Fuel supply pipe assembly, gas turbine combustor and gas turbine

Abstract

To provide a fuel supply pipe assembly capable of supplying fuel at a required flow rate with a fuel nozzle provided at a side part of a combustion cylinder of a gas turbine combustor.SOLUTION: A fuel supply pipe assembly according to at least one embodiment of the present disclosure is configured to supply fuel to a fuel nozzle provided at a side part of a combustion cylinder of a gas turbine combustor, and comprises a fuel supply pipe for supplying the fuel to the fuel nozzle, a first flange part which can be coupled to a flange part of fuel piping for supplying the fuel to the fuel supply pipe, and a second flange part which can be coupled to a top hat part of the gas turbine combustor. The first flange part has a plurality of projections which are provided circumferentially at intervals and protrude radially outward, and a plurality of bolt holes which penetrate the first flange part axially. The plurality of first bolt holes are formed at the same positions as circumferential positions of the projections, respectively.SELECTED DRAWING: Figure 3

Description

Technical Field

[0001] The present disclosure relates to a fuel supply pipe assembly, a gas turbine combustor, and a gas turbine.

Background Art

[0002] There is known a gas turbine combustor capable of supplying fuel into a combustion cylinder from a fuel nozzle provided on a side portion of the combustion cylinder of the gas turbine combustor. In such a gas turbine combustor, a fuel supply pipe for supplying fuel to the fuel nozzle penetrates through a mounting ring for fixing the gas turbine combustor to a vehicle compartment (see, for example, Patent Document 1).

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] For example, when a flange portion is provided at an upstream end of the fuel supply pipe and configured to be coupled to a flange portion of a fuel pipe for supplying fuel to the fuel supply pipe, it is necessary to insert the flange portion at the upstream end of the fuel supply pipe into a through-hole of the mounting ring. Therefore, the size of the through-hole of the mounting ring must be such that the flange portion at the upstream end of the fuel supply pipe can be inserted therethrough.

[0005] From the perspective of ensuring the flow rate of fuel supplied to the fuel nozzle, it is necessary to ensure a certain diameter of the fuel supply pipe. However, increasing the diameter of the fuel supply pipe also increases the diameter of the flange at the upstream end of the fuel supply pipe. However, the size of the through-hole of the mounting ring is constrained by the size of the vehicle compartment, combustion chamber, etc., to which the mounting ring is attached, making it difficult to increase its size. Therefore, using standard flanges makes it difficult to increase the diameter of the fuel supply pipe, making it difficult to ensure the flow rate of fuel supplied to the fuel nozzle.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure aims to provide a fuel supply pipe assembly capable of supplying a required flow rate of fuel through a fuel nozzle provided on the side of the combustion chamber of a gas turbine combustor, and a gas turbine combustor and gas turbine equipped with the fuel supply pipe assembly. [Means for solving the problem]

[0007] (1) A fuel supply pipe assembly according to at least one embodiment of the present disclosure is A fuel supply pipe assembly for supplying fuel to a fuel nozzle located on the side of the combustion chamber of a gas turbine combustor, A fuel supply pipe for supplying the fuel to the fuel nozzle, A first flange portion that can be connected to the flange portion of a fuel pipe for supplying the fuel to the fuel supply pipe, A second flange portion that can be connected to the top hat portion of the gas turbine combustor, Equipped with, The first flange portion has multiple projections that are spaced apart in the circumferential direction and protrude radially outward, and multiple first bolt holes that penetrate the first flange portion in the axial direction. Each of the aforementioned plurality of first bolt holes is formed at the same position as the circumferential position of the projection.

[0008] (2) A gas turbine combustor according to at least one embodiment of the present disclosure is A fuel supply pipe assembly having the configuration described in (1) above, The combustion chamber and, The fuel nozzle and, The aforementioned top hat portion, Equipped with, The top hat portion includes a top hat body having a through hole through which the first flange portion can pass in the axial direction. The top hat body has a plurality of top hat projections provided at intervals in the circumferential direction and projecting radially inward toward the center of the through hole, and a plurality of third bolt holes that penetrate the top hat body in the axial direction. Each of the aforementioned third bolt holes is formed at the same position as the circumferential position of the top hat projection.

