WO2023153042A1 - Injection nozzle and combustion device - Google Patents

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

Injection nozzle and combustion device

The present disclosure relates to injection nozzles and combustion devices. This application claims the benefit of priority based on Japanese Patent Application No. 2022-17901 filed on February 8, 2022, the content of which is incorporated herein by reference.

A gas turbine system that obtains power by burning fuel in a combustor is used. As a gas turbine system, for example, as disclosed in Patent Document 1, there is a system that uses a fuel injection nozzle that premixes fuel and air and injects them into a combustor. NOx emissions are reduced by premixing the fuel with sufficient air for lean combustion.

Japanese Patent No. 5472863

In the fuel injection nozzle described in Patent Document 1, a fuel passage for circulating fuel and an air passage for circulating air are formed by assembling a plurality of members. However, for example, when a fuel passage is formed by assembling a plurality of members, the fuel may flow unevenly in the fuel passage due to processing accuracy or assembly error, resulting in deterioration of combustibility in the combustor. be.

An object of the present disclosure is to provide an injection nozzle and a combustion device capable of improving combustibility.

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, and an annular ring formed between the inner wall and the outer wall. and an inner air passage formed inside the inner wall.

At least one of the inner wall and the outer wall may be integrally formed with a swirl portion arranged in the fuel passage so as to be inclined with respect to the circumferential direction of the inner wall and the outer wall.

A swirl vane may be integrally formed with the inner wall and arranged in the inner air passage so as to be inclined with respect to the circumferential direction of the inner wall.

A shaft portion disposed on the central axis of the inner air passage and integrally formed with the swirl blade, a distribution portion formed inside the shaft portion, and a distribution portion formed inside the swirl blade and communicating with the fuel passage. and a fuel communication passage.

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 separately from the air supply passage in a circumferential direction and communicating with the fuel passage. .

In order to solve the above problems, the combustion device of the present disclosure includes the above injection nozzle.

According to the present disclosure, combustibility can be improved.

FIG. 1 is a schematic diagram showing the configuration of a gas turbine system according to this embodiment. FIG. 2 is a schematic cross-sectional view showing the configuration of the injection nozzle according to this embodiment. FIG. 3 is a schematic cross-sectional view showing the configuration of an injection nozzle according to a first modified example. FIG. 4 is a schematic cross-sectional view showing the configuration of an injection nozzle according to a second modification. FIG. 5 is a schematic cross-sectional view of a plurality of air supply channels.

Embodiments of the present disclosure will be described below with reference to the accompanying drawings. Dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for facilitating understanding, and do not limit the present disclosure unless otherwise specified. In the present specification and drawings, elements having substantially the same function and configuration are given the same reference numerals to omit redundant description, and elements that are not directly related to the present disclosure are omitted from the drawings. do.

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 supercharger 11 , a generator 12 , a combustor 13 , an injection nozzle mechanism 14 , a fuel tank 15 and a flow control valve 16 .

In 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.

The supercharger 11 has a compressor 11a and a turbine 11b. Compressor 11a and turbine 11b rotate as a unit. Compressor 11a and turbine 11b are connected by a shaft.

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

The turbine 11 b 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 passage 22 . Exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b generates rotational power by being rotated by the exhaust gas.

The generator 12 is connected to the turbocharger 11. The generator 12 generates power using the rotational power generated by the supercharger 11 .

The combustor 13 has a casing 13a, a liner 13b, and a combustion chamber 13c. The casing 13a has a substantially cylindrical shape. A liner 13b is provided inside the casing 13a. The liner 13b has a substantially cylindrical shape. The liner 13b is arranged coaxially with the casing 13a. A combustion chamber 13c is formed inside the liner 13b. That is, the internal space of the liner 13b corresponds to the combustion chamber 13c. The combustion chamber 13c is a substantially cylindrical space. An exhaust passage 22 is connected to the combustion chamber 13c.

