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

Abstract

In a fuel supply pipe assembly according to at least one embodiment of the present disclosure, a fuel supply pipe comprises: a first flange portion that can be coupled to a fuel pipe for supplying fuel to the fuel supply pipe; and a second flange portion that can be coupled to a top hat portion. The top hat portion is provided in an end portion on one side in the axial direction of a first cylindrical portion, and includes: a top hat flange portion for attaching the top hat portion to a casing of a gas turbine; and a third flange portion that is provided in an end portion on the other side in the axial direction of a second cylindrical portion and that can be coupled to the second flange portion. The first flange portion is positioned between the top hat flange portion and the third flange portion, in the axial direction, when the second flange portion is coupled to the third flange portion.

Description

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

[0001] This application claims priority to Japanese Patent Application No. 2023-132670, filed with the Japan Patent Office on August 16, 2023, 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 protrudes toward the upstream side of the flow of combustion gas along the axial direction of the combustion liner (see, for example, Patent Document 1).

[0003] Japanese Patent Application Laid-Open No. 2015-210075

[0004] For example, a combustion liner without a protruding fuel supply pipe, such as the combustion liner of the gas turbine combustor described in Patent Document 1, is attached to the lower half of the turbine from which the upper half has been removed during periodic inspection. In this case, the combustion liner is inserted into a gap that is formed in the radial direction of the turbine rotor between the lower half of the casing and the intermediate shaft cover from the horizontal dividing plane between the upper and lower halves, and the orientation of the combustion liner is changed at a position between the combustor window and the blade ring within the gap to install the combustion liner in the turbine.

[0005] However, in the combustion liner of the gas turbine combustor described in Patent Document 1, for example, the fuel supply pipe protrudes in the axial direction of the combustion liner as described above. Therefore, when installing the combustion liner, even if an attempt is made to change the orientation of the combustion liner at a position between the combustor window and the blade ring within the above-described gap, the fuel supply pipe gets in the way and the combustion liner cannot be changed to the desired orientation. Therefore, when installing the combustion liner of the gas turbine combustor described in Patent Document 1, for example, in the turbine, the combustion liner is installed from the outside of the combustor window provided in the casing through the combustor window. In this case, the installation work takes longer than when installing the combustion liner in the turbine by changing the orientation of the combustion liner at a position between the combustor window and the blade ring within the above-described gap.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure has an object to provide a fuel supply pipe assembly, a gas turbine combustor, and a gas turbine that can reduce the time required for the work of attaching a combustion liner to a turbine.

[0007] (1) According to at least one embodiment of the present disclosure, there is provided a fuel supply pipe assembly for supplying fuel to a side fuel nozzle provided at a side of a combustion liner of a gas turbine combustor, the fuel supply pipe assembly comprising: a fuel supply pipe for supplying the fuel to the side fuel nozzle; and a top hat portion of the gas turbine combustor, wherein the fuel supply pipe comprises: a first flange portion coupleable to a fuel pipe for supplying the fuel to the fuel supply pipe; and a second flange portion coupleable to the top hat portion, wherein the top hat portion comprises: a first cylindrical portion extending in the axial direction, the first cylindrical portion having at least one axial fuel nozzle disposed therein, the axial fuel nozzle being different from the side fuel nozzle and extending in the axial direction of the combustion liner; a second cylindrical portion extending in the axial direction and provided on an outer circumferential side of the first cylindrical portion; and a top hat flange portion provided at one end of the first cylindrical portion in the axial direction, for attaching the top hat portion to a casing of a gas turbine. and a third flange portion provided at the other end of the second cylindrical portion in the axial direction and connectable to the second flange portion, wherein when the second flange portion is connected to the third flange portion, the first flange portion is located between the top hat flange portion and the third flange portion in the axial direction.

[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; the side fuel nozzle; and the at least one axial 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, the time required to attach a combustion liner to a turbine can be reduced.

[0011] FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment. FIG. 2 is a schematic diagram showing a combustor and an inlet portion of a turbine of a gas turbine according to an embodiment. FIG. 3 is a schematic cross-sectional view of a combustor of a gas turbine according to an embodiment. FIG. 4 is a perspective view of a top hat part. FIG. 5 is a view of the top hat part as seen from inside a casing. FIG. 6 is a view of the vicinity of a third flange part of a second cylindrical part. FIG. 7 is a view of the vicinity of the third flange part of a second cylindrical part. FIG. 8 is a view of the vicinity of the third flange part of a second cylindrical part. FIG. 9 is a view of the vicinity of the third flange part of a second cylindrical part. FIG. 10 is a view of the vicinity of the third flange part of a second cylindrical part.

