thereto, the inner wall 101, the first outer wall 102, and the second outer wall 103 may be formed in, for example, a truncated cone shape. Furthermore, the inner wall 101, the first outer wall 102, and the second outer wall 103 may have an inclined shape in which a portion of the cylinder is inclined toward or away from the central axis. In this way, the inner wall 101, the first outer wall 102, and the second outer wall 103 may have an inclined shape in which at least a portion of the cylinder is inclined along the central axis direction. The inner wall 101, the first outer wall 102, and the second outer wall 103 are radially spaced apart from each other. The inner wall 101 is disposed radially inward of the first outer wall 102 and the second outer wall 103. The first outer wall 102 is disposed between the inner wall 101 and the second outer wall 103, and is disposed radially outward from the inner wall 101 and radially inward from the second outer wall 103. The second outer wall 103 is disposed radially outward from the inner wall 101 and the first outer wall 102. The second outer wall 103 is connected to a plate P (see FIG. 1).

[0026] The inner air passage 104 is formed by the inner circumferential surface of the inner wall 101. An air inlet 104a is formed at one end of the inner air passage 104, and an air outlet 104b is formed at the other end. The air inlet 104a is in communication with a space S (see FIG. 1) to which air is sent from the compressor 11a. In the inner air passage 104, air flows from the air inlet 104a toward the air outlet 104b. A shaft 105 and inner swirler vanes 106 are provided in the inner air passage 104.

[0027] The shaft portion 105 is formed in a substantially cylindrical shape. The shaft portion 105 is arranged on the central axis of the inner air passage 104. A plurality of inner swirler vanes 106 are provided on the outer peripheral surface of the shaft portion 105, spaced apart in the circumferential direction. The plurality of inner swirler vanes 106 are arranged at equal intervals in the circumferential direction of the shaft portion 105. The inner swirler vanes 106 are connected to the outer peripheral surface of the shaft portion 105 and the inner peripheral surface of the inner wall 101. The inner swirler vanes 106 are arranged in the inner air passage 104 at an angle with respect to the circumferential direction of the inner wall 101 and the shaft portion 105. The inner swirler vanes 106 swirl air in a clockwise or counterclockwise direction about the central axis of the inner air passage 104.

[0028] The connecting portion 107 connects the inner wall 101 and the first outer wall 102. The connecting portion 107 is provided on the side of the inner wall 101 that includes the air inlet 104a, and connects the inner wall 101 and the first outer wall 102.

[0029] The fuel passage 108 is formed between the inner wall 101 and the first outer wall 102. The fuel passage 108 is formed in an annular shape. One end of the fuel passage 108 is connected to a fuel communication passage 108a over a portion of the circumferential direction, and the other end is formed with a fuel discharge port 108b. In the fuel passage 108, fuel flows from the fuel communication passage 108a toward the fuel discharge port 108b. A resistance portion 109 and a swirling portion 110 are provided in the fuel passage 108.

[0030] The resistance portion 109 is provided upstream of the swirl portion 110. However, without being limited thereto, the resistance portion 109 may be provided downstream of the swirl portion 110. The resistance portion 109 is, for example, a protrusion formed around the entire outer circumferential surface of the inner wall 101 and protruding radially from the outer circumferential surface of the inner wall 101 toward the inner circumferential surface of the first outer wall 102. A gap through which fuel can flow is formed between the resistance portion 109 and the inner circumferential surface of the first outer wall 102. The resistance portion 109 makes it possible to uniform the flow rate of fuel flowing through the fuel passage 108 in the circumferential direction.