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 combustion in the combustion chamber 13 c 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 to the space S from the compressor 11 a through the intake passage 21 . An opening is formed at the end of the liner 13b to which air is sent from the compressor 11a (left end in FIG. 1). A plate P is provided near the opening at the end of the liner 13b.

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

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 swirl vane 106, a connecting portion 107, a fuel passage 108, and a resistance portion 109. , a swirl section 110 , an outer air passage 111 and an outer swirler 112 .

The inner wall 101, the first outer wall 102, and the second outer wall 103 are formed in a cylindrical shape. However, the shape is not limited to this, and the inner wall 101, the first outer wall 102, and the second outer wall 103 may be formed in a truncated cone shape, for example. In addition, the inner wall 101, the first outer wall 102, and the second outer wall 103 may have a slanted shape in which a part of the cylinder is slanted toward or away from the central axis. Thus, 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 part 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 separated from each other. The inner wall 101 is arranged radially inward of the first outer wall 102 and the second outer wall 103 . The first outer wall 102 is arranged between the inner wall 101 and the second outer wall 103 , radially outside the inner wall 101 and radially inside the second outer wall 103 . The second outer wall 103 is arranged radially outside the inner wall 101 and the first outer wall 102 . The second outer wall 103 is connected to the plate P (see FIG. 1).

The inner air passage 104 is formed by the inner peripheral 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 communicates with the 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 portion 105 and an inner swirl vane 106 are provided in the inner air passage 104 .

The shaft portion 105 is formed in a substantially cylindrical shape. Axial portion 105 is arranged on the central axis of inner air passage 104 . A plurality of inner swirl vanes 106 are provided on the outer peripheral surface of the shaft portion 105 so as to be spaced apart in the circumferential direction. The plurality of inner swirl vanes 106 are arranged at regular intervals in the circumferential direction of the shaft portion 105 . The inner swirl vane 106 is connected to the outer peripheral surface of the shaft portion 105 and the inner peripheral surface of the inner wall 101 . The inner swirl vane 106 is arranged in the inner air passage 104 so as to be inclined with respect to the circumferential direction of the inner wall 101 and the shaft portion 105 . The inner swirl vane 106 swirls the air clockwise or counterclockwise around the central axis of the inner air passage 104 .

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 including the air inlet 104 a and connects the inner wall 101 and the first outer wall 102 .

A fuel passage 108 is formed between the inner wall 101 and the first outer wall 102 . Fuel passage 108 is formed in an annular shape. A fuel communication passage 108a is connected to one end of the fuel passage 108 in the circumferential direction, and a fuel discharge port 108b is formed at the other end. 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 turning portion 110 are provided in the fuel passage 108 .

The resistance section 109 is provided upstream of the turning section 110 . However, the present invention is not limited to this, and the resistance portion 109 may be provided downstream of the turning portion 110 . The resistance portion 109 is, for example, a protrusion that is formed along the entire circumference of the outer peripheral surface of the inner wall 101 and protrudes radially from the outer peripheral surface of the inner wall 101 toward the inner peripheral surface of the first outer wall 102 . Between the resistance portion 109 and the inner peripheral surface of the first outer wall 102, a gap is formed through which fuel can flow. The resistance portion 109 can uniformize the flow rate of the fuel flowing through the fuel passage 108 in the circumferential direction.

However, the present invention is not limited to this, and the resistance portion 109 is formed along the entire circumference of the inner peripheral surface of the first outer wall 102 and radially extends from the inner peripheral surface of the first outer wall 102 toward the outer peripheral surface of the inner wall 101 . It may be a protruding protrusion. Also, a pair of resistance portions 109 may be formed along the entire circumference of the outer peripheral surface of the inner wall 101 and the inner peripheral surface of the first outer wall 102 . The pair of resistance portions 109 are, for example, protrusions that are disposed at positions facing each other in the radial direction and protrude in a direction toward each other. As described above, the resistance portion 109 is a projection that is formed on at least one of the inner wall 101 and the first outer wall 102 and that reduces the 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 in at least one of the outer peripheral surface of the inner wall 101 and the inner peripheral surface of the first outer wall 102 . A plurality of slits may be formed so as to be spaced apart from each other in the circumferential direction. Alternatively, the resistance portion 109 may be an orifice-like hole provided between the inner wall 101 and the first outer wall 102 . A plurality of holes may be formed so as to be spaced apart from each other in the circumferential direction.