[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 illustrating 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. Fig. 4 is a perspective view of a top hat section 60, which will be described later. Fig. 5 is a view of the top hat section 60 as viewed from inside the casing 20.

[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. １ The 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. In the following description, the first fuel nozzle 40 and the second fuel nozzle 46 will also be referred to as axial fuel nozzles.

[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 the 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 the embodiment includes a fuel supply pipe 101 for supplying fuel to the third fuel nozzle 70, and a top hat portion 60 of the combustor 4, which will be described later. In the fuel supply pipe assembly 100 according to the embodiment, fuel supplied from a fuel pipe 150 flows through the fuel supply pipe 101 and is supplied to the third fuel nozzle 70. Note that, as will be described later, the fuel pipe 150 includes an external fuel pipe 151 outside the combustor 4, and a connecting pipe 152, which will be described later, that connects the external fuel pipe 151 and the fuel supply pipe 101.

[0029] In the combustor 4 according to the embodiment, one fuel supply pipe assembly 100 is provided for one combustor 4. Note that, in a case where a plurality of third fuel nozzles 70 are provided along the circumferential direction of the combustor 4, fuel is distributed from one fuel supply pipe assembly 100 to the plurality of third fuel nozzles 70. In the combustor 4 according to the embodiment, the fuel supply pipe assembly 100 includes a fuel supply pipe 101 and a top hat portion 60.

[0030] 2 to 5 , 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 to 5 , the top hat flange portion 62 has a shape that protrudes radially outward of the combustor 4, and is fixed to the casing 20 by bolts 59 as shown in FIGS. 2 and 3 .

[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 C １ In one embodiment, the first cylindrical portion 64 is located radially inward of the casing 20.

[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 to 5, 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 3, the second cylindrical portion 65 has a 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 120 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 is separated from the space inside the second cylindrical part 65, i.e., the space outside the casing 20, by a third flange part 67 and a second flange part 120 (described later) that is coupled to the third flange part 67. Details of the third flange part 67 will be described later.

[0036] (Fuel Supply Pipe 101) An end of the fuel supply pipe 101 on the downstream side in the fuel flow direction (the lower right side in FIGS. 2 and 3 ) is connected to the third fuel nozzle 70 directly or via a pipe (not shown). A first flange portion 110 that can be coupled to the fuel pipe 150 (connecting pipe 152) is provided on an end of the fuel supply pipe 101 on the upstream side in the fuel flow direction (the upper left side in FIGS. 2 and 3 ). The fuel supply pipe 101 is provided with a second flange portion 120 that can be coupled to the third flange portion 67 of the top hat part 60, downstream of the first flange portion 110. In the combustor 4 according to one embodiment, the fuel supply pipe 101 is fixed to the combustion liner 36.

[0037] In the combustor 4 according to the embodiment, when the second flange portion 120 is coupled to the third flange portion 67, the first flange portion 110 is aligned with the central axis C １ In the combustor 4 according to the embodiment, when the second flange portion 120 is coupled to the third flange portion 67, the first flange portion 110 is positioned between the top hat flange portion 62 and the third flange portion 67 in the extending direction of the central axis C. １ In the combustor 4 according to an embodiment, the first flange portion 110 and the second flange portion 120 are positioned closer to the third flange portion 67 than the top hat flange portion 62 in the extending direction of the combustor 4. １2 and 3 ) in the extending direction of the combustion liner 36, the length of the fuel supply pipe 101 can be made relatively short. This makes it easier to route the combustion liner 36 inside the casing 20, and reduces the time required to attach the combustion liner 36 to the turbine 6.

[0038] (Fuel Pipe 150) In the combustor 4 according to one embodiment, the fuel pipe 150 for supplying fuel to the fuel supply pipe 101 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 101. 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 the first flange portion 110. 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. Thus, the connecting pipe 152 can be connected to the fuel supply pipe 101 by coupling the first flange portion 110 to the fourth flange portion 154. Furthermore, because the connecting pipe 152 and the external fuel pipe 151 can be connected outside the top hat part 60, the connecting pipe 152 and the external fuel pipe 151 can be easily connected.