[0031] However, without being limited thereto, the resistance portion 109 may be a protrusion formed around the entire circumference of the inner circumferential surface of the first outer wall 102 and protruding radially from the inner circumferential surface of the first outer wall 102 toward the outer circumferential surface of the inner wall 101. Alternatively, a pair of resistance portions 109 may be formed around the entire circumference of the outer circumferential surface of the inner wall 101 and the inner circumferential surface of the first outer wall 102. The pair of resistance portions 109 are, for example, protrusions arranged at positions facing each other in the radial direction and protruding toward each other. In this way, the resistance portion 109 is a protrusion formed on at least one of the inner wall 101 and the first outer wall 102 and reduces the flow path cross-sectional area of ​​the fuel passage 108. Note that the resistance portion 109 is not limited to a protrusion, and may be, for example, a slit formed on at least one of the outer circumferential surface of the inner wall 101 and the inner circumferential surface of the first outer wall 102. A plurality of slits may be formed spaced apart from each other in the circumferential direction. Moreover, the resistance portion 109 may be a hole such as an orifice provided between the inner wall 101 and the first outer wall 102. A plurality of holes may be formed spaced apart from each other in the circumferential direction.

[0032] The swirl portion 110 is formed, for example, on the inner wall 101, and at least a portion of it is disposed so as to be inclined with respect to the circumferential direction of the inner wall 101. By swirl portion 110 being inclined, it is possible to swirl the fuel in a clockwise or counterclockwise direction about the central axis of the inner air passage 104. However, without being limited thereto, the swirl portion 110 may be formed on the first outer wall 102, or on both the inner wall 101 and the first outer wall 102. In other words, the swirl portion 110 may be formed on at least one of the inner wall 101 and the first outer wall 102, and may be disposed in the fuel passage 108 so as to be inclined with respect to the circumferential direction of the inner wall 101 and the first outer wall 102.

[0033] The outer air passage 111 is formed between the inner circumferential surface of the second outer wall 103 and the outer circumferential surface of the first outer wall 102. The outer air passage 111 has a circular ring shape. An air inlet 111a is formed at one end of the outer air passage 111, and an ejection port 111b is formed at the other end. The air inlet 111a is in communication with a space S to which air is sent from the compressor 11a. In the outer air passage 111, air flows from the air inlet 111a toward the ejection port 111b. An outer swirler vane 112 is provided in the outer air passage 111.

[0034] A plurality of outer swirler vanes 112 are provided on the outer peripheral surface of the first outer wall 102, spaced apart in the circumferential direction. The plurality of outer swirler vanes 112 are arranged at equal intervals in the circumferential direction of the first outer wall 102. The outer swirler vanes 112 are connected to the outer peripheral surface of the first outer wall 102 and the inner peripheral surface of the second outer wall 103. The outer swirler vanes 112 swirl air in a clockwise or counterclockwise direction about the central axis of the outer air passage 111.

[0035] One end of the fuel supply pipe 150 is connected to the connecting portion 107 and the outer peripheral surface of the first outer wall 102, and the other end is connected to a flow path 24 (see FIG. 1) described below. The fuel supply pipe 150 supplies fuel from the flow path 24 to the injection nozzle 100. A fuel supply path 160 is formed inside the fuel supply pipe 150. The fuel supply path 160 is connected to the fuel path 108 via a fuel communication path 108a.

[0036] Returning to FIG. 1 , fuel is stored in fuel tank 15. The fuel is, for example, natural gas or hydrogen. Note that the hydrogen in fuel tank 15 may be liquid or gas. Fuel tank 15 is connected to flow control valve 16 via flow path 23. Flow control valve 16 is connected to fuel supply pipe 150 via flow path 24. The fuel stored in fuel tank 15 is supplied to fuel supply pipe 150 via flow path 23, flow control valve 16, and flow path 24. Flow control valve 16 controls (i.e., adjusts) the flow rate of fuel supplied from fuel tank 15 to fuel supply pipe 150. The amount of fuel supplied from fuel tank 15 to fuel supply pipe 150 is adjusted by adjusting the opening of flow control valve 16.