[0009] (3) A gas turbine according to at least one embodiment of the present disclosure is Compressor and, A gas turbine combustor with the configuration described in (2) above, A turbine configured to be driven by combustion gas from the aforementioned gas turbine combustor, It is equipped with. [Effects of the Invention]

[0010] According to at least one embodiment of the present disclosure, a fuel nozzle provided on the side of the combustion chamber of a gas turbine combustor can supply fuel at the required flow rate. [Brief explanation of the drawing]

[0011] [Figure 1] This is a schematic diagram of a gas turbine according to one embodiment. [Figure 2] This is a schematic diagram showing the combustor and turbine inlet portion of a gas turbine according to one embodiment. [Figure 3] This is a schematic cross-sectional view of a combustor of a gas turbine according to one embodiment. [Figure 4A] This is a view of the first flange portion of the fuel supply pipe assembly from the axial upstream side. [Figure 4B] This is a view of the second flange portion of the fuel supply pipe assembly from the axial upstream side. [Figure 4C] This is a diagram showing the through holes of the flange portion of the top hat portion and the third bolt holes provided in the flange portion when viewed from the upstream side in the axial direction. [Figure 4D] This is an enlarged view of the vicinity of the second flange portion of the fuel supply pipe assembly in FIG. 3.

Embodiments for Carrying out the Invention

[0012] Hereinafter, some embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described as embodiments or shown in the drawings are not intended to limit the scope of the present disclosure, but are merely illustrative examples. For example, expressions representing relative or absolute arrangements such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric", or "coaxial" not only strictly represent such arrangements, but also represent a state of being relatively displaced with tolerances or with angles and distances such that the same function can be obtained. For example, expressions representing that things such as "identical", "equal", and "homogeneous" are in an equal state not only strictly represent an equal state, but also represent a state in which there are tolerances or differences such that the same function can be obtained. For example, expressions representing shapes such as a rectangular shape or a cylindrical shape not only represent shapes such as a rectangular shape or a cylindrical shape in a geometrically strict sense, but also represent shapes including concave and convex portions, chamfered portions, etc. within a range where the same effect can be obtained. On the other hand, the expressions "comprising", "having", "including", or "possessing" one component are not exclusive expressions that exclude the existence of other components.

[0013] First, a gas turbine, which is an example of the application target of the 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 Figure 1, the gas turbine 1 comprises 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 stationary blades 16 fixed to the compressor casing 10 side, and a plurality of rotor blades 18 mounted on the rotor 8 so as to be arranged alternately with respect to the stationary blades 16. Air taken in from the air intake 12 is supplied to the compressor 2, and this air is compressed by passing through multiple stationary blades 16 and multiple rotor blades 18 to become high-temperature, high-pressure compressed air.

[0015] The combustor 4 is supplied with fuel and compressed air generated by the compressor 2. In the combustor 4, the fuel is burned, and combustion gas, which is the working fluid for the turbine 6, is generated. As shown in Figure 1, the gas turbine 1 has multiple combustors 4 arranged circumferentially around the rotor 8 within the casing 20.

[0016] The turbine 6 has a combustion gas passage 28 formed by the turbine casing 22, and includes a plurality of stator blades 24 and rotor blades 26 provided in the combustion gas passage 28. The stator blades 24 and rotor blades 26 of the turbine 6 are located downstream of the combustor 4 with respect to the flow of combustion gases. The stator blades 24 are fixed to the turbine casing 22, and multiple stator blades 24 arranged along the circumferential direction of the rotor 8 constitute a stator blade row. The rotor blades 26 are mounted on the rotor 8, and multiple rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator blade row and the rotor blade row are arranged alternately in the axial direction of the rotor 8. In the turbine 6, combustion gases from the combustor 4 flow into the combustion gas passage 28 and pass through multiple stationary blades 24 and multiple rotor blades 26, causing the rotor 8 to rotate around axis O. This drives a generator connected to the rotor 8, generating electricity. After driving the turbine 6, the combustion gases are discharged to the outside through the exhaust chamber 30.