[0039] As described above, the end on one side of the second cylindrical portion 65 is an opening 65a, so the connecting pipe 152, which is a pipe for supplying fuel to the fuel supply pipe 101, can be inserted into the second cylindrical portion 65 through the opening 65a and connected to the fuel supply pipe 101.

[0040] FIG. 6 is a view showing the vicinity of the third flange portion 67 of the second cylindrical portion 65, illustrating the second flange portion 120 and the third flange portion 67 joined together with bolts. FIG. 7 is a view showing the vicinity of the third flange portion 67 of the second cylindrical portion 65, illustrating the state before the second flange portion 120 and the third flange portion 67 are joined together with bolts. FIG. 8 is a view showing the vicinity of the third flange portion 67 of the second cylindrical portion 65, illustrating the state after the second flange portion 120 and the third flange portion 67 are joined together with bolts in another example. FIG. 9 is a view showing the vicinity of the third flange portion 67 of the second cylindrical portion 65, illustrating the state after the first flange portion 110 and the fourth flange portion 154 are joined together with bolts. FIG. 10 is a view showing the vicinity of the third flange portion 67 of the second cylindrical portion 65, illustrating the state before the first flange portion 110 and the fourth flange portion 154 are joined together with bolts. FIG. 11 shows the first flange portion 110 along the central axis C １ 12 is a view of the third flange portion 67 viewed from one side to the other side in the extending direction of the central axis C. １ 1 is a view seen from one side to the other in the extension direction.

[0041] (Regarding Shapes of the First Flange Portion 110 and the Through Hole 68) As shown in FIG. 12 , the third flange portion 67 has a through hole 68 through which the first flange portion 110 shown in FIG. 11 can be inserted. When attaching the combustor 4 according to the embodiment to the turbine 6, the combustion liner 36 and the fuel supply pipe 101 fixed to the combustion liner 36 are attached to the casing 20, and then the top hat portion 60 is inserted into the combustor insertion hole 20h formed in the casing 20. At this time, the first flange portion 110 of the fuel supply pipe 101 passes through the through hole 68 provided in the third flange portion 67 of the top hat portion 60. Thus, the top hat portion 60 can be attached to the casing 20 without interference between the first flange portion 110 and the third flange portion 67. Then, by joining the fourth flange portion 154 of the connecting pipe 152 to the first flange portion 110 of the fuel supply pipe 101, the first flange portion 110, which has been inserted through the through hole 68, can be connected to the connecting pipe 152.

[0042] As described above, in the combustor 4 according to one embodiment, the third flange portion 67 has the through-hole 68 through which the fuel supply pipe 101 can be inserted, and therefore the connecting pipe 152 can be connected to the fuel supply pipe 101 that has been inserted through the through-hole 68.

[0043] In the combustor 4 according to the embodiment, as shown in FIG. 11 , the first flange portion 110 is aligned with the central axis C of the fuel supply pipe 101. ２ A plurality of the circumferentially spaced apart axial members are provided around the central axis C. ２ The first flange portion 110 has a protrusion 112 that protrudes outward in the radial direction about the central axis C. ... ２ A plurality of first flange bolt holes 111 extending in the direction of the center axis C ２ The first flange bolt holes 111 are formed at the same positions as the protrusions 112 in the circumferential direction. The first flange portion 110 is formed between two protrusions 112 adjacent to each other in the circumferential direction and is spaced apart from each other in the circumferential direction about the central axis C. ２ The groove 112 is recessed radially inward from the center thereof, and has a plurality of recesses 113 provided at intervals in the circumferential direction.

[0044] In the combustor 4 according to the embodiment, as shown in FIG. 12 , the third flange portion 67 is aligned with the central axis C of the fuel supply pipe 101 attached to the third flange portion 67. ２ A plurality of the circumferentially spaced apart axial members are provided around the central axis C. ２ The third flange portion 67 has a protrusion 67a that protrudes radially inward about the central axis C. ... ２ A plurality of third flange bolt holes 69 penetrating in the extending direction of the center axis C ２ The third flange bolt holes 69 are formed at the same positions as the protrusions 67a in the circumferential direction. The third flange portion 67 is formed between two protrusions 67a adjacent to each other in the circumferential direction and is spaced apart from each other in the circumferential direction about the central axis C. ２The recess 67b is recessed radially outward from the center and has a plurality of recesses 67b provided at intervals in the circumferential direction.