[0037] Returning to Figure 2, the fuel communication passage 108a is connected to the fuel supply path 160 of the fuel supply pipe 150. Fuel is supplied from the fuel supply pipe 150 to the fuel passage 108 via the fuel communication passage 108a. When the fuel supplied to the fuel passage 108 is injected from the fuel discharge port 108b, it merges with and is mixed with the air that has flowed through the inner air passage 104.

[0038] Here, the air flowing through the inner air passage 104 is swirled by the inner swirler 106, and the fuel flowing through the fuel passage 108 is swirled by the swirler 110. When the swirling air and fuel meet, the fuel is atomized by shear force, promoting mixing of the air and fuel. In this embodiment, the swirling direction of the air imparted by the inner swirler 106 and the swirling direction of the fuel imparted by the swirler 110 are the same. However, the present disclosure is not limited to this, and the swirling direction of the air imparted by the inner swirler 106 and the swirling direction of the fuel imparted by the swirler 110 may be opposite to each other.

[0039] The mixture of air and fuel is discharged from the mixture injection port 102a of the first outer wall 102 and flows into the outer air passage 111 of the second outer wall 103. The mixture discharged from the mixture injection port 102a meets and is mixed with the air that has flowed through the outer air passage 111.

[0040] Here, the air flowing through the outer air passage 111 is swirled by the outer swirler vanes 112. When the swirling air and the air-fuel mixture join together, the fuel is atomized by shear force, and the mixing of the air and the air-fuel mixture is promoted. In this embodiment, the swirling direction of the air imparted by the outer swirler vanes 112 and the direction of the inner swirler vanes 106 the swirl direction of the air imparted by The swirl directions of the fuel imparted by the swirler 110 are the same. However, the present disclosure is not limited to this, and the swirl direction of the air imparted by the outer swirler 112 and the swirl direction of the air imparted by the inner swirler 106, or the swirl direction of the fuel imparted by the swirler 110, may be opposite to each other. The air-fuel mixture mixed inside the second outer wall 103 is injected into the combustion chamber 13c from the injection port 111b.

[0041] However, when the inner wall, outer wall, connecting portion, and other components that make up the injection nozzle are made of separate members and the injection nozzle is constructed by assembling these members, the fuel may flow unevenly within the fuel passage or the fuel may leak from gaps between multiple members due to machining accuracy, assembly errors, etc. If the fuel flows unevenly within the fuel passage, the combustibility within the combustor may deteriorate.

[0042] Therefore, in this embodiment, the components that make up the injection nozzle 100 are integrally formed. Specifically, the inner wall 101, the first outer wall 102, the second outer wall 103, the shaft portion 105, the inner swirler vanes 106, the connection portion 107, the resistance portion 109, the swirling portion 110, and the outer swirler vanes 112 are integrally formed by three-dimensional additive manufacturing technology.

[0043] By integrally forming each part of the injection nozzle 100 using 3D additive manufacturing technology, it is possible to prevent the fuel from flowing unevenly within the fuel passage or the fuel from leaking from the gaps between multiple parts due to processing accuracy, assembly errors, etc.

[0044] Specifically, because the inner wall 101 and the first outer wall 102 are integrally formed, any gap between them can be eliminated, preventing fuel leakage. Furthermore, because no processing or assembly is required, the radial width of the fuel passage 108 can be made uniform over the entire circumference. In other words, eccentricity between the central axis of the cylindrical inner wall 101 and the central axis of the cylindrical first outer wall 102, which is caused by assembly, can be reduced. As a result, the flow rate of fuel in the circumferential direction of the fuel passage 108 can be made uniform, improving combustibility within the combustion chamber 13c.

[0045] Furthermore, by forming resistance portion 109 integrally with inner wall 101 and first outer wall 102, the influence of machining accuracy and assembly error is eliminated, and the fuel flow rate flowing through fuel passage 108 can be made uniform in the circumferential direction. Furthermore, by forming swirl portion 110 integrally with inner wall 101 and first outer wall 102, the influence of machining accuracy and assembly error is eliminated, and the swirling flow of fuel can be made uniform in the circumferential direction. Similarly, by forming inner swirler vane 106 integrally with inner wall 101 and outer swirler vane 112 integrally with first outer wall 102, the influence of machining accuracy and assembly error is eliminated, and the swirling flow of air can be made uniform in the circumferential direction.

