Fuel supply pipe assembly, gas turbine combustor, and gas turbine

Abstract

A fuel supply pipe assembly according to at least one embodiment of the present disclosure comprises: an inlet part for fuel; an outlet part for fuel; and a fuel supply pipe connecting the inlet part and the outlet part. The fuel supply pipe includes a first pipe region and a second pipe region extending in the circumferential direction of a combustion cylinder, a first connection pipe region provided between the inlet part and the first pipe region, a second connection pipe region provided between the outlet part and the second pipe region, and a third connection pipe region provided between the first pipe region and the second pipe region. The third connection pipe region is formed so as to be directed to one side in the circumferential direction from the first pipe region toward the third connection pipe region on the upstream side and is formed so as to be directed toward the other side in the circumferential direction from the third connection pipe region toward the second pipe region on the downstream side.

Description

Fuel supply pipe assembly, gas turbine combustor, and gas turbine

[0001] This application claims priority to Japanese Patent Application No. 2024-047415, filed with the Japan Patent Office on March 25, 2024, the contents of which are incorporated herein by reference.

[0002] A gas turbine combustor is known in which fuel can be supplied into a combustion liner from a fuel nozzle provided on a side of the combustion liner of the gas turbine combustor. In such a gas turbine combustor, a fuel supply pipe for supplying fuel to the fuel nozzle extends along the axial direction of the combustion liner (see, for example, Patent Document 1).

[0003] US Patent Application Publication No. 2010 / 0018210

[0004] As described above, since the fuel supply pipe extends along the axial direction of the combustion liner, thermal stress occurs due to the difference in thermal expansion between the fuel supply pipe and the combustion liner in the axial direction. Therefore, in the fuel supply pipe described in Patent Document 1, a region that extends in the circumferential direction of the combustion liner is provided midway along the fuel supply pipe, and the difference in thermal expansion between the fuel supply pipe and the combustion liner in the axial direction is absorbed by the deflection of that region.

[0005] However, in the fuel supply pipe described in Patent Document 1, in order to efficiently absorb the difference in thermal expansion between the combustion liner and the fuel supply pipe in the axial direction, the length of the region extending in the circumferential direction needs to be long, which results in a relatively large difference in the circumferential positions of the inlet and outlet sides of the fuel supply pipe. Therefore, if the difference in the circumferential positions of the inlet and outlet sides of the fuel supply pipe is relatively small, the difference in the thermal expansion between the combustion liner and the fuel supply pipe in the axial direction cannot be sufficiently absorbed, and the thermal stress generated in the fuel supply pipe increases.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure has an object to reduce thermal stress generated in a fuel supply pipe that supplies fuel to a fuel nozzle provided on a side of a combustion liner of a gas turbine combustor.

[0007] (1) A fuel supply pipe assembly according to at least one embodiment of the present disclosure is a fuel supply pipe assembly disposed in a cabin for supplying fuel to a side fuel nozzle provided on a side of a combustion liner of a gas turbine combustor, the fuel supply pipe assembly comprising: an inlet portion connected to a supply source of the fuel; an outlet portion constituting a part of a fuel manifold for supplying the fuel to the side fuel nozzle; and a fuel supply pipe connecting the inlet portion and the outlet portion, wherein the fuel supply pipe includes: a first piping region extending in a circumferential direction of the combustion liner along an outer surface of the combustion liner; a second piping region extending in the circumferential direction along the outer surface and spaced apart from the first piping region in the axial direction of the combustion liner; a first connecting pipe region provided between the inlet portion and the first piping region; a second connecting pipe region provided between the outlet portion and the second piping region; and a third connecting pipe region provided between the first piping region and the second piping region. At least one of the first piping region and the second piping region extends such that its position in both the circumferential direction and the axial direction changes as it moves toward the downstream side of the fuel flow, and the third connecting pipe region is formed so as to move toward one side in the circumferential direction from the first piping region toward the third connecting pipe region on the upstream side, and is formed so as to move toward the other side in the circumferential direction from the third connecting pipe region toward the second piping region on the downstream side.

[0008] (2) A gas turbine combustor according to at least one embodiment of the present disclosure includes: a fuel supply pipe assembly having the configuration described in (1); the combustion liner; and the side fuel nozzle.

[0009] (3) A gas turbine according to at least one embodiment of the present disclosure includes: a compressor; a gas turbine combustor having the configuration described in (2); and a turbine configured to be driven by combustion gas from the gas turbine combustor.

[0010] According to at least one embodiment of the present disclosure, it is possible to reduce thermal stress occurring in a fuel supply pipe for supplying fuel to a fuel nozzle provided on the side of a combustion liner of a gas turbine combustor.

[0011] 5 is a schematic configuration diagram of a gas turbine according to an embodiment. FIG. 5 is a schematic diagram showing a combustor and an inlet portion of the turbine of the gas turbine according to an embodiment. FIG. 5 is a schematic cross-sectional view of a combustor of a gas turbine according to an embodiment. FIG. 5 is a schematic diagram showing an inlet section, a fuel supply pipe, and an outlet section according to an embodiment, developed in a circumferential direction about a central axis of a combustion liner. FIG. 5 is a schematic diagram showing an inlet section, a fuel supply pipe, and an outlet section according to another embodiment, developed in a circumferential direction about a central axis of a combustion liner. FIG. 5 is a diagram for explaining the wall thickness of the piping from the first connecting pipe region to the first piping region, and the wall thickness of the piping from a downstream region of the third connecting pipe region to the second piping region in FIG. 5. FIG. 5 is a diagram for explaining the wall thickness of the piping from the second piping region to the second connecting pipe region, and the wall thickness of the piping from the first piping region to an upstream region of the third connecting pipe region in FIG.

[0012] Several embodiments of the present disclosure will be described below with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are not intended to limit the scope of the present disclosure and are merely illustrative examples. For example, expressions expressing relative or absolute arrangements, such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial," not only strictly express such arrangements, but also express relative displacements with a tolerance or angle or distance to the extent that the same function is achieved. For example, expressions expressing the equality of things, such as "same," "equal," and "homogeneous," not only express strict equality, but also express tolerance or differences to the extent that the same function is achieved. For example, expressions expressing shapes such as a square or cylindrical shape not only express shapes such as a square or cylindrical shape in the strict geometric sense, but also express shapes including concave and convex portions, chamfered portions, etc., to the extent that the same effect is achieved. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0013] First, a gas turbine, which is an example of an application of a fuel supply pipe assembly according to an embodiment, will be described with reference to Fig. 1. Fig. 1 is a schematic configuration diagram of a gas turbine according to an embodiment. As shown in Fig. 1, the gas turbine 1 includes a compressor 2 for generating compressed air, a gas turbine combustor (combustor) 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas. In the case of a gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6.

[0014] The compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, thereby becoming high-temperature, high-pressure compressed air.

[0015] The combustors 4 are supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustors 4 to generate combustion gas, which is a working fluid for the turbine 6. As shown in Figure 1, the gas turbine 1 has a plurality of combustors 4 arranged in a casing 20 along the circumferential direction around a rotor 8.