[0045] In the first flange portion 110, the shape of the outer edge of the first flange portion 110 that forms the recess 113, the radial dimension of the first flange portion 110, and the circumferential position of the recess 113 are set so that the first flange portion 110 passes through the through hole 68 of the third flange portion 67 of the top hat part 60 without interfering with the protrusion 67 a of the third flange portion 67. In other words, the circumferential position of the recess 113 is set to be the same as the circumferential position of the protrusion 67 a of the third flange portion 67.

[0046] Similarly, in the third flange portion 67 of the top hat part 60, the shape of the outer edge of the through hole 68 that forms the recess 67b, the radial dimension of the through hole 68, and the circumferential position of the recess 67b are set so that the first flange portion 110 does not interfere with the protrusion 112 of the first flange portion 110 when passing through the through hole 68. In other words, the circumferential position of the recess 67b is set to be the same as the circumferential position of the protrusion 112 of the first flange portion 110.

[0047] (Regarding the female thread portion 69a of the third flange bolt hole 69) In the combustor 4 according to one embodiment, as shown in Figures 6, 7, 8, and 12, the third flange bolt hole 69 is formed with a female thread portion 69a that can be threaded onto the male thread portion 82a of the bolt 82.

[0048] When the second flange portion 120 and the third flange portion 67 are joined with the bolts 82, as described above, the combustion liner 36 and the fuel supply pipe 101 fixed to the combustion liner 36 are attached to the casing 20. Then, after the top hat portion 60 is inserted into the combustor insertion hole 20h formed in the casing 20, the male thread portions 82a of the bolts 82 must be screwed into the female thread portions 122 formed in the second flange bolt holes 121 of the second flange portion 120 shown in, for example, Figures 6 and 7 . For this reason, after the top hat section 60 is inserted into the combustor insertion hole 20h, it is relatively difficult to insert the bolt 82 into the third flange bolt hole 69 of the third flange portion 67, which is located behind the opening 65a of the second cylindrical portion 65, and to thread the male thread portion 82a of the bolt 82 into the female thread portion 122 (see FIGS. 6 and 7 ) formed in the second flange bolt hole 121 of the second flange portion 120 or the nut 125 (see FIG. 8 ) for joining the second flange portion 120. Furthermore, if the top hat section 60 is inserted into the combustor insertion hole 20h in a state in which the bolt 82 is inserted into the third flange bolt hole 69 in which the female thread portion 69a is not formed, there is a risk that the bolt 82 will fall out of the third flange bolt hole 69.

[0049] 7 , in the combustor 4 according to one embodiment, when the second flange portion 120 and the third flange portion 67 are joined together, the male thread portions 82 a of the bolts 82 can be threaded into the female thread portions 69 a of the third flange bolt holes 69 in advance. This reduces the possibility that the bolts 82 will fall off from the third flange portion 67 during joining of the second flange portion 120 and the third flange portion 67, thereby facilitating the operation of joining the second flange portion 120 and the third flange portion 67.

[0050] 6 and 7, a female thread portion 122 that can be threaded onto the male thread portion 82a of the bolt 82 is formed on the second flange portion 120. This eliminates the need for a separate nut when joining the second flange portion 120 and the third flange portion 67 with the bolt 82, thereby reducing the number of parts.

[0051] 8 has a nut 125, which is a separate member from the second flange portion 120, and a female thread portion 126 that can be threaded onto the male thread portion 82a of the bolt 82. The nut 125 shown in FIG. 8 is fixed to the fuel supply pipe 101 in advance.

[0052] 9 and 10 , in the combustor 4 according to one embodiment, the fourth flange portion 154 of the connecting pipe 152 has a fourth flange bolt hole 155 through which a bolt 81 is inserted to connect the first flange portion 110 of the fuel supply pipe 101 and the fourth flange portion 154. The fourth flange bolt hole 155 has a female thread portion 156 formed therein that can be threadedly engaged with the male thread portion 81 a of the bolt 81.