[0046] Figure 3 is a schematic cross-sectional view showing the configuration of an injection nozzle 200 according to a first modified example. Components that are substantially the same as those in the injection nozzle 100 of the above embodiment are given the same reference numerals and descriptions thereof will be omitted. As shown in Figure 3, the injection nozzle 200 according to the first modified example differs from the above embodiment in that a fuel communication passage 208a is formed in the inner swirler vane 106 and a distributor 210 is formed in the shaft portion 105.

[0047] In the first modified example, the inner wall 101, the first outer wall 102, the second outer wall 103, the shaft portion 105, the inner swirler vanes 106, the connection portion 107, the resistance portion 109, the swirl portion 110, and the outer swirler vanes 112 are integrally formed using three-dimensional additive manufacturing technology. At this time, the fuel communication passage 208a and the distribution portion 210 are formed in the inner swirler vanes 106 and the shaft portion 105, respectively.

[0048] The distribution section 210 is an internal space formed inside the shaft section 105 and to which fuel is supplied. The fuel supply pipe 150 is connected to the shaft section 105. The fuel supply path 160 of the fuel supply pipe 150 is connected to the distribution section 210. The distribution section 210 is in communication with the fuel supply path 160. A plurality of fuel communication paths 208a are connected to the distribution section 210. Each fuel communication path 208a has the same shape and size. One fuel communication path 208a is formed inside one inner swirler vane 106. One end of each fuel communication path 208a is connected to the distribution section 210 and the other end is connected to the fuel path 108.

[0049] The fuel that passes through the fuel supply passage 160 of the fuel supply pipe 150 is supplied to the distribution unit 210. The distribution unit 210 distributes the fuel supplied from the fuel supply passage 160 evenly to each fuel communication passage 208a. The fuel communication passage 208a supplies the fuel distributed by the distribution unit 210 to the fuel passage 108. Because the multiple inner swirler vanes 106 are arranged at equal intervals in the circumferential direction of the shaft portion 105, the multiple fuel communication passages 208a can supply fuel evenly around the entire circumference of the fuel passage 108.

[0050] According to the first modified example, the fuel communication passage 208a is formed inside the inner swirler vane 106, so the injection nozzle 200 can be made more compact than in the above embodiment. Also, the fuel supply pipe 150 is connected to the shaft portion 105, and is not connected to the outer peripheral surface of the first outer wall 102, so that, for example, the obstruction of air flow into the outer air passage 111 by the fuel supply pipe 150 can be reduced.

[0051] FIG. 4 is a schematic cross-sectional view showing the configuration of an injection nozzle 300 according to a second modified example. Components substantially identical to those in the injection nozzle 100 of the above embodiment are denoted by the same reference numerals, and a description thereof will be omitted. As shown in FIG. 4, the injection nozzle 300 according to the second modified example differs from the above embodiment in that it includes multiple air supply passages 310 instead of the inner swirler vanes 106. Hereinafter, the configuration that imparts swirl to air using the inner swirler vanes 106 will also be referred to as an axial swirler, and the configuration that imparts swirl to air using the air supply passages 310 (described later) will also be referred to as a tangential swirler. The injection nozzle 300 also differs from the above embodiment in that a distribution section 320 and multiple fuel communication passages 308a are formed within the connection section 107.

[0052] In the second modified example, the inner wall 101, the first outer wall 102, the second outer wall 103, the shaft portion 105, the connection portion 107, the resistance portion 109, the swirling portion 110, and the outer swirler vanes 112 are integrally formed by three-dimensional additive manufacturing technology. At this time, a plurality of air supply passages 310, a plurality of fuel communication passages 308a, and a distribution portion 320 are formed within the connection portion 107.