The turning part 110 is formed, for example, on the inner wall 101, and at least a part thereof is inclined with respect to the circumferential direction of the inner wall 101. The inclination of the swirl portion 110 allows the fuel to swirl clockwise or counterclockwise about the central axis of the inner air passage 104 . However, the present invention is not limited to this, and the turning portion 110 may be formed on the first outer wall 102 or may be formed on both the inner wall 101 and the first outer wall 102 . That is, swirling portion 110 may be formed on at least one of inner wall 101 and first outer wall 102 and arranged in fuel passage 108 so as to be inclined with respect to the circumferential direction of inner wall 101 and first outer wall 102 .

The outer air passage 111 is formed between the inner peripheral surface of the second outer wall 103 and the outer peripheral surface of the first outer wall 102 . The outer air passage 111 has an annular shape. An air inlet 111a is formed at one end of the outer air passage 111, and an injection port 111b is formed at the other end. The air inlet 111a communicates 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 injection port 111b. An outer swirl vane 112 is provided in the outer air passage 111 .

A plurality of outer swirl vanes 112 are provided on the outer peripheral surface of the first outer wall 102 and are spaced apart from each other in the circumferential direction. The plurality of outer swirl vanes 112 are arranged at regular intervals in the circumferential direction of the first outer wall 102 . The outer swirl vane 112 is 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 swirl vane 112 swirls the air clockwise or counterclockwise around the central axis of the outer air passage 111 .

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 the flow path 24 (see FIG. 1) described later. A fuel supply pipe 150 supplies fuel from the flow path 24 to the injection nozzle 100 . A fuel supply path 160 is formed in the fuel supply pipe 150 . The fuel supply passage 160 communicates with the fuel passage 108 via the fuel communication passage 108a.

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

Returning to FIG. 2, the fuel supply passage 160 of the fuel supply pipe 150 is connected to the fuel communication passage 108a. Fuel is supplied from the fuel supply pipe 150 to the fuel passage 108 through the fuel communication passage 108a. The fuel supplied to the fuel passage 108 joins and mixes with the air flowing through the inner air passage 104 when injected from the fuel discharge port 108b.

Here, the air flowing through the inner air passage 104 is swirled by the inner swirl vane 106 and the fuel flowing through the fuel passage 108 is swirled by the swirling section 110 . When the swirling air and fuel join, the shear force atomizes the fuel and promotes mixing of the air and fuel. In this embodiment, the swirling direction of the air imparted by the inner swirl vane 106 and the swirling direction of the fuel imparted by the swirling section 110 are the same. However, the present disclosure is not limited to this, and the swirling direction of the air imparted by the inner swirl vanes 106 and the swirling direction of the fuel imparted by the swirling section 110 may be opposite to each other.

A mixture of air and fuel is discharged from the mixture injection port 102 a of the first outer wall 102 and flows into the outer air passage 111 of the second outer wall 103 . The air-fuel mixture discharged from the air-fuel mixture injection port 102a joins and mixes with the air flowing through the outer air passage 111 .

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

By the way, when the inner wall, the outer wall, the connection part, etc. that constitute the injection nozzle are made of separate members, and the injection nozzle is constructed by assembling these members, the fuel may flow unevenly in the fuel passage due to processing accuracy, assembly error, etc. or the fuel may leak through gaps between multiple members. If the fuel flows unevenly through the fuel passage, combustibility in the combustor may deteriorate.