[0016] The turbine 6 has a combustion gas passage 28 formed by the turbine casing 22 and includes a plurality of stator vanes 24 and rotor blades 26 provided in the combustion gas passage 28. The stator vanes 24 and rotor blades 26 of the turbine 6 are provided downstream of the combustor 4 with respect to the flow of combustion gas. The stator vanes 24 are fixed to the turbine casing 22, and a plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The rotor blades 26 are implanted in the rotor 8, and a plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator vane rows and rotor blade rows are arranged alternately in the axial direction of the rotor 8. In the turbine 6, combustion gas from the combustor 4 flows into the combustion gas passage 28 and passes through the stator vanes 24 and rotor blades 26, thereby driving the rotor 8 to rotate about the axis O. This drives a generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas is discharged to the outside via an exhaust chamber 30.

[0017] Next, the combustor 4 according to one embodiment will be described. Fig. 2 is a schematic diagram showing the combustor 4 and an inlet portion of the turbine 6 of the gas turbine 1 according to one embodiment. Fig. 3 is a schematic cross-sectional view of the combustor 4 of the gas turbine 1 according to one embodiment.

[0018] In the gas turbine 1 according to some embodiments, each of the plurality of combustors 4 (see FIG. 1 ) arranged in the circumferential direction around the rotor 8 includes a combustion liner 36 provided in a combustor casing 32 defined by the casing 20, and a first combustion burner 38 and a plurality of second combustion burners 44 arranged to surround the first combustion burner 38, each of which is arranged in the combustion liner 36. That is, the combustion liner 36, the first combustion burner 38, and the second combustion burner 44 are housed in the casing 20.

[0019] The combustion liner (combustor liner) 36 has an inner liner 48 disposed around the first combustion burner 38 and the plurality of second combustion burners 44, and a transition piece 50 connected to the tip of the inner liner 48. The inner liner 48 and the transition piece 50 may be integrally formed.

[0020] The first combustion burner 38 is aligned with the central axis C of the combustion tube 36. １The combustor 4 has a first fuel nozzle 40 for injecting fuel and a first burner cylinder 41 disposed so as to surround the first fuel nozzle 40. Fuel is supplied to the first fuel nozzle 40 via a first fuel port 42. The first fuel port 42 is connected to an external fuel pipe (not shown) outside the combustor 4.

[0021] The second combustion burner 44 has a second fuel nozzle 46 for injecting fuel and a second burner cylinder 47 arranged to surround the second fuel nozzle 46. Fuel is supplied to the second fuel nozzle 46 via a second fuel port 43. The second fuel port 43 is connected to an external fuel pipe (not shown) outside the combustor 4.

[0022] The combustor 4 further includes an outer casing 52 provided on the outer circumferential side of the inner casing 48 inside the casing 20. An air passage 54 through which compressed air flows is formed on the outer circumferential side of the inner casing 48 and on the inner circumferential side of the outer casing 52.

[0023] Compressed air generated by the compressor 2 (see FIG. 1) is supplied into the combustor casing 32 through the casing inlet 31, and flows from the combustor casing 32 into an air passage 54 as combustion air, where it is redirected by a wall surface 53 provided along a plane perpendicular to the axial direction of the combustor 4, and flows into the first burner tube 41 and the second burner tube 47. In each burner tube, fuel injected from the fuel nozzle is mixed with the compressed air (combustion air), and this mixture flows into the combustion tube 36, where it is ignited and combusted, generating combustion gas.

[0024] The first combustion burner 38 may be a burner for generating a diffusion combustion flame, and the second combustion burner 44 may be a burner for burning a premixed air-fuel mixture to generate a premixed combustion flame. That is, in the second combustion burner 44, fuel from the second fuel port 43 is premixed with compressed air, and the premixed air-fuel mixture is mainly formed into a swirling flow by the swirler 49 and flows into the combustion liner 36. Furthermore, the compressed air and fuel injected from the first combustion burner 38 through the first fuel port 42 are mixed in the combustion liner 36, ignited by an ignition means (not shown), and combusted, generating combustion gas. At this time, a portion of the combustion gas diffuses with the flame to the surroundings, igniting and combusting the premixed air-fuel flowing into the combustion liner 36 from each second combustion burner 44. That is, the diffusion combustion flame of the fuel injected from the first combustion burner 38 can provide flame stabilization for stable combustion of the premixed air-fuel mixture (premixed fuel) from the second combustion burner 44.

[0025] The combustion gas generated by the combustion of fuel in the combustor 4 flows into the turbine 6 through an outlet 51 of the combustor 4 located at the downstream end of the transition piece 50 .

[0026] 2, the combustor 4 includes a third fuel nozzle 70 provided on the side of the combustion liner 36. That is, the third fuel nozzle 70 is a fuel nozzle for supplying fuel into the combustion liner 36 from the side of the combustion liner 36. Note that the third fuel nozzle 70 is aligned with the central axis C of the combustion liner 36. １ A plurality of third fuel nozzles 70 may be provided along the circumferential direction (i.e., the circumferential direction of the combustor 4) around the transition piece 50. The third fuel nozzles 70 are fixed to, for example, the transition piece 50. When fuel is injected from the third fuel nozzles 70 into the combustion liner 36, the injected fuel is mixed with the combustion air in the combustion liner 36 and combusted. By injecting fuel from the third fuel nozzles 70 into the combustion liner 36, the fuel can be supplied to a secondary combustion zone in a transition area downstream of the primary combustion zone where the fuel from the first fuel nozzle 40 and the second fuel nozzle 46 is combusted. This reduces nitrogen oxides (NO ｘ ) and improves combustion efficiency. In the following description, the third fuel nozzle 70 is also referred to as a side fuel nozzle.

[0027] The combustor 4 may include other components such as a bypass pipe (not shown) for bypassing the combustion gas.

[0028] The combustor 4 according to one embodiment includes a fuel supply pipe assembly 100 for supplying fuel to the third fuel nozzle 70. The fuel supply pipe assembly 100 according to one embodiment includes a fuel inlet portion 101, a fuel outlet portion 107, and a fuel supply pipe 105 connecting the inlet portion 101 and the outlet portion 107. In the fuel supply pipe assembly 100 according to one embodiment, fuel supplied from a fuel pipe 150 flows through the fuel supply pipe 105 and is supplied to the third fuel nozzle 70.

[0029] In the combustor 4 according to the embodiment, one fuel supply pipe assembly 100 is provided for one combustor 4. Note that in the combustor 4 according to the embodiment, a plurality of third fuel nozzles 70 are provided along the circumferential direction of one combustor 4, and fuel is distributed from an outlet portion 107 of one fuel supply pipe assembly 100 to the plurality of third fuel nozzles 70 via distribution pipes 108. Details of the fuel supply pipe assembly 100 will be described later.

[0030] 2 and 3 , the combustor 4 according to the embodiment includes a top hat flange 62 attached to the casing 20, and an annular first cylindrical portion 64 extending from the top hat flange 62 along the axial direction of the combustor 4. In the combustor 4 according to the embodiment, a portion including the top hat flange 62 and the first cylindrical portion 64 may be referred to as the top hat portion 60 due to its shape. The top hat portion 60 according to the embodiment is a cylindrical member with a bottom provided to close the combustor insertion hole 20h formed in the casing 20.

[0031] As shown in FIGS. 2 and 3 , the top hat flange portion 62 has a shape that protrudes radially outward from the combustor 4 and is fixed to the casing 20 by bolts 59 .