[0053] Fig. 5 is a schematic cross-sectional view of a plurality of air supply channels 310. As shown in Fig. 5, a plurality of air supply channels 310 that are connected to the inner air passage 104 and are spaced apart from one another in the circumferential direction are formed in the connection portion 107. In the second modified example, four air supply channels 310 are provided at equal intervals in the circumferential direction of the inner air passage 104. However, this is not limited thereto, and the plurality of air supply channels 310 may be provided at unequal intervals in the circumferential direction of the inner air passage 104. Furthermore, the number of air supply channels 310 may be one, two, three, five or more.

[0054] One end of the air supply passage 310 is connected to the outer edge of the inner air passage 104, and the other end opens to the connecting portion 107 or the outer peripheral surface of the first outer wall 102. The air supply passage 310 communicates with the space S (see FIG. 1) to which air is sent from the compressor 11a. The air supply passage 310 extends in a tangential direction to the outer periphery of the inner air passage 104. This makes it possible to impart swirl to the air supplied to the inner air passage 104 even if the inner swirler vane 106 is not provided. Note that, with reference to FIG. 4, an injection nozzle 300 according to a second modified example may be provided with a plurality of air supply passages similar to the above-described air supply passage 310, instead of the outer swirler vane 112.

[0055] The distribution section 320 is an internal space formed within the connection section 107 and to which fuel is supplied. The fuel supply pipe 150 is connected to the connection section 107. The fuel supply path 160 of the fuel supply pipe 150 is connected to the distribution section 320. The distribution section 320 is in communication with the fuel supply path 160. A plurality of fuel communication paths 308a are connected to the distribution section 320. The plurality of fuel communication paths 308a are formed within the connection section 107 and are spaced apart from one another in the circumferential direction of the inner air passage 104, as shown in FIG. 5 . The plurality of fuel communication paths 308a are formed, for example, at equal intervals in the circumferential direction of the inner air passage 104. However, this is not limited thereto, and the plurality of fuel communication paths 308a may be formed at unequal intervals in the circumferential direction of the inner air passage 104. Each of the fuel communication paths 308a has the same shape and size.

[0056] Each fuel communication passage 308a has one end connected to the distribution section 320 and the other end connected to the fuel passage 108. 320 5, the fuel communication passage 308a is formed in the connecting portion 107 and is spaced apart from the air supply passage 310 in the circumferential direction. Therefore, the fuel communication passage 308a does not communicate with the air supply passage 310, and it is possible to prevent the fuel flowing through the fuel communication passage 308a from leaking into the air supply passage 310.

[0057] The fuel that has passed through the fuel supply passage 160 of the fuel supply pipe 150 is supplied to the distribution section 320. The distribution section 320 distributes the fuel supplied from the fuel supply passage 160 evenly to each fuel communication passage 308a. The fuel communication passage 308a supplies the fuel distributed by the distribution section 320 to the fuel passage 108. Because the multiple fuel communication passages 308a are arranged at equal intervals in the circumferential direction of the inner air passage 104, the multiple fuel communication passages 308a can supply fuel evenly around the entire circumference of the fuel passage 108.

[0058] According to the second modification, by providing a plurality of air supply paths 310 extending in the tangential direction of the inner air passage 104, it is possible to increase the swirl angle of the swirling air flow compared to when the inner swirler vanes 106 are provided as in the above embodiment and the first modification. This is because, in three-dimensional additive manufacturing, there is a limit to the inclination angle of the inner swirler vanes 106 with respect to the central axis direction of the shaft portion 105 in the above embodiment, and it is difficult to increase the inclination angle of the inner swirler vanes 106 by more than a predetermined angle. In the second modification, the air supply paths 310 extending in the tangential direction of the inner air passage 104 are provided in the direction of the central axis of the shaft portion 105. Orthogonal direction and Since they are formed in parallel, the swirl angle of the swirling air flow in the inner air passage 104 can be made larger than in the above embodiment.