Therefore, in the present embodiment, each part constituting the injection nozzle 100 is integrally formed. Specifically, the inner wall 101, the first outer wall 102, the second outer wall 103, the shaft portion 105, the inner swirl blade 106, the connection portion 107, the resistance portion 109, the swirl portion 110, and the outer swirl blade 112 are integrated by a three-dimensional layered manufacturing technique. forming.

By integrally forming each part that constitutes the injection nozzle 100 by three-dimensional layered manufacturing technology, the fuel flows unevenly in the fuel passage due to processing accuracy, assembly error, etc., and the fuel leaks through the gaps between multiple members. Leakage can be suppressed.

Specifically, since the inner wall 101 and the first outer wall 102 are integrally formed, a gap between them can be eliminated, and fuel leakage can be prevented. In addition, since processing and assembly are not required, the radial width of the fuel passage 108 can be made uniform over the entire circumference. That is, the eccentricity between the central axis of the cylindrical inner wall 101 and the central axis of the cylindrical first outer wall 102 due to 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, and the combustibility within the combustion chamber 13c can be improved.

In addition, since the resistance portion 109 is integrally formed with the inner wall 101 and the first outer wall 102, the effects of processing accuracy and assembly error are eliminated, and the flow rate of fuel flowing through the fuel passage 108 can be made uniform over the circumferential direction. can be done. Further, since the swirl portion 110 is integrally formed with the inner wall 101 and the first outer wall 102, the effects of machining accuracy and assembly errors are eliminated, and the swirling flow of fuel can be made uniform in the circumferential direction. Similarly, the inner swirl vane 106 is integrally formed with the inner wall 101 and the outer swirl vane 112 is integrally formed with the first outer wall 102, thereby eliminating the effects of machining accuracy and assembly errors and allowing the swirl flow of air to circulate. It can be uniform across all directions.

FIG. 3 is a schematic cross-sectional view showing the configuration of the injection nozzle 200 according to the first modified example. Constituent elements that are substantially the same as those of the injection nozzle 100 of the above-described embodiment are denoted by the same reference numerals, and descriptions thereof are omitted. As shown in FIG. 3, the injection nozzle 200 according to the first modification differs from the above-described embodiment in that the fuel communication passage 208a is formed in the inner swirl vane 106 and the distribution portion 210 is formed in the shaft portion 105. different.

In the first modification, the inner wall 101, the first outer wall 102, the second outer wall 103, the shaft portion 105, the inner swirl blade 106, the connection portion 107, the resistance portion 109, the swirl portion 110, and the outer swirl blade 112 are formed by three-dimensional layered manufacturing technology. It is integrally formed by At this time, the fuel communication passage 208a and the distribution portion 210 are formed in the inner swirl vane 106 and the shaft portion 105, respectively.

The distribution section 210 is an internal space formed inside the shaft section 105 and supplied with fuel. A fuel supply pipe 150 is connected to the shaft portion 105 . A fuel supply path 160 of a fuel supply pipe 150 is connected to the distribution portion 210 . Distribution unit 210 communicates with fuel supply path 160 . A plurality of fuel communication passages 208 a are connected to the distribution portion 210 . Each fuel communication passage 208a has the same shape and size. One fuel communication passage 208 a is formed inside one inner swirl vane 106 . Each fuel communication passage 208 a has one end connected to the distribution portion 210 and the other end connected to the fuel passage 108 .

The fuel that has passed through the fuel supply path 160 of the fuel supply pipe 150 is supplied to the distribution section 210 . The distribution unit 210 evenly distributes the fuel supplied from the fuel supply path 160 to each fuel communication path 208a. The fuel communication passage 208 a supplies the fuel distributed by the distribution section 210 to the fuel passage 108 . Since the plurality of inner swirl vanes 106 are arranged at regular intervals in the circumferential direction of the shaft portion 105 , the plurality of fuel communication passages 208 a can evenly supply fuel over the entire circumference of the fuel passage 108 .