[0032] The first cylindrical portion 64 extends from the top hat flange portion 62 toward the internal space of the casing 20 along the central axis C１ The casing 1 has a cylindrical shape extending along the extension direction of the casing 1.

[0033] 2 and 3 , the air passage 54 may be at least partially defined by the first cylindrical portion 64. That is, the first cylindrical portion 64 may include an air passage forming portion 66 (outer cylinder 52) that defines the air passage 54.

[0034] As shown in FIGS. 2 and 3, the top hat part 60 according to one embodiment is provided on the outer circumferential side of the first cylindrical part 64 and has a central axis C １ The second cylindrical portion 65 is a cylindrical portion formed to cover the outer periphery of a connecting pipe 152 of the fuel pipe 150, which will be described later. As shown in FIG. 3, the second cylindrical portion 65 is oriented along the central axis C. １ The second cylindrical portion 65 has an opening 65a that opens to the surface 62a of the top hat flange 62 on one side thereof in the extending direction thereof, i.e., an outer end of the casing 20 when viewed from the inside of the casing 20. １ The third flange portion 67 is provided at the other end in the extending direction of the central axis C and can be coupled to the second flange portion 102 described later. １ The second cylindrical portion 64 is provided near an end 64a of the first cylindrical portion 64 located on the other side in the extending direction (inside the casing 20).

[0035] In the top hat part 60 according to one embodiment, the space inside the first cylindrical part 64, i.e., the space inside the casing 20, is separated from the space outside the casing 20 by a top hat flange part 62 attached to the casing 20. In the top hat part 60 according to one embodiment, the space inside the casing 20 and the space inside the second cylindrical part 65, i.e., the space outside the casing 20, are separated from each other by a third flange part 67 and a second flange part 102 (described later) coupled to the third flange part 67.

[0036] (Fuel Pipe 150) In the combustor 4 according to one embodiment, the fuel pipe 150 for supplying fuel to the fuel supply pipe 105 includes an external fuel pipe 151 outside the combustor 4 and a connecting pipe 152 that connects the external fuel pipe 151 and the fuel supply pipe 105. As shown in FIG. 3 , the connecting pipe 152 has a downstream end 152a in the fuel flow direction and a fourth flange portion 154 that can be coupled to a first flange portion 104 (described later) of the fuel supply pipe assembly 100. An upstream end 152b of the connecting pipe 152 in the fuel flow direction protrudes outside the top hat part 60 and is connected to the external fuel pipe 151. In the following description, the upstream side of the fuel pipe 150 or the fuel supply pipe assembly 100 in the fuel flow direction will also be simply referred to as the upstream side, and the downstream side of the fuel flow direction will also be simply referred to as the downstream side.

[0037] (Fuel Supply Pipe Assembly 100) As described above, the fuel supply pipe assembly 100 according to one embodiment includes the fuel inlet portion 101, the fuel outlet portion 107, and the fuel supply pipe 105 connecting the inlet portion 101 and the outlet portion 107. The inlet portion 101 is connected to the fuel pipe 150 (described later) that serves as a fuel supply source, and is configured to be fixed to the casing 20, more specifically, to the third flange portion 67 of the top hat part 60. That is, the inlet portion 101 includes a second flange portion 102 that can be coupled to the third flange portion 67 of the top hat part 60, a pipe portion 103 that protrudes from the second flange portion 102 upstream in the fuel flow direction (the upper left side in FIGS. 2 and 3 ), and a first flange portion 104 that is provided at the upstream end of the pipe portion 103 and can be coupled to the fourth flange portion 154 of the connecting pipe 152.

[0038] The outlet portion 107 is provided downstream of the fuel supply pipe 105, receives fuel from the fuel supply pipe 105, and functions as a temporary storage portion for distributing the fuel received from the fuel supply pipe 105 to the plurality of third fuel nozzles 70. The outlet portion 107 constitutes a part of the fuel manifold 109. Note that, as described above, fuel is supplied from the outlet portion 107 to the plurality of third fuel nozzles 70 via the distribution pipes 108. The fuel manifold 109 includes the outlet portion 107 and the distribution pipes 108. As shown in FIG. 2 , the outlet portion 107 is fixed to the combustion liner 36 via a bracket 107 a.

[0039] The fuel supply pipe 105 is a pipe whose upstream side is connected to the inlet portion 101 and whose downstream side is connected to the outlet portion 107. The fuel supply pipe 105 will be described in detail later.

[0040] In the combustor 4 according to the embodiment, the first flange portion 104 and the piping portion 103 are located inside the second cylindrical portion 65, i.e., in a space outside the casing 20. In the combustor 4 according to the embodiment, the inlet portion 101, the fuel supply pipe 105, and the outlet portion 107 are located in a space inside the casing 20, i.e., in a combustor casing 32 defined by the casing 20.

[0041] In the combustor 4 having the fuel supply pipe assembly 100 configured in this manner, fuel supplied from an external fuel pipe 151 outside the combustor 4 is supplied to the inlet portion 101 of the fuel supply pipe assembly 100 via a connecting pipe 152. The fuel supplied to the inlet portion 101 flows through the fuel supply pipe 105 and the outlet portion 107, and is supplied to the plurality of third fuel nozzles 70 via a distribution pipe 108.

[0042] (Regarding the fuel supply pipe 105) FIG. 4 shows the inlet portion 101, the fuel supply pipe 105, and the outlet portion 107 according to one embodiment, with respect to the central axis C of the combustion liner 36. １ 5 is a schematic diagram of an inlet portion 101, a fuel supply pipe 105, and an outlet portion 107 according to another embodiment, which are developed in the circumferential direction around the central axis C of the combustion liner 36. １ In the following description, the central axis C of the combustion liner 36 is １The circumferential direction centered on the central axis C of the combustion liner 36 is also referred to simply as the circumferential direction. １ The radial direction centered on the central axis C of the combustion liner 36 is also referred to simply as the radial direction. １ When referring to the axial direction, the upstream side of the flow of combustion gas flowing inside the combustion liner 36 is referred to as the axial upstream side, and the downstream side of the flow of combustion gas flowing inside the combustion liner 36 is referred to as the axial downstream side.

[0043] 4 and 5 , the fuel supply pipe 105 according to some embodiments includes a first piping region 111, a second piping region 112, a first connecting pipe region 121, a second connecting pipe region 122, and a third connecting pipe region 123. The first piping region 111 is a region of the fuel supply pipe 105 that extends circumferentially along the outer surface of the combustion liner 36. The second piping region 112 is a region of the fuel supply pipe 105 that extends circumferentially along the outer surface of the combustion liner 36 and is separated from the first piping region 111 in the axial direction of the combustion liner 36. The first connecting pipe region 121 is a region of the fuel supply pipe 105 that is provided between the inlet portion 101 and the first piping region 111. The second connecting pipe region 122 is a region of the fuel supply pipe 105 that is provided between the outlet portion 107 and the second piping region 112. The third connecting pipe region 123 is a region of the fuel supply pipe 105 that is provided between the first piping region 111 and the second piping region 112. That is, in the fuel supply pipe 105 according to some embodiments, the following regions are arranged in order from the upstream side in the fuel flow direction: the first connecting pipe region 121, the first piping region 111, the third connecting pipe region 123, the second piping region 112, and the second connecting pipe region 122. That is, in the fuel supply pipe 105 according to some embodiments, the above-mentioned regions are also arranged in the same order from the axial upstream side. In FIGS. 4 and 5 , the fuel flow direction is indicated by arrow F.