[0053] When the first flange portion 110 and the fourth flange portion 154 are joined together with the bolts 81, as described above, the combustion liner 36 and the fuel supply pipe 101 fixed to the combustion liner 36 are attached to the casing 20. Then, after the top hat portion 60 is inserted into the combustor insertion hole 20h formed in the casing 20, the male thread portions 81a of the bolts 81 must be threaded into the nuts 115 that are located on the back surface of the first flange portion 110 as seen from the opening 65a and are fixed by welding to the first flange portion 110 or the side portion of the fuel supply pipe 101. For this reason, after the top hat portion 60 is inserted into the combustor insertion hole 20h, it is relatively difficult to insert the bolts 81 into the fourth flange bolt holes 155 of the fourth flange portion 154, which are located behind the opening 65a of the second tubular portion 65, and the first flange bolt holes 111 of the first flange portion 110, and then thread the male thread portions 81a of the bolts 81 into the nuts 115. Furthermore, if the connecting pipe 152 is inserted into the second tubular portion 65 with the bolt 81 inserted into the fourth flange bolt hole 155, which does not have a female thread portion 156, there is a risk that the bolt 81 will fall out of the fourth flange bolt hole 155.

[0054] 10 , in the combustor 4 according to one embodiment, when the first flange portion 110 and the fourth flange portion 154 are joined together, the male thread portions 81 a of the bolts 81 can be threaded into the female thread portions 156 of the fourth flange bolt holes 155 in advance. This reduces the possibility that the bolts 81 will fall off from the fourth flange portion 154 during the joining of the first flange portion 110 and the fourth flange portion 154, thereby facilitating the operation of joining the first flange portion 110 and the fourth flange portion 154.

[0055] 4 and 5, the combustor 4 according to one embodiment includes a flow guide 90 for guiding fuel air supplied to burners having axial fuel nozzles, i.e., the first combustion burner 38 and the second combustion burner 44. The flow guide 90 according to one embodiment has a flow guide 90 for guiding a gap between the outer circumferential surface 64b of the first cylindrical portion 64 and the inner circumferential surface 20i of the casing 20 opposed to the outer circumferential surface 64b, the flow guide 90 being aligned with the central axis C. １ from the other side in the extending direction (the lower right side in FIGS. 2 and 3 ) of the combustor casing 32 and serves to guide the combustion air in the combustor casing 32 toward the air passage 54 .

[0056] The flow guide 90 according to the embodiment has a central axis C １ The flow guide 90 extends toward one side and the other side in the circumferential direction about the center. The flow guide 90 according to one embodiment is also provided in the region where the second cylindrical portion 65 is present in the circumferential direction. That is, as shown in FIGS. 3, 6, 7, and 8, a portion of the flow guide 90 is attached to the fuel supply pipe 101. In the example shown in FIGS. 3, 6, and 7, a portion of the flow guide 90 is attached to the center axis C of the second flange portion 120. ２ 8, a part of the flow guide 90 is attached to a nut 125 that is fixed to the fuel supply pipe 101 in advance.

[0057] In this manner, in the combustor 4 according to one embodiment, the combustion air flowing near the fuel supply pipe 101 can be guided by a part of the flow guide 90 attached to the fuel supply pipe 101 .

[0058] 3, 6, and 7, the surface 127 of the second flange portion 120 forms a part of the flow guide 90. This allows the surface 127 of the second flange portion 120 to guide the combustion air flowing near the fuel supply pipe 101.

[0059] The combustor 4 according to one embodiment includes the fuel supply pipe assembly 100 including the fuel supply pipe 101 and the top hat portion 60, the combustion liner 36, the third fuel nozzle 70 which is a side fuel nozzle, and the first fuel nozzle 40 and the second fuel nozzle 46 which are axial fuel nozzles. This reduces the time required for attaching the combustion liner 36 to the turbine 6, and therefore reduces the time required for attaching the combustor 4 to the turbine 6.

[0060] A gas turbine 1 according to one embodiment includes the compressor 2, the combustor 4 configured as described above, and a turbine 6 configured to be driven by combustion gas from the combustor 4. This reduces the time required for attaching the combustor 4 to the turbine 6, thereby reducing the time required for assembling the gas turbine 1.

[0061] 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.