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

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

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

[0020] The first combustion burner 38 is positioned along the direction of the central axis C1 of the combustion cylinder 36 (i.e., the axial direction of the combustor 4) and has a first fuel nozzle 40 for injecting fuel and a first burner cylinder 41 positioned to surround the first fuel nozzle 40. Fuel is supplied to the first fuel nozzle 40 through a first fuel port 42.

[0021] The second combustion burner 44 has a second fuel nozzle 46 for injecting fuel and a second burner cylinder 47 positioned to surround the second fuel nozzle 46. Fuel is supplied to the second fuel nozzle 46 through a second fuel port 43.

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

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

[0024] The first combustion burner 38 described above may be a burner for generating a diffusion combustion flame, and the second combustion burner 44 may be a burner for burning a premixed gas to generate a premixed combustion flame. In other words, in the second combustion burner 44, the fuel from the second fuel port 43 and compressed air are premixed, and this premixed gas mainly forms a swirling flow by the swirler 49 and flows into the combustion chamber 36. Also, the compressed air and the fuel injected from the first combustion burner 38 via the first fuel port 42 are mixed in the combustion chamber 36, ignited by an ignition means (not shown), and burned, generating combustion gases. At this time, a portion of the combustion gases diffuses into the surroundings with a flame, igniting and burning the premixed gas that has flowed into the combustion chamber 36 from each of the second combustion burners 44. In other words, the diffuse combustion flame from the fuel injected from the first combustion burner 38 can maintain the flame for stable combustion of the premixed gas (premixed fuel) from the second combustion burner 44.

[0025] In this way, the combustion gas generated by the combustion of fuel in the combustor 4 flows into the turbine 6 through the outlet 51 of the combustor 4 located at the downstream end of the tailpipe 50.

[0026] (Third fuel nozzle 70) The combustor 4 is equipped with a third fuel nozzle 70 located on the side of the combustion chamber 36. In other words, the third fuel nozzle 70 is a fuel nozzle for supplying fuel into the combustion chamber 36 from the side of the combustion chamber 36. Furthermore, multiple third fuel nozzles 70 may be provided along the circumferential direction (i.e., the circumferential direction of the combustor 4) centered on the central axis C1 of the combustion cylinder 36. The third fuel nozzles 70 are fixed to the tailpipe 50, for example. When fuel is injected into the combustion chamber 36 from the third fuel nozzle 70, the combustion air in the combustion chamber 36 and the injected fuel mix and burn. By injecting fuel into the combustion chamber 36 from the third fuel nozzle 70, fuel can be supplied to the secondary combustion zone in the transition section downstream of the primary combustion region where fuel from the first fuel nozzle 40 and the second fuel nozzle 46 burns. This reduces nitrogen oxides (NOx). x This allows for improved combustion efficiency while suppressing the generation of (fuel).

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

[0028] In one embodiment, the combustor 4 includes a fuel supply pipe assembly 100 for supplying fuel to a third fuel nozzle 70. The fuel supply pipe assembly 100 in one embodiment includes a fuel supply pipe 101 for supplying fuel to the third fuel nozzle 70, a first flange portion 110 that can be connected to a flange portion of a fuel pipe (not shown) for supplying fuel to the fuel supply pipe 101, and a second flange portion 120 that can be connected to a top hat portion 60 of the combustor 4, which will be described later. In one embodiment of the fuel supply pipe assembly 100, fuel supplied from a fuel pipe (not shown) via the first flange portion 110, which is also the third fuel port 74, flows through the fuel supply pipe 101 and is supplied to the third fuel nozzle 70. In one embodiment of the combustor 4, one fuel supply pipe assembly 100 is provided for each combustor 4. If 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. A fuel supply pipe assembly 100 according to one embodiment will be described in detail later.

[0029] (Top hat section 60) As shown in Figures 2 and 3, a combustor 4 according to one embodiment includes a flange portion 62 attached to the casing 20 and an annular extension portion 64 extending from the flange portion 62 along the axial direction of the combustor 4. In one embodiment of the combustor 4, the portion composed of the flange portion 62 and the extension portion 64 is sometimes referred to as the top hat portion 60 due to its shape. In one embodiment, the top hat portion 60 is a bottomed cylindrical member provided to close the combustor insertion hole 20h formed in the casing 20.