[0044] The first connecting pipe region 121 is formed in a shape like a bent pipe or elbow configured so that the direction of the flow of fuel flowing axially downstream is directed to one side in the circumferential direction, for example.

[0045] The second connecting pipe region 122 is formed in a shape similar to a bent pipe or elbow, configured so that the direction of the flow of fuel flowing toward the axial downstream side and the other circumferential side is not in the circumferential direction but toward the axial downstream side.

[0046] In the fuel supply pipe 105 according to some embodiments, the third connecting pipe region 123 is formed so as to extend from the first piping region 111 toward one side in the circumferential direction on the upstream side toward the third connecting pipe region 123, and so as to extend from the third connecting pipe region 123 toward the second piping region 112 on the downstream side toward the other side in the circumferential direction. That is, the third connecting pipe region 123 is configured to redirect the circumferential direction of the fuel that has flowed into the third connecting pipe region 123 from one side in the circumferential direction to the other side. For ease of explanation, in FIGS. 4 and 5 , the lower side of the paper surface will be referred to as the one side in the circumferential direction, and the upper side of the paper surface will be referred to as the other side in the circumferential direction.

[0047] In the fuel supply pipe 105 shown in Fig. 5, the third connecting pipe region 123 includes, in order from the upstream side, an upstream region 123U, a midstream region 123M, and a downstream region 123D. In the fuel supply pipe 105 shown in Fig. 5, the upstream region 123U and the downstream region 123D have larger outer diameters than the midstream region 123M. Note that the outer diameter of the third connecting pipe region 123 may be uniform throughout its entire region.

[0048] In some embodiments, the fuel supply pipe 105 includes a first piping region 111 and a second piping region 112, and the first piping region 111 and the second piping region 112 extend such that their positions change in both the circumferential and axial directions as they move downstream in the fuel flow. For example, in the example shown in Figures 4 and 5, only the second piping region 112 extends such that its positions change in both the circumferential and axial directions as it moves downstream in the fuel flow, while the axial position of the first piping region 111 remains constant regardless of its circumferential position. In other words, in Figures 4 and 5, of the first piping region 111 and the second piping region 112, only the second piping region 112 extends from one circumferential side to the other circumferential side and from the axial upstream side to the axial downstream side as it moves from the upstream side to the downstream side in the fuel flow direction.

[0049] Of the first piping region 111 and the second piping region 112, only the first piping region 111 may be configured to extend so that its position in both the circumferential direction and the axial direction changes as it moves downstream in the fuel flow. In this case, the fuel supply pipe 105 has a shape that is reversed left and right on the paper surfaces of FIGS. 4 and 5 . Also, both the first piping region 111 and the second piping region 112 may be configured to extend so that their positions in both the circumferential direction and the axial direction change as they move downstream in the fuel flow. In this case, in FIGS. 4 and 5 , the first piping region 111 is configured to move from the other circumferential side to one circumferential side and from the axial upstream side to the axial downstream side as it moves from the upstream side to the downstream side in the fuel flow direction, and the second piping region 112 is configured to move from the one circumferential side to the other circumferential side and from the axial upstream side to the axial downstream side as it moves from the upstream side to the downstream side in the fuel flow direction.

[0050] (Regarding the Problems Solved by the Fuel Supply Pipe 105) In the combustor 4 according to some embodiments, the second flange portion 102 of the inlet portion 101 of the fuel supply pipe assembly 100 is fixed to the casing 20, more specifically, to the third flange portion 67 of the top hat section 60. The outlet portion 107 of the fuel supply pipe assembly 100 is fixed to the combustion liner 36 via a bracket 107a (see FIG. 2 ). Therefore, during operation of the combustor 4, a temperature difference occurs between the combustion liner 36 and the fuel supply pipe 105. Thermal stress acts on the fuel supply pipe 105 due to the difference between the change in the axial distance between the inlet portion 101 and the outlet portion 107 caused by thermal expansion of the combustion liner 36 and the thermal expansion of the fuel supply pipe 105 itself. For example, if the inlet portion 101 and the outlet portion 107 are connected by a single straight pipe, a relatively large thermal stress acts on the straight pipe.

[0051] To alleviate this thermal stress, it is conceivable to provide the piping connecting the inlet portion 101 and the outlet portion 107 with a circumferentially extending region, such as the first piping region 111 in Figure 4, and absorb the thermal expansion difference with the combustion liner 36 by deflection of this region. In this case, the circumferential positions of the inlet portion 101 and the outlet portion 107 must also be shifted according to the extension length of this region. However, if the difference in the circumferential positions of the inlet portion 101 and the outlet portion 107 is relatively small, the extension length of the circumferentially extending region described above becomes short, and deflection of this region will not be able to sufficiently absorb the thermal expansion difference with the combustion liner 36 in the axial direction.

[0052] In this regard, in the fuel supply pipe 105 according to some embodiments, the direction from the inlet portion 101 toward the third connecting pipe region 123 in the first piping region 111 is the direction toward one side in the circumferential direction, and the direction from the third connecting pipe region 123 toward the outlet portion 107 in the second piping region 112 is the direction toward the other side in the circumferential direction. As a result, even if the difference in the circumferential positions of the inlet portion 101 and the outlet portion 107 is relatively small, the circumferential lengths of the first piping region 111 and the second piping region 112 can be sufficiently ensured, and thermal stress generated in the fuel supply pipe 105 due to the thermal expansion difference can be effectively reduced.

[0053] 6 is a diagram illustrating the wall thickness of the piping from the first connecting pipe region 121 to the first piping region 111 in FIG. 5 , and the wall thickness of the piping from the downstream region 123D of the third connecting pipe region 123 to the second piping region 112 in FIG. 7 is a diagram illustrating the wall thickness of the piping from the second piping region 112 to the second connecting pipe region 122 in FIG. 5 , and the wall thickness of the piping from the first piping region 111 to the upstream region 123U of the third connecting pipe region 123 in FIG. 5 . For example, in the fuel supply pipe 105 shown in FIG. 5 , the outer diameter doa of the first connecting pipe region 121 is preferably larger than the outer diameter dob of the first piping region 111, as shown in FIG. 6 . Similarly, in the fuel supply pipe 105 shown in FIG. 5 , the outer diameter doc of the second connecting pipe region 122 is preferably larger than the outer diameter dod of the second piping region 112, as shown in FIG. 7 . That is, in the fuel supply pipe 105 according to some embodiments, it is preferable to increase the outer diameter of the necessary region from the viewpoint of vibration suppression of the fuel supply pipe 105. Generally, it is desirable to increase the outer diameter of the pipe to ensure the vibration strength and characteristic value of the pipe. On the other hand, it is desirable to decrease the outer diameter of the pipe to alleviate thermal stress in the pipe. According to the fuel supply pipe 105 shown in FIG. 5 , it is possible to ensure the vibration strength and characteristic value in the first connecting pipe region 121 and the second connecting pipe region 122, which have relatively large outer diameters, and to alleviate thermal stress in the first piping region 111 and the second piping region 112, which have relatively small outer diameters.