According to the first modification, since the fuel communication passage 208a is formed inside the inner swirl vane 106, the injection nozzle 200 can be made more compact than in the above embodiment. Further, since 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, for example, the fuel supply pipe 150 can reduce the obstruction of the air flowing into the outer air passage 111. can.

FIG. 4 is a schematic cross-sectional view showing the configuration of an injection nozzle 300 according to a second modified example. Constituent elements that are substantially the same as those of the injection nozzle 100 of the above-described embodiment are denoted by the same reference numerals, and descriptions thereof are omitted. As shown in FIG. 4 , the injection nozzle 300 according to the second modification differs from the above embodiment in that it includes a plurality of air supply passages 310 instead of the inner swirler 106 . Hereinafter, the configuration in which the inner swirl vane 106 imparts swirl to the air is also referred to as an axial swirler, and the configuration in which the air supply path 310 to be described later imparts swirl to the air is also referred to as a tangential swirler. Further, the injection nozzle 300 differs from the above-described embodiment in that a distribution portion 320 and a plurality of fuel communication passages 308a are formed in the connection portion 107. As shown in FIG.

In the second modification, 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 swirl portion 110, and the outer swirl vane 112 are integrally formed by a three-dimensional layered manufacturing technique. there is At this time, a plurality of air supply passages 310, a plurality of fuel communication passages 308a, and a distribution portion 320 are formed in the connecting portion 107. As shown in FIG.

FIG. 5 is a schematic cross-sectional view of a plurality of air supply paths 310. FIG. As shown in FIG. 5, the connection portion 107 is formed with a plurality of air supply passages 310 connected to the inner air passage 104 and spaced from each other in the circumferential direction. In the second modification, four air supply passages 310 are provided at regular intervals in the circumferential direction of the inner air passage 104 . However, the invention is not limited to this, and the plurality of air supply paths 310 may be provided at uneven intervals in the circumferential direction of the inner air passage 104 . Also, the number of air supply paths 310 may be one, two, three, or five or more.

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 connection portion 107 or the outer peripheral surface of the first outer wall 102 . The air supply path 310 communicates with the space S (see FIG. 1) to which air is sent from the compressor 11a. The air supply passage 310 extends tangentially to the outer circumference of the inner air passage 104 . As a result, the air supplied to the inner air passage 104 can be swirled even if the inner swirl vane 106 is not provided. Note that, referring to FIG. 4 , the injection nozzle 300 according to the second modification may include air supply paths similar to the plurality of air supply paths 310 described above instead of the outer swirler 112 .

The distribution section 320 is an internal space formed within the connection section 107 and supplied with fuel. A fuel supply pipe 150 is connected to the connection portion 107 . A fuel supply path 160 of a fuel supply pipe 150 is connected to the distribution portion 320 . Distributor 320 communicates with fuel supply path 160 . A plurality of fuel communication passages 308 a are connected to the distribution portion 320 . A plurality of fuel communication passages 308a are formed in the connection portion 107 and are formed apart from each other in the circumferential direction of the inner air passage 104 as shown in FIG. The plurality of fuel communication passages 308a are formed at regular intervals in the circumferential direction of the inner air passage 104, for example. However, the invention is not limited to this, and the plurality of fuel communication passages 308a may be formed at uneven intervals in the circumferential direction of the inner air passage 104 . Each fuel communication passage 308a has the same shape and size.

Each fuel communication passage 308 a has one end connected to the distribution portion 320 and the other end connected to the fuel passage 108 . Each fuel communication passage 308 a extends from distribution portion 210 toward fuel passage 108 along the central axis direction of inner wall 101 and first outer wall 102 . As shown in FIG. 5, the fuel communication path 308a is formed in the connecting portion 107 so as to be separated from the air supply path 310 in the circumferential direction. Therefore, the fuel communication path 308 a does not communicate with the air supply path 310 , so that the fuel flowing through the fuel communication path 308 a can be prevented from leaking into the air supply path 310 .