[0062] The contents described in each of the above 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 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 a fuel supply pipe 101 for supplying fuel to the side fuel nozzle (third fuel nozzle 70), and a top hat portion 60 of the gas turbine combustor 4. The fuel supply pipe 101 includes a first flange portion 110 that can be coupled to a fuel pipe 150 that supplies fuel to the fuel supply pipe 101, and a second flange portion 120 that can be coupled to the top hat portion 60. The top hat portion 60 is a fuel nozzle different from the side fuel nozzle (third fuel nozzle 70) and is arranged in a direction parallel to the axial direction (center axis C) of the combustion liner 36. １ At least one axial fuel nozzle (first fuel nozzle 40, second fuel nozzle 46) extending in the axial direction (direction of extension of central axis C) is disposed therein. １ a first cylindrical portion 64 extending in the axial direction (the direction of extension of the central axis C), and a second cylindrical portion 65 provided on the outer circumferential side of the first cylindrical portion 64 and extending in the axial direction (the direction of extension of the central axis C). １ the second cylindrical portion 65 extending in the axial direction (the central axis C １ a top hat flange portion 62 for attaching the top hat portion 60 to the casing 20 of the gas turbine 1; and a second cylindrical portion 65 extending in the axial direction (the central axis C). １ Extending direction, central axis C ２ The first flange portion 110 has a third flange portion 67 provided at the other end in the axial direction (the direction of extension of the center axis C) and connectable to the second flange portion 120. When the second flange portion 120 is connected to the third flange portion 67, the first flange portion 110 is connected to the third flange portion 67 in the axial direction (the direction of extension of the center axis C). １ Extending direction, central axis C ２ The flange 62 is located between the top hat flange 62 and the third flange 67 in the extending direction of the flange 62 .

[0063] According to the configuration (1) above, the first flange portion 110 and the second flange portion 120 are arranged in the axial direction (the central axis C １ Extending direction, central axis C ２2 and 3 ) in the direction of extension of the combustion liner 36, the length of the fuel supply pipe 101 can be made relatively short. This makes it easier to route the combustion liner 36 inside the casing 20, and reduces the time required to attach the combustion liner 36 to the turbine 6.

[0064] (2) In some embodiments, in the configuration of (1) above, the axial direction (central axis C １ Extending direction, central axis C ２ The end portion on one side in the extending direction of the flange 62 may be an opening 65 a that opens to the surface 62 a on the one side of the top hat flange portion 62 .

[0065] According to the configuration (2) above, the piping (connecting pipe 152) for supplying fuel to the fuel supply pipe 101 can be inserted into the second cylindrical portion 65 through the opening 65a and connected to the fuel supply pipe 101.

[0066] (3) In some embodiments, in the configuration of (1) or (2) above, the third flange portion 67 may have a through-hole 68 through which the fuel supply pipe 101 can be inserted.

[0067] According to the configuration (3) above, a pipe (connecting pipe 152 ) for supplying fuel to the fuel supply pipe 101 can be connected to the fuel supply pipe 101 inserted through the through hole 68 .

[0068] (4) In some embodiments, in the configuration of (3) above, the through hole 68 may be such that the first flange portion 110 can be inserted therethrough.

[0069] According to the above configuration (4), the first flange portion 110 , which has the through-hole 68 inserted therethrough, can be connected to the pipe (connecting pipe 152 ) for supplying fuel to the fuel supply pipe 101 .

[0070] (5) In some embodiments, in any of the configurations (1) to (4) above, the third flange portion 67 may have a third flange bolt hole 69 through which a bolt 82 is inserted to connect the second flange portion 120 and the third flange portion 67. The third flange bolt hole 69 may have a female thread portion 69a formed therein that can be threaded onto the male thread portion 82a of the bolt 82.

[0071] According to the configuration of (5) above, when joining the second flange portion 120 and the third flange portion 67, the male thread portion 82a of the bolt 82 can be threaded into the female thread portion 69a of the third flange bolt hole 69 in advance. This reduces the possibility that the bolt 82 will fall off the third flange portion 67 during joining of the second flange portion 120 and the third flange portion 67, making it easier to join the second flange portion 120 and the third flange portion 67.

[0072] (6) In some embodiments, in any of the configurations (1) to (5) above, the fuel pipe 150 may include an external fuel pipe 151 outside the gas turbine combustor 4 and a connecting pipe 152 connecting the external fuel pipe 151 and the fuel supply pipe 101. The connecting pipe 152 is located downstream in the fuel flow direction (across the central axis C ２ 2 and 3 ) and can be coupled to the first flange portion 110. ２ It is preferable that one side in the extending direction of the top hat portion 60 (i.e., the upper left side in FIGS. 2 and 3 ) protrudes outside the top hat portion 60.