[0054] For example, in the fuel supply pipe 105 shown in FIG. 5 , the wall thickness ta of the first connecting pipe region 121 is preferably greater than the wall thickness tb of the first piping region 111, as shown in FIG. 6 . Similarly, in the fuel supply pipe 105 shown in FIG. 5 , the wall thickness tc of the second connecting pipe region 122 is preferably greater than the wall thickness td of the second piping region 112, as shown in FIG. 7 . Generally, it is desirable to increase the wall thickness of the pipe to ensure the vibration strength and characteristic value of the pipe. On the other hand, it is desirable to decrease the wall thickness of the pipe to alleviate thermal stress in the pipe. The fuel supply pipe 105 shown in FIGS. 5 and 6 ensures the vibration strength and characteristic value in the first connecting pipe region 121 and the second connecting pipe region 122, which have relatively large wall thicknesses, while alleviating thermal stress in the first piping region 111 and the second piping region 112, which have relatively small wall thicknesses.

[0055] For example, in the fuel supply pipe 105 shown in Fig. 5 , the inner diameter di of the first connecting pipe region 121 may be the same as the inner diameter di of the first piping region 111, as shown in Fig. 6 . Similarly, in the fuel supply pipe 105 shown in Fig. 5 , the inner diameter di of the second connecting pipe region 122 may be the same as the inner diameter di of the second piping region 112, as shown in Fig. 7 . Similarly, in the fuel supply pipe 105 shown in Fig. 4 , the inner diameter di of the first connecting pipe region 121 may be the same as the inner diameter di of the first piping region 111, and the inner diameter di of the second connecting pipe region 122 may be the same as the inner diameter di of the second piping region 112. As a result, there is no change in the inner diameter di from the first connecting pipe region 121 to the first piping region 111, and from the second piping region 112 to the second connecting pipe region 122, thereby reducing pressure loss of the fuel flowing therethrough.

[0056] For example, in the fuel supply pipe 105 shown in Fig. 5, the outer diameter doe of the upstream region 123U of the third connecting pipe region 123 may be larger than the outer diameter dob of the first piping region 111, as shown in Fig. 7. Similarly, in the fuel supply pipe 105 shown in Fig. 5, the outer diameter dof of the downstream region 123D of the third connecting pipe region 123 may be larger than the outer diameter dod of the second piping region 112, as shown in Fig. 6. This ensures vibration strength and characteristic values ​​in at least the upstream region 123U and downstream region 123D of the third connecting pipe region 123, which have relatively large outer diameters, and also alleviates thermal stress in the first piping region 111 and the second piping region 112, which have relatively small outer diameters.

[0057] For example, in the fuel supply pipe 105 shown in Fig. 5, the wall thickness te of the upstream region 123U of the third connecting pipe region 123 may be greater than the wall thickness tb of the first piping region 111, as shown in Fig. 7. Similarly, in the fuel supply pipe 105 shown in Fig. 5, the wall thickness tf of the downstream region 123D of the third connecting pipe region 123 may be greater than the wall thickness td of the second piping region 112, as shown in Fig. 6. This ensures vibration strength and characteristic values ​​in at least the upstream region 123U and downstream region 123D of the third connecting pipe region 123, which have relatively large wall thicknesses, and also alleviates thermal stress in the first piping region 111 and the second piping region 112, which have relatively small wall thicknesses.

[0058] For example, in the fuel supply pipe 105 shown in FIG. 5 , the inner diameter d i of the third connecting pipe region 123 may be the same as the inner diameter d i of the first piping region 111 and the second piping region 112, as shown in FIGS. 6 and 7 . Similarly, in the fuel supply pipe 105 shown in FIG. 4 , the inner diameter d of the third connecting pipe region 123 may be the same as the inner diameter d i of the first piping region 111 and the second piping region 112. This reduces the pressure loss of the fuel flowing therethrough, since the inner diameter d i does not change from the first piping region 111 to the third connecting pipe region 123 and from the third connecting pipe region 123 to the second piping region 112. Note that it is desirable for the inner diameter d i of the third connecting pipe region 123 to be constant throughout the entire third connecting pipe region 123. However, in some embodiments of the fuel supply pipe 105, the inner diameter d i of the third connecting pipe region 123 may be different in some regions from in other regions.

[0059] 4 and 5, it is desirable that the inner diameter d of the fuel supply pipe 105 is constant throughout the entire area. However, in some embodiments, the inner diameter d of the fuel supply pipe 105 may be different in some regions from in other regions.

[0060] (Regarding the Transition Region) As described above, in the fuel supply pipe 105 shown in Fig. 5 , the first connecting pipe region 121 and the first piping region 111 have different outer diameters, and the second connecting pipe region 122 and the second piping region 112 have different outer diameters. Therefore, in the fuel supply pipe 105 shown in Fig. 5 , a first transition region 131 is provided between the first connecting pipe region 121 and the first piping region 111. The first transition region 131 is formed so that the outer diameter gradually changes from the first connecting pipe region 121 side to the first piping region 111 side. That is, the outer diameter dog of the first transition region 131 gradually changes from the outer diameter doa of the first connecting pipe region 121 to the outer diameter dob of the first piping region 111 as it moves from a connection position 131a with the first connecting pipe region 121 to a connection position 131b with the first piping region 111.

[0061] 5 , a second transition region 132 is provided between the second connecting pipe region 122 and the second piping region 112. The second transition region 132 is formed so that the outer diameter gradually changes from the second connecting pipe region 122 side toward the second piping region 112. That is, the outer diameter doh of the second transition region 132 gradually changes from the outer diameter doc of the second connecting pipe region 122 to the outer diameter dod of the second piping region 112 as it moves from a connection position 132a with the second connecting pipe region 122 to a connection position 132b with the second piping region 112.

[0062] This eliminates any areas where the change in outer diameter is discontinuous from the first connecting pipe region 121 to the first piping region 111, and any areas where the change in outer diameter is discontinuous from the second connecting pipe region 122 to the second piping region 112, making it less likely to cause stress concentration.

[0063] 5 , when the outer diameter of the upstream region 123U of the third connecting pipe region 123 is larger than that of the first piping region 111, it is preferable to provide a third transition region 133 similar to the first transition region 131 and the second transition region 132 between the first piping region 111 and the third connecting pipe region 123. Similarly, when the outer diameter of the downstream region 123D of the third connecting pipe region 123 is larger than that of the second piping region 112, it is preferable to provide a third transition region 133 similar to the first transition region 131 and the second transition region 132 between the second piping region 112 and the third connecting pipe region 123.

[0064] Furthermore, if the outer diameters of the upstream region 123U and the downstream region 123D are larger than that of the midstream region 123M, it is preferable to provide a third transition region 133 similar to the first transition region 131 and the second transition region 132 between the upstream region 123U and the midstream region 123M, and between the midstream region 123M and the downstream region 123D.

[0065] 6, in the fuel supply pipe 105 shown in Fig. 5, from the first connecting pipe region 121 to the first transition region 131, the outer peripheral surface 121c of the first connecting pipe region 121 and the outer peripheral surface 131c of the first transition region 131 are preferably connected by a curved surface Cs having a center of curvature Oa on the inside in the radial direction (the radial direction Drf of the fuel supply pipe 105) of the first connecting pipe region 121 and the first transition region 131. In the fuel supply pipe 105 shown in Fig. 5, from the first transition region 131 to the first piping region 111, the outer peripheral surface 131c of the first transition region 131 and the outer peripheral surface 111c of the first piping region 111 are preferably connected by a curved surface Cs having a center of curvature Oa on the outside in the radial direction Drf of the first transition region 131 and the first piping region 111.