[0059] Furthermore, since the fuel supply pipe 150 is not connected to the outer peripheral surface of the first outer wall 102, it is possible to reduce the obstruction of air flow into the outer air passage 111 caused by the fuel supply pipe 150, for example.

[0060] Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear that a person skilled in the art can conceive of various modifications and alterations within the scope of the claims, and it is understood that such modifications and alterations also fall within the technical scope of the present disclosure.

[0061] In the above, an example has been described in which the rotational power generated by the turbocharger 11 in the gas turbine system 1 is used as energy to drive the generator 12. However, the present invention is not limited to this, and for example, the combustion device 10 in the gas turbine system 1 may be applied to a combustion device such as a jet engine or an industrial furnace. Furthermore, in the gas turbine system 1, the rotational power generated by the turbocharger 11 may be used for other purposes (for example, to drive a moving body such as a ship).

[0062] In the above embodiment, first modified example, and second modified example, examples have been described in which the resistance portion 109 and the swirl portion 110 are provided in the fuel passage 108. However, the resistance portion 109 and the swirl portion 110 are not essential components, and the resistance portion 109 and the swirl portion 110 do not necessarily have to be provided in the fuel passage 108.

[0063] In the above embodiment, an example has been described in which the shaft portion 105 and the inner swirler vanes 106 are provided in the inner air passage 104. However, in the above embodiment, the shaft portion 105 and the inner swirler vanes 106 are not essential components, and the shaft portion 105 and the inner swirler vanes 106 do not necessarily have to be provided in the inner air passage 104.

[0064] In the above embodiment, first modified example, and second modified example, examples have been described in which the outer swirler vanes 112 are provided in the outer air passage 111. However, the outer swirler vanes 112 are not an essential component, and the outer swirler vanes 112 do not necessarily have to be provided in the outer air passage 111. [Explanation of symbols]

[0065] 1 Gas turbine system 10 Combustion equipment 100 spray nozzles 101 Interior wall 102 1st outer wall 103 Second outer wall 104 Inner air passage 105 Shaft 106 Inner Swirl Wing 107 Connection 108 Fuel passage 108a Fuel communication passage 109 Resistance section 110 Swivel section 111 outer air passage 112 Outer Swirl Wing 200 spray nozzles 208a Fuel communication passage 210 Distribution section 300 spray nozzle 308a Fuel communication passage 310 Air supply line 320 Distribution section

Claims

1. A cylindrical inner wall, a cylindrical outer wall integrally formed with the inner wall via a connecting portion; an annular fuel passage formed between the inner wall and the outer wall; an inner air passage formed inside the inner wall; swirler vanes formed integrally with the inner wall and disposed in the inner air passage at an angle relative to the circumferential direction of the inner wall; a shaft portion disposed on a central axis of the inner air passage and integrally formed with the swirler; a distributor formed inside the shaft; a fuel communication passage formed inside the swirler and communicating the distribution section with the fuel passage; An injection nozzle comprising:

2. A cylindrical inner wall, a cylindrical outer wall integrally formed with the inner wall via a connecting portion; an annular fuel passage formed between the inner wall and the outer wall; an inner air passage formed inside the inner wall; an air supply passage connected to the inner air passage and extending tangentially to the inner air passage; a fuel communication passage formed circumferentially spaced from the air supply passage and communicating with the fuel passage; An injection nozzle comprising:

3. a swirl portion formed integrally with at least one of the inner wall and the outer wall, the swirl portion being inclined with respect to the circumferential direction of the inner wall and the outer wall and disposed in the fuel passage; 3. An injection nozzle according to claim 1 or 2, comprising:

4. The injection nozzle according to claim 1 or 2. A combustion device comprising:

5. The injection nozzle according to claim 3 A combustion device comprising:

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