[0030] As shown in Figures 2 and 3, the flange portion 62 has a shape that protrudes radially outward from the combustor 4 and is fixed to the casing 20 by bolts 59. The flange portion 62 is also referred to as the top hat body.

[0031] The extension 64 has a cylindrical shape that extends from the flange portion 62 toward the internal space of the casing 20 along the axial direction of the combustor 4. In one embodiment, the extension 64 is located radially inward from the casing 20.

[0032] As shown in Figures 2 and 3, the air passage 54 may be at least partially formed by the extension 64. That is, the extension 64 may include an air passage forming portion 66 (outer cylinder 52) that forms the air passage 54.

[0033] As shown in Figure 3, in the gas turbine 1 according to one embodiment, in the region of the outer cylinder 52 located relatively radially outward from the axis O of the rotor 8, the outer surface 52a of the outer cylinder 52 is spaced apart from the inner surface 20i of the combustor insertion hole 20h. As a result, in the gas turbine 1 according to one embodiment, a void 33 is formed between the outer surface 52a of the outer cylinder 52 and the inner surface 20i of the combustor insertion hole 20h in the region located relatively radially outward from the axis O of the rotor 8. The void 33 is part of the combustor chamber 32 defined by the casing 20 and is filled with compressed air generated by the compressor 2 (see Figure 1) during operation of the gas turbine 1.

[0034] In one embodiment of the gas turbine 1, the fuel supply pipe 101 of the fuel supply pipe assembly 100 is located within the cavity 33. The fuel supply pipe assembly 100 has a second flange portion 120 attached to the flange portion 62 of the top hat portion 60 within the combustor casing 32. A through-hole 65 is formed in the flange portion 62 of the top hat portion 60, passing through the flange portion 62 along the central axis C1 of the combustion cylinder 36. A fuel supply pipe 101 is inserted through the through-hole 65.

[0035] Furthermore, in order to prevent compressed air in the cavity 33 from leaking out of the casing 20 through the through hole 65, the second flange portion 120 of the fuel supply pipe assembly 100 abuts against the flange portion 62 of the top hat portion 60 from the inside of the casing 20, that is, from the axial downstream side of the combustion cylinder 36, thereby sealing the through hole 65. The second flange portion 120 of the fuel supply pipe assembly 100 is fixed to the flange portion 62 of the top hat portion 60 by bolts 151 at multiple locations in the circumferential direction around the central axis C2 of the fuel supply pipe 101, as will be described later.

[0036] In the following description, with respect to the fuel supply pipe assembly 100, the axial direction of the fuel supply pipe 101, which is the direction in which the central axis C2 of the fuel supply pipe 101 extends, will also be simply referred to as the axial direction. Similarly, in the following description, with respect to the fuel supply pipe assembly 100, the circumferential direction of the fuel supply pipe 101, which is the circumferential direction with respect to the central axis C2, will also be simply referred to as the circumferential direction, and the radial direction of the fuel supply pipe 101, which is the radial direction with respect to the central axis C2, will also be simply referred to as the radial direction. Furthermore, in at least a portion of the fuel supply pipe 101, the central axis C2 of the fuel supply pipe 101 is parallel to the central axis C1 of the combustion cylinder 36. Within the axial direction of the fuel supply pipe 101, the upstream side of the fuel flow within the fuel supply pipe 101 is defined as the axial upstream side, and the downstream side of the fuel flow within the fuel supply pipe 101 is defined as the axial downstream side.