[0066] 7, in the fuel supply pipe 105 shown in Fig. 5, from the second connecting pipe region 122 to the second transition region 132, the outer peripheral surface 122c of the second connecting pipe region 122 and the outer peripheral surface 132c of the second transition region 132 are preferably connected by a curved surface Cs having a center of curvature Oa on the inside in the radial direction Drf of the second connecting pipe region 122 and the second transition region 132. In the fuel supply pipe 105 shown in Fig. 5, from the second transition region 132 to the second piping region 112, the outer peripheral surface 132c of the second transition region 132 and the outer peripheral surface 112c of the second piping region 112 are preferably connected by a curved surface Cs having a center of curvature Oa on the outside in the radial direction Drf of the second transition region 132 and the second piping region 112.

[0067] This allows a smooth connection between the outer peripheral surface 121c of the first connecting pipe region 121 and the outer peripheral surface 131c of the first transition region 131, a smooth connection between the outer peripheral surface 131c of the first transition region 131 and the outer peripheral surface 111c of the first piping region 111, a smooth connection between the outer peripheral surface 122c of the second connecting pipe region 122 and the outer peripheral surface 132c of the second transition region 132, and a smooth connection between the outer peripheral surface 132c of the second transition region 132 and the outer peripheral surface 112c of the second piping region 112. This further reduces the likelihood of stress concentration.

[0068] Similarly, the third transition region 133 may also be provided with the curved surface Cs.

[0069] (Regarding the Joint) The fuel supply pipe 105 according to some embodiments may be integrally formed over the entire length of the fuel supply pipe 105. That is, the fuel supply pipe 105 according to some embodiments may be formed as a single piping component from the beginning, rather than being obtained by connecting the ends of several piping components together. Note that, in order to obtain the fuel supply pipe 105 that is integrally formed over the entire length of the fuel supply pipe 105, the fuel supply pipe 105 may be formed by, for example, an additive manufacturing method.

[0070] However, if the additive manufacturing device is unable to manufacture the entire fuel supply pipe 105 at once due to limitations on the size of the parts that can be manufactured by the additive manufacturing device, the fuel supply pipe 105 may be divided into several regions, and the ends of the piping parts manufactured by additive manufacturing for each region may be connected to obtain the fuel supply pipe 105. In this case, when the piping parts are joined by welding or brazing, it is desirable to locate the joints connecting the piping parts at locations where there is no change in outer diameter or thickness in order to reduce stress concentration as much as possible.

[0071] Therefore, for example, when the fuel supply pipe 105 shown in FIG. 5 is obtained by welding together piping components, the first piping region 111 preferably has an upstream region 111U of the first piping region 111 connected to a downstream region 111D of the first piping region 111 via a joint 141. That is, the joint 141 may be provided at a position away from both ends of the first piping region 111. Similarly, the second piping region 112 preferably has an upstream region 112U of the second piping region 112 connected to a downstream region 112D of the second piping region 112 via a joint 141. That is, the joint 141 may be provided at a position away from both ends of the second piping region 112. This allows the joint 141 to be provided in a location where there is no change in the outer diameter or wall thickness, making it less likely that stress will concentrate at the joint 141.

[0072] 5, the joints 141 may be provided in the upstream region 123U of the third connecting pipe region 123 at positions away from both ends of the upstream region 123U, or in the downstream region 123D at positions away from both ends of the downstream region 123D. At the joints 141, the piping components are joined together by, for example, welding or brazing.

[0073] (Regarding Support of the Fuel Supply Pipe 105) For example, as shown in FIG. 2 , the fuel supply pipe 105 may be supported by the combustion liner 36 via a support portion 145 that supports the fuel supply pipe 105. The support position of the support portion 145 may be the third connection pipe region 123, which is circumferentially farthest from the inlet portion 101, which is fixed to the third flange portion 67 of the top hat portion 60, and the outlet portion 107, which is fixed to the combustion liner 36 via a bracket 107 a. That is, in the fuel supply pipe 105 according to some embodiments, the third connection pipe region 123 may be supported by the combustion liner 36 via the support portion 145. This suppresses vibration of the third connection pipe region 123, which is circumferentially farthest from the inlet portion 101 and the outlet portion 107, and therefore suppresses vibration of the entire fuel supply pipe 105.

[0074] The combustor 4 according to one embodiment includes the fuel supply pipe assembly 100 according to some of the above-described embodiments, the combustion liner 36, and the third fuel nozzle 70. This can reduce thermal stress that occurs in the fuel supply pipe 105 due to the difference in axial thermal expansion between the fuel supply pipe 105 and the combustion liner 36.

[0075] A gas turbine 1 according to one embodiment includes the compressor 2, the gas turbine combustor 4 configured as described above, and the turbine 6 configured to be driven by combustion gas from the gas turbine combustor 4. This can improve the reliability of the turbine 6.

[0076] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0077] The contents of the above-described embodiments can be understood, for example, as follows: (1) A fuel supply pipe assembly 100 according to at least one embodiment of the present disclosure is a fuel supply pipe assembly 100 disposed in a casing (combustor casing 32) for supplying fuel to a side fuel nozzle (third fuel nozzle 70) provided on a side of a combustion liner 36 of a gas turbine combustor 4. The fuel supply pipe assembly 100 according to at least one embodiment of the present disclosure includes an inlet portion 101 connected to a fuel supply source (fuel piping 150), an outlet portion 107 constituting a part of a fuel manifold 109 for supplying fuel to the side fuel nozzle (third fuel nozzle 70), and a fuel supply pipe 105 connecting the inlet portion 101 and the outlet portion 107. The fuel supply pipe 105 includes a first piping region 111 extending circumferentially of the combustion tube 36 along the outer surface of the combustion tube 36, a second piping region 112 extending circumferentially along the outer surface and spaced apart from the first piping region 111 in the axial direction of the combustion tube 36, a first connecting pipe region 121 provided between the inlet portion 101 and the first piping region 111, a second connecting pipe region 122 provided between the outlet portion 107 and the second piping region 112, and a third connecting pipe region 123 provided between the first piping region 111 and the second piping region 112. At least one of the first piping region 111 and the second piping region 112 extends such that its position in both the circumferential and axial directions changes as it moves downstream in the fuel flow. The third connecting pipe region 123 is formed on the upstream side so as to extend from the first piping region 111 toward the third connecting pipe region 123 to one side in the circumferential direction, and on the downstream side so as to extend from the third connecting pipe region 123 toward the second piping region 112 to the other side in the circumferential direction.