[0073] According to the configuration (6) above, by joining the first flange portion 110 and the fourth flange portion 154, the connecting pipe 152 can be connected to the fuel supply pipe 101. Furthermore, according to the configuration (6) above, the connecting pipe 152 and the external fuel pipe 151 can be connected outside the top hat part 60, which makes it easy to connect the connecting pipe 152 and the external fuel pipe 151.

[0074] (7) In some embodiments, in the configuration of (6) above, the fourth flange portion 154 may have a fourth flange bolt hole 155 through which a bolt 81 is inserted to connect the first flange portion 110 and the fourth flange portion 154. The fourth flange bolt hole 155 may have a female thread portion 156 formed therein that can be threaded onto the male thread portion 81 a of the bolt 81.

[0075] According to the configuration (7) above, when joining the first flange portion 110 and the fourth flange portion 154, the male thread portion 81 a of the bolt 81 can be threaded into the female thread portion 156 of the fourth flange bolt hole 155 in advance. This reduces the possibility that the bolt 81 will fall off the fourth flange portion 154 midway when joining the first flange portion 110 and the fourth flange portion 154, making it easier to join the first flange portion 110 and the fourth flange portion 154.

[0076] (8) In some embodiments, in any of the configurations (1) to (7) above, a flow guide 90 may be provided for guiding fuel air supplied to the burners (first combustion burner 38, second combustion burner 44) having axial fuel nozzles (first fuel nozzle 40, second fuel nozzle 46). A portion of the flow guide 90 may be attached to the fuel supply pipe 101.

[0077] According to the above configuration (8), the combustion air flowing near the fuel supply pipe 101 can be guided by a part of the flow guide 90 attached to the fuel supply pipe 101 .

[0078] (9) In some embodiments, in the configuration of (8), the downstream side of the fuel flow direction (the central axis C ２ The end face (surface 127) of the second flange portion 120 facing the other side in the extending direction (i.e., the lower right side in FIGS. 2 and 3) may form the above-mentioned part of the flow guide 90.

[0079] According to the above configuration (9), the downstream side of the fuel flow direction (the central axis C ２ The combustion air flowing near the fuel supply pipe 101 can be guided by the end face (surface 127) of the second flange portion 120 facing the other side in the extending direction (i.e., the lower right side in FIGS. 2 and 3).

[0080] (10) In some embodiments, in any of the configurations (1) to (9) above, the second flange portion 120 may be formed with a female thread portion 122 that can be threaded onto the male thread portion 82a of the bolt 82 for connecting the second flange portion 120 and the third flange portion 67.

[0081] According to the configuration (10) above, when joining the second flange portion 120 and the third flange portion 67 with the bolts 82, there is no need to prepare additional nuts, so the number of parts can be reduced.

[0082] (11) 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 (10), a combustion liner 36, a side fuel nozzle (third fuel nozzle 70), and at least one axial fuel nozzle (first fuel nozzle 40, second fuel nozzle 46).

[0083] According to the configuration (11) above, since the fuel supply pipe assembly 100 having any of the configurations (1) to (10) above is provided, the time required for the work of attaching the combustion liner 36 to the turbine 6 can be reduced. As a result, the time required for the work of attaching the gas turbine combustor 4 to the turbine 6 can be reduced.

[0084] (12) 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 (11) above, and a turbine 6 configured to be driven by combustion gas from the gas turbine combustor 4.

[0085] According to the configuration of (12) above, the gas turbine combustor 4 having the configuration of (11) above is included, so that the time required for an operation of attaching the gas turbine combustor 4 to the turbine 6 can be reduced. As a result, the time required for an operation of assembling the gas turbine 1 can be reduced.