[0037] Figure 4A is a view of the first flange portion 110 of the fuel supply pipe assembly 100 from the axial upstream side, and corresponds to the view indicated by arrow AA in Figure 3. In Figure 4A, the through hole 65 of the flange portion 62 of the top hat portion 60 and the third bolt hole 68 provided in the flange portion 62, which will be described later, are shown by dashed lines when viewed from the axial upstream side. Figure 4B is a view of the second flange portion 120 of the fuel supply pipe assembly 100 from the axial upstream side, and corresponds to the view taken by arrow B in Figure 3. In Figure 4B, the through hole 65 of the flange portion 62 of the top hat portion 60 and the shape of the first flange portion 110 when viewed from the axial direction are represented by dashed lines. Figure 4C shows the through-hole 65 in the flange portion 62 of the top hat portion 60 and the third bolt hole 68 provided in the flange portion 62, as viewed from the axial upstream side, and corresponds to the view indicated by arrow C in Figure 3. Figure 4D is an enlarged view of the vicinity of the second flange portion 120 of the fuel supply pipe assembly 100 in Figure 3.

[0038] (Regarding the relationship between the first flange portion 110, the second flange portion 120, and the flange portion 62) In one embodiment of the fuel supply pipe assembly 100, when attaching the top hat portion 60 of the combustor 4 to the casing 20, it is necessary to insert and pass the first flange portion 110 through the through hole 65 provided in the top hat portion 60. Therefore, the size of the through hole 65 provided in the top hat portion 60 must be large enough for the first flange portion 110 to pass through. From the perspective of ensuring the flow rate of fuel supplied to the third fuel nozzle 70, it is necessary to secure a certain diameter for the fuel supply pipe 101. However, if the diameter of the fuel supply pipe 101 is increased, the diameter of the first flange portion 110 will also increase. However, the size of the through-hole 65 in the top hat section 60 is constrained by the position of the casing 20 to which the top hat section 60 is attached, and the radial size of the cavity 33, making it difficult to enlarge. Therefore, if a standard flange is used for the first flange section 110, it becomes difficult to enlarge the diameter of the fuel supply pipe 101, making it difficult to secure the flow rate of fuel supplied to the third fuel nozzle 70. Furthermore, as mentioned above, to prevent leakage to the outside of the casing 20, the flange portion 62 of the top hat portion 60 and the second flange portion 120 of the fuel supply pipe assembly 100 are connected by a plurality of bolts 151. However, the pitch circle diameter PCD3 of the plurality of bolt holes (third bolt holes 68) for attaching the bolts 151 is subject to the same constraints as in the case of the through holes 65, making it difficult to increase its size.

[0039] In other words, in the combustor 4 according to one embodiment, it is desirable to increase the diameter of the fuel supply pipe 101 in order to secure the necessary fuel flow rate at the third fuel nozzle 70, and to increase the pitch circle diameter PCD1 of the bolt holes (first bolt holes) 112 of the first flange portion 110. However, as described above, there are circumstances that make it difficult to increase the diameter of the first flange portion 110. Furthermore, in the combustor 4 according to one embodiment, as described above, there are circumstances that make it difficult to increase the pitch circle diameter PCD3 of the multiple third bolt holes 68 for attaching the bolts 151.

[0040] Therefore, in the combustor 4 according to one embodiment, as shown in Figures 4A to 4C, the first flange portion 110 of the fuel supply pipe assembly 100 is provided with a plurality of protrusions 111 that are spaced apart in the circumferential direction and project radially outward. The first flange portion 110 is provided with a plurality of first bolt holes 112 that penetrate the first flange portion 110 axially and are spaced apart in the circumferential direction for connecting to the flange portion of a fuel pipe (not shown) for supplying fuel to the fuel supply pipe 101 with bolts (not shown). In the combustor 4 according to one embodiment, as shown in Figures 4A to 4C, the plurality of first bolt holes 112 are each formed at the same position as the circumferential position of the projection 111. As shown in Figure 4A, the projection 111 protrudes radially in the radial direction. Therefore, when viewed from the axial direction, the first flange portion 110 has a petal shape in which the projection 111 protrudes radially outward in a petal-like manner.

[0041] Furthermore, in the combustor 4 according to one embodiment, in order to reduce the size of the through-hole 65 in the flange portion 62 of the top hat portion 60 to the extent that the first flange portion 110 of the fuel supply pipe assembly 100 can pass through, the shape of the through-hole 65 when viewed from the axial direction is made to be the same petal shape as the first flange portion 110. That is, the flange portion 62 is provided in multiple locations spaced apart in the circumferential direction and has top hat projections 67 that project radially inward toward the center of the through-hole 65. The flange portion 62 is provided with multiple third bolt holes 68 for attaching bolts 151, spaced apart in the circumferential direction. In the combustor 4 according to one embodiment, as shown in Figures 4A and 4C, the multiple third bolt holes 68 are formed at the same circumferential positions as the top hat projection 67. Multiple third bolt holes 68 are through which bolts 151 are inserted.