[0078] According to the configuration (1) above, the difference in thermal expansion in the axial direction between the fuel supply pipe 105 and the combustion liner 36 can be absorbed by the first piping region 111 and the second piping region 112 extending in the circumferential direction, thereby reducing thermal stress generated in the fuel supply pipe 105 due to the difference in thermal expansion. Furthermore, according to the configuration (1) above, in the first piping region 111, the direction from the inlet portion 101 toward the third connecting pipe region 123 is a direction toward one side in the circumferential direction, and in the second piping region 112, the direction from the third connecting pipe region 123 toward the outlet portion 107 is a direction toward the other side in the circumferential direction. As a result, even if the difference in circumferential position between the inlet portion 101 and the outlet portion 107 is relatively small, the circumferential lengths of the first piping region 111 and the second piping region 112 can be sufficiently secured, thereby effectively reducing thermal stress generated in the fuel supply pipe 105 due to the difference in thermal expansion.

[0079] (2) In some embodiments, in the configuration of (1) above, the outer diameters doa and doc of the first connecting pipe region 121 and the second connecting pipe region 122 may be larger than the outer diameters dob and dod of the first piping region 111 and the second piping region 112.

[0080] According to the above configuration (2), vibration strength and characteristic values ​​can be ensured in the first connecting pipe region 121 and the second connecting pipe region 122, which have relatively large outer diameters, and thermal stress can be alleviated in the first piping region 111 and the second piping region 112, which have relatively small outer diameters.

[0081] (3) In some embodiments, in the configurations (1) or (2) above, the thicknesses ta and tc of the first connecting pipe region 121 and the second connecting pipe region 122 may be greater than the thicknesses tb and td of the first piping region 111 and the second piping region 112.

[0082] According to the above configuration (3), vibration strength and characteristic values ​​can be ensured in the first connecting pipe region 121 and the second connecting pipe region 122, which have relatively large wall thicknesses, and thermal stress can be alleviated in the first piping region 111 and the second piping region 112, which have relatively small wall thicknesses.

[0083] (4) In some embodiments, in any of the configurations (1) to (3) above, the inner diameters di of the first connecting pipe region 121 and the second connecting pipe region 122 may be the same as the inner diameters di of the first piping region 111 and the second piping region 112.

[0084] According to the configuration (4) above, there is no change in the inner diameter di from the first connecting pipe region 121 to the first piping region 111, and from the second piping region 112 to the second connecting pipe region 122, so the pressure loss of the fuel flowing inside can be reduced.

[0085] (5) In some embodiments, in any of the configurations (1) to (4) above, the outer diameters doe, dof of at least the upstream region 123U and the downstream region 123D of the third connecting pipe region 123 may be larger than the outer diameters dob, dod of the first piping region 111 and the second piping region 112.

[0086] According to the above configuration (5), vibration strength and characteristic values ​​can be ensured at least in the upstream region 123U and downstream region 123D of the third connecting pipe region 123, which has a relatively large outer diameter, and thermal stress can be alleviated in the first piping region 111 and the second piping region 112, which have a relatively small outer diameter.

[0087] (6) In some embodiments, in any of the configurations (1) to (5) above, the thicknesses te and tf of at least the upstream region 123U and downstream region 123D of the third connecting pipe region 123 may be greater than the thicknesses tb and td of the first piping region 111 and the second piping region 112.

[0088] According to the above configuration (6), vibration strength and characteristic values ​​can be ensured at least in the upstream region 123U and downstream region 123D of the third connecting pipe region 123, which have a relatively large thickness, and thermal stress can be alleviated in the first piping region 111 and the second piping region 112, which have a relatively small thickness.

[0089] (7) In some embodiments, in any of the configurations (1) to (6) above, the inner diameter di of the third connecting pipe region 123 may be the same as the inner diameter di of the first piping region 111 and the second piping region 112.

[0090] According to the configuration (7) above, there is no change in the inner diameter di from the first piping region 111 to the third connecting pipe region 123, and from the third connecting pipe region 123 to the second piping region 112, so the pressure loss of the fuel flowing inside can be reduced.

[0091] (8) In some embodiments, in any of the configurations (1) to (7) above, the fuel supply pipe 105 may include a first transition region 131 provided between the first connecting pipe region 121 and the first piping region 111, and a second transition region 132 provided between the second connecting pipe region 122 and the second piping region 112. The outer diameters doa and doc of the first connecting pipe region 121 and the second connecting pipe region 122 may be larger than the outer diameters dob and dod of the first piping region 111 and the second piping region 112. The outer diameter dog of the first transition region 131 may gradually change from the outer diameter doa of the first connecting pipe region 121 to the outer diameter dob of the first piping region 111 as it moves from a connection position 131a with the first connecting pipe region 121 to a connection position 131b with the first piping region 111. The outer diameter doh of the second transition region 132 preferably gradually changes from the outer diameter doc of the second connecting pipe region 122 to the outer diameter dod of the second piping region 112 as it moves from the connection position 132a with the second connecting pipe region 122 to the connection position 132b with the second piping region 112.

[0092] According to the above configuration (8), there are no parts where the change in outer diameter is discontinuous from the first connecting pipe region 121 to the first piping region 111, and there are no parts where the change in outer diameter is discontinuous from the second connecting pipe region 122 to the second piping region 112, so stress concentration is less likely to occur.

[0093] (9) In some embodiments, in the configuration of (8) above, from the first connecting pipe region 121 to the first transition region 131, the outer peripheral surface 121 c of the first connecting pipe region 121 and the outer peripheral surface 131 c of the first transition region 131 may be connected by a curved surface Cs having a center of curvature Oa on the inside in the radial direction Drf of the first connecting pipe region 121 and the first transition region 131. From the first transition region 131 to the first piping region 111, the outer peripheral surface 131 c of the first transition region 131 and the outer peripheral surface 111 c of the first piping region 111 may be connected by a curved surface Cs having a center of curvature Oa on the outside in the radial direction Drf of the first transition region 131 and the first piping region 111. From the second connecting pipe region 122 to the second transition region 132, the outer peripheral surface 122c of the second connecting pipe region 122 and the outer peripheral surface 132c of the second transition region 132 may be connected by a curved surface Cs having a center of curvature Oa on the inside in the radial direction Drf of the second connecting pipe region 122 and the second transition region 132. From the second transition region 132 to the second piping region 112, the outer peripheral surface 132c of the second transition region 132 and the outer peripheral surface 112c of the second piping region 112 may be connected by a curved surface Cs having a center of curvature Oa on the outside in the radial direction Drf of the second transition region 132 and the second piping region 112.

[0094] According to the configuration (9) above, the outer peripheral surface 121c of the first connecting pipe region 121 is smoothly connected to the outer peripheral surface 131c of the first transition region 131, the outer peripheral surface 131c of the first transition region 131 is smoothly connected to the outer peripheral surface 111c of the first piping region 111, the outer peripheral surface 122c of the second connecting pipe region 122 is smoothly connected to the outer peripheral surface 132c of the second transition region 132, and the outer peripheral surface 132c of the second transition region 132 is smoothly connected to the outer peripheral surface 112c of the second piping region 112. This further reduces the likelihood of stress concentration.

[0095] (10) In some embodiments, in any of the configurations (1) to (9) above, the first piping region 111 may be configured such that an upstream region 111U of the first piping region 111 and a downstream region 111D of the first piping region 111 are connected via a joint 141. The second piping region 112 may be configured such that an upstream region 112U of the second piping region 112 and a downstream region 112D of the second piping region 112 are connected via a joint 141.

[0096] According to the above configuration (10), the joint 141 can be provided at a location where there is no change in the outer diameter or thickness, so that stress is less likely to be concentrated at the joint 141 .