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

According to the second modification, by providing a plurality of air supply passages 310 extending tangentially to the inner air passage 104, compared to the case of including the inner swirl vane 106 as in the above embodiment and the first modification, , the swirl angle of the air swirl flow can be increased. This is because, in three-dimensional additive manufacturing, there is a limit to the inclination angle of the inner swirl vane 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 swirl vane 106 by a predetermined angle or more. It's for. In the second modification, the air supply passage 310 extending in the tangential direction of the inner air passage 104 is formed parallel to the central axis direction of the shaft portion 105. The swirling angle of the swirling flow of air can be increased.

In addition, 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, for example, the fuel supply pipe 150 from hindering air from flowing into the outer air passage 111.

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 or modifications within the scope of the claims, and it is understood that these also belong to the technical scope of the present disclosure. be done.

An example in which the rotational power generated by the turbocharger 11 is used as energy for driving the generator 12 in the gas turbine system 1 has been described above. However, it is not limited to this, and for example, the combustion device 10 in the gas turbine system 1 may be applied to combustion devices such as jet engines and industrial furnaces. Further, in the gas turbine system 1, the rotational power generated by the turbocharger 11 may be used for other purposes (for example, for the purpose of driving a mobile object such as a ship).

In the above embodiment, the first modified example, and the second modified example, the example in which the resistance portion 109 and the turning portion 110 are provided in the fuel passage 108 has been described. However, the resistance portion 109 and the turning portion 110 are not essential components, and the resistance portion 109 and the turning portion 110 may not be provided in the fuel passage 108 .

In the above embodiment, an example in which the shaft portion 105 and the inner swirl vanes 106 are provided in the inner air passage 104 has been described. However, in the above-described embodiment, the shaft portion 105 and the inner swirl vane 106 are not essential components, and the shaft portion 105 and the inner swirl vane 106 may not be provided in the inner air passage 104 .

In the above embodiment, the first modified example, and the second modified example, the example in which the outer swirl vane 112 is provided in the outer air passage 111 has been described. However, the outer swirl vane 112 is not an essential component, and the outer swirl vane 112 may not be provided in the outer air passage 111 .

1 gas turbine system 10 combustion device 100 injection nozzle 101 inner wall 102 first outer wall 103 second outer wall 104 inner air passage 105 shaft portion 106 inner swirl vane 107 connection portion 108 fuel passage 108a fuel communication passage 109 resistance portion 110 swirl portion 111 outer air Passage 112 Outer swirl vane 200 Injection nozzle 208a Fuel communication passage 210 Distributor 300 Injection nozzle 308a Fuel communication passage 310 Air supply passage 320 Distributor

Claims (9)

1. a cylindrical inner wall;
   a cylindrical outer wall integrally formed via the inner wall and 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 injection nozzle comprising a
2. 2. The injection nozzle according to claim 1, further comprising: a swirling portion integrally formed with at least one of said inner wall and said outer wall and arranged in said fuel passage so as to be inclined with respect to the circumferential direction of said inner wall and said outer wall.
3. 3. The injection nozzle according to claim 1, further comprising a swirl vane integrally formed with the inner wall and arranged in the inner air passage so as to be inclined with respect to the circumferential direction of the inner wall.
4. a shaft part disposed on the central axis of the inner air passage and integrally formed with the swirl vane;
   a distribution portion formed inside the shaft;
   a fuel communication passage formed inside the swirl vane and communicating between the distribution portion and the fuel passage;
   4. The injection nozzle of claim 3, comprising:
5. an air supply passage connected to the inner air passage and extending tangentially to the inner air passage;
   a fuel communication passage formed circumferentially apart from the air supply passage and communicating with the fuel passage;
   3. An injection nozzle according to claim 1 or 2, comprising:
6. A combustion device comprising an injection nozzle according to claim 1 or 2.
7. A combustion device comprising an injection nozzle according to claim 3.
8. A combustion device comprising an injection nozzle according to claim 4.
9. A combustion device comprising an injection nozzle according to claim 5.

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