[0086] REFERENCE SIGNS LIST 1 Gas turbine 2 Compressor 4 Gas turbine combustor (combustor) 6 Turbine 20 Casing 20h Combustor insertion hole 32 Combustor casing 36 Combustor liner (combustor liner) 38 First combustion burner 40 First fuel nozzle 44 Second combustion burner 46 Second fuel nozzle 48 Inner cylinder 50 Transition piece 52 Outer cylinder 60 Top hat portion 62 Top hat flange portion 62a Surface 64 First tubular portion 64a End portion 65 Second tubular portion 65a Opening 67 Third flange portion 67a Projection portion 67b Recessed portion 68 Through hole 69 Third flange bolt hole 69a Female thread portion 70 Third fuel nozzle 81 Bolt 81a Male thread portion 82 Bolt 82a Male thread portion 90 Flow guide 100 Fuel supply pipe assembly 101 Fuel supply pipe 110 First flange portion 111 First flange bolt hole 112 Protrusion 113 Recess 115 Nut 120 Second flange portion 121 Second flange bolt hole 122 Female thread portion 125 Nut 126 Female thread portion 127 Surface 150 Fuel pipe 151 External fuel pipe 152 Connecting pipe 154 Fourth flange portion 155 Fourth flange bolt hole 156 Female thread portion

Claims

1. A fuel supply pipe assembly for supplying fuel to a side fuel nozzle provided on a side of a combustion liner of a gas turbine combustor, comprising: a fuel supply pipe for supplying the fuel to the side fuel nozzle; and a top hat portion of the gas turbine combustor, wherein the fuel supply pipe comprises: a first flange portion coupleable to a fuel piping for supplying the fuel to the fuel supply pipe; and a second flange portion coupleable to the top hat portion, and the top hat portion has: a first cylindrical portion extending in the axial direction, and having at least one axial fuel nozzle disposed therein, the axial fuel nozzle being different from the side fuel nozzle and extending in the axial direction of the combustion liner; a second cylindrical portion provided on an outer circumferential side of the first cylindrical portion and extending in the axial direction; a top hat flange portion provided at one end of the first cylindrical portion in the axial direction, for attaching the top hat portion to a casing of a gas turbine; and a third flange portion provided at the other end of the second cylindrical portion in the axial direction, coupleable to the second flange portion, the first flange portion is located between the top hat flange portion and the third flange portion in the axial direction when the second flange portion is coupled to the third flange portion.

2. A fuel supply pipe assembly as set forth in claim 1, wherein said one axial end of said second cylindrical portion is an opening that opens into said one side surface of said top hat flange portion.

3. The fuel supply pipe assembly according to claim 1 or 2, wherein the third flange portion has a through hole through which the fuel supply pipe can be inserted.

4. The fuel supply pipe assembly according to claim 3, wherein the first flange portion can be inserted through the through hole.

5. A fuel supply pipe assembly as described in claim 1 or 2, wherein the third flange portion has a third flange bolt hole through which a bolt for joining the second flange portion and the third flange portion is inserted, and the third flange bolt hole is formed with a female thread portion which can be screwed into the male thread portion of the bolt.

6. A fuel supply pipe assembly according to claim 1 or 2, wherein the fuel piping includes an external fuel piping outside the gas turbine combustor and a connecting pipe connecting the external fuel piping and the fuel supply pipe, the connecting pipe is provided at an end portion on a downstream side in a flow direction of the fuel and has a fourth flange portion connectable to the first flange portion, and an end portion on an upstream side in the flow direction of the connecting pipe protrudes outside the top hat portion.

7. A fuel supply pipe assembly as set forth in claim 6, wherein the fourth flange portion has a fourth flange bolt hole through which a bolt for joining the first flange portion and the fourth flange portion is inserted, and the fourth flange bolt hole is formed with a female thread portion which can be screwed into the male thread portion of the bolt.

8. The fuel supply pipe assembly according to claim 1 or 2, further comprising a flow guide for guiding fuel air supplied to a burner having said axial fuel nozzle, a portion of said flow guide being attached to said fuel supply pipe.

9. The fuel supply pipe assembly according to claim 8, wherein an end face of said second flange portion facing the downstream side in the flow direction of said fuel constitutes said part of said flow guide.

10. A fuel supply pipe assembly as set forth in claim 1 or 2, wherein the second flange portion is formed with a female thread portion that can be screwed into a male thread portion of a bolt for connecting the second flange portion and the third flange portion.

11. A gas turbine combustor comprising: a fuel supply pipe assembly according to claim 1 or 2; said combustion liner; said side fuel nozzle; and said at least one axial fuel nozzle.

12. A gas turbine comprising: a compressor; a gas turbine combustor according to claim 11; and a turbine configured to be driven by combustion gas from the gas turbine combustor.

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