[0097] (11) In some embodiments, in any of the configurations (1) to (10) above, the third connecting pipe region 123 may be supported by the combustion liner 36 via a support portion 145 .

[0098] According to the configuration (11) above, vibration of the third connecting pipe region 123 is suppressed, and therefore vibration of the entire fuel supply pipe 105 can be suppressed.

[0099] (12) A gas turbine combustor 4 according to at least one embodiment of the present disclosure includes the fuel supply pipe assembly 100 having the configuration described in any one of (1) to (11), a combustion liner 36, and a side fuel nozzle (third fuel nozzle 70).

[0100] According to the configuration (12), the fuel supply pipe assembly 100 having any one of the configurations (1) to (11) is provided, thereby making it possible to reduce thermal stress generated in the fuel supply pipe 105 due to the difference in axial thermal expansion between the fuel supply pipe 105 and the combustion liner 36. Furthermore, according to the configuration (12), even if the difference in circumferential position between the inlet portion 101 and the outlet portion 107 is relatively small, the circumferential lengths of the first piping region 111 and the second piping region 112 can be sufficiently ensured, making it possible to effectively reduce thermal stress generated in the fuel supply pipe 105 due to the difference in thermal expansion. Therefore, according to the configuration (12), it is possible to improve the reliability of the gas turbine combustor 4.

[0101] (13) A gas turbine 1 according to at least one embodiment of the present disclosure includes a compressor 2, a gas turbine combustor 4 having the configuration described in (12) above, and a turbine 6 configured to be driven by combustion gas from the gas turbine combustor 4.

[0102] According to the configuration of (13) above, since the gas turbine combustor 4 having the configuration of (12) above is provided, the reliability of the turbine 6 can be improved.

[0103] REFERENCE SIGNS LIST 1 Gas turbine 2 Compressor 4 Gas turbine combustor (combustor) 6 Turbine 20 Casing 22 Turbine casing 32 Combustor casing 36 Combustor liner 50 Transition piece 52 Outer casing 60 Top hat section 70 Third fuel nozzle 100 Fuel supply pipe assembly 101 Inlet section 105 Fuel supply pipe 107 Outlet section 109 Fuel manifold 111 First piping region 112 Second piping region 121 First connecting pipe region 122 Second connecting pipe region 123 Third connecting pipe region 123D Downstream region 123M Midstream region 123D Upstream region 131 First transition region 131a Connection position 131b Connection position 132 Second transition region 132a Connection position 132b Connection position 133 Third transition region 141 Joint portion 145 Support portion 150 Fuel pipe

Claims

1. A fuel supply pipe assembly disposed within a cabin for supplying fuel to a side fuel nozzle provided on a side of a combustion liner of a gas turbine combustor, the fuel supply pipe assembly comprising: an inlet portion connected to a fuel supply source; an outlet portion constituting a part of a fuel manifold for supplying the fuel to the side fuel nozzle; and a fuel supply pipe connecting the inlet portion and the outlet portion, wherein the fuel supply pipe includes: a first piping region extending in the circumferential direction of the combustion liner along an outer surface of the combustion liner; a second piping region extending in the circumferential direction along the outer surface and spaced apart from the first piping region in the axial direction of the combustion liner; a first connecting pipe region provided between the inlet portion and the first piping region; a second connecting pipe region provided between the outlet portion and the second piping region; and a third connecting pipe region provided between the first piping region and the second piping region, wherein at least one of the first piping region and the second piping region extends such that its position in both the circumferential direction and the axial direction changes as it moves downstream in the flow of the fuel, the third connecting pipe region is formed on the upstream side so as to extend from the first piping region toward the third connecting pipe region toward one side in the circumferential direction, and is formed on the downstream side so as to extend from the third connecting pipe region toward the second piping region toward the other side in the circumferential direction.

2. The fuel supply pipe assembly according to claim 1, wherein the outer diameters of the first connecting pipe region and the second connecting pipe region are larger than the outer diameters of the first piping region and the second piping region.

3. The fuel supply pipe assembly according to claim 1 or 2, wherein the wall thickness of the first connecting pipe region and the second connecting pipe region is greater than the wall thickness of the first piping region and the second piping region.

4. The fuel supply pipe assembly according to claim 1 or 2, wherein the inner diameters of the first connecting pipe region and the second connecting pipe region are the same as the inner diameters of the first piping region and the second piping region.

5. The fuel supply pipe assembly according to claim 1 or 2, wherein the outer diameter of at least the upstream region and downstream region of the third connecting pipe region is larger than the outer diameters of the first piping region and the second piping region.

6. A fuel supply pipe assembly according to claim 1 or 2, wherein the wall thickness of at least the upstream and downstream regions of the third connecting pipe region is greater than the wall thickness of the first piping region and the second piping region.

7. A fuel supply pipe assembly according to claim 1 or 2, wherein the inner diameter of the third connecting pipe region is the same as the inner diameters of the first piping region and the second piping region.

8. A fuel supply pipe assembly according to claim 1 or 2, wherein the fuel supply pipe includes: a first transition region provided between the first connecting pipe region and the first piping region; and a second transition region provided between the second connecting pipe region and the second piping region; outer diameters of the first connecting pipe region and the second connecting pipe region are larger than outer diameters of the first piping region and the second piping region; the outer diameter of the first transition region gradually changes from the outer diameter of the first connecting pipe region to the outer diameter of the first piping region as it moves from the connection position with the first connecting pipe region to the connection position with the first piping region; and the outer diameter of the second transition region gradually changes from the outer diameter of the second connecting pipe region to the outer diameter of the second piping region as it moves from the connection position with the second connecting pipe region to the connection position with the second piping region.

9. The fuel supply pipe assembly according to claim 8, wherein, from the first connecting pipe region to the first transition region, the outer peripheral surface of the first connecting pipe region and the outer peripheral surface of the first transition region are connected by a curved surface having a center of curvature radially inward of the first connecting pipe region and the first transition region; from the first transition region to the first piping region, the outer peripheral surface of the first transition region and the outer peripheral surface of the first piping region are connected by a curved surface having a center of curvature radially outward of the first transition region and the first piping region; from the second connecting pipe region to the second transition region, the outer peripheral surface of the second connecting pipe region and the outer peripheral surface of the second transition region are connected by a curved surface having a center of curvature radially inward of the second connecting pipe region and the second transition region; and from the second transition region to the second piping region, the outer peripheral surface of the second transition region and the outer peripheral surface of the second piping region are connected by a curved surface having a center of curvature radially outward of the second transition region and the second piping region.

10. A fuel supply pipe assembly as described in claim 1 or 2, wherein the first piping region is connected to an upstream region of the first piping region and a downstream region of the first piping region via a joint, and the second piping region is connected to an upstream region of the second piping region and a downstream region of the second piping region via a joint.

11. A fuel supply pipe assembly according to claim 1 or 2, wherein the third connecting pipe region is supported on the combustion liner via a support portion.

12. A gas turbine combustor comprising: a fuel supply pipe assembly according to claim 1 or 2; the combustion liner; and the side fuel nozzle.

13. A gas turbine comprising: a compressor; the gas turbine combustor according to claim 12; and a turbine configured to be driven by combustion gas from the gas turbine combustor.

Images