[0042] The first flange portion 110 of the fuel supply pipe assembly 100 has a plurality of recesses 113 that are formed between two adjacent protrusions 111 in the circumferential direction, recessed radially inward, and spaced apart in the circumferential direction. In the first flange portion 110, the shape of the outer edge of the first flange portion 110 that forms the recesses 113, the radial dimensions of the first flange portion 110, and the circumferential position of the recesses 113 are set so that when the first flange portion 110 passes through the through hole 65 of the flange portion 62 of the top hat portion 60, it passes radially inward of the top hat protrusion 67 of the flange portion 62 without interfering with the top hat protrusion 67 of the flange portion 62. In other words, the circumferential position of the recesses 113 is set to be the same as the circumferential position of the top hat protrusion 67 of the flange portion 62.

[0043] The flange portion 62 of the top hat portion 60 is formed between two adjacent top hat protrusions 67 in the circumferential direction and is recessed radially outward, and has multiple top hat recesses 69 spaced apart in the circumferential direction. In the top hat portion 60, the shape of the outer edge of the through hole 65 forming the top hat recess 69, the radial dimensions of the through hole 65, and the circumferential position of the top hat recess 69 are set so that the first flange portion 110 of the fuel supply pipe assembly 100 does not interfere with the protrusion 111 of the first flange portion 110 when it passes through the through hole 65. In other words, the circumferential position of the top hat recess 69 is set to be the same as the circumferential position of the protrusion 111 of the first flange portion 110.

[0044] As shown in Figures 3 and 4D, the second flange portion 120 of the fuel supply pipe assembly 100 is located downstream in the axial direction from the first flange portion 110, and is provided so that the axially extending fuel supply pipe 101 passes through it. Established in Multiple second bolt holes 122 are provided at intervals in the circumferential direction. The pitch circle diameter PCD2 of the multiple second bolt holes 122 is equal to the pitch circle diameter PCD3 of the multiple third bolt holes 68 in the flange portion 62 of the top hat portion 60. Furthermore, the circumferential arrangement of the multiple second bolt holes 122 is the same as the circumferential arrangement of the third bolt holes 68. In other words, when viewed from the axial direction, the center positions of the multiple second bolt holes 122 and the center positions of the third bolt holes 68 are at the same location.

[0045] The second flange portion 120 is a disc-shaped plate flange and has an outer diameter larger than the bottom of the top hat recess 69 in the flange portion 62 of the top hat portion 60, that is, the largest diameter portion in the through hole 65.

[0046] Multiple second bolt holes 122 have female threads formed in them that can be screwed into the male threads of the bolts 151. As described above, the second flange portion 120 abuts against the flange portion 62 of the top hat portion 60 from the downstream side in the axial direction, thereby blocking the through hole 65. The second flange portion 120 is fixed to the flange portion 62 of the top hat portion 60 by bolts 151.

[0047] Thus, in the fuel supply pipe assembly 100 according to one embodiment, by providing a plurality of protrusions 111 on the first flange portion 110 and forming a plurality of first bolt holes 112 at the same circumferential positions as the protrusions 111, it is possible to set the positions of the first bolt holes 112 relatively radially outward while suppressing an increase in the size of the first flange portion 110 other than the protrusions 111. This ensures that the diameter of the fuel supply pipe 101 is large enough and that the flow rate of fuel supplied to the third fuel nozzle 70 is secured.

[0048] In one embodiment of the combustor 4, multiple top hat protrusions 67 are provided on the flange portion 62 of the top hat portion 60, and multiple third bolt holes 68 are formed at the same circumferential positions as the top hat protrusions 67, thereby allowing the positions of the third bolt holes 68 to be set relatively radially inward. This makes it easier to provide the third bolt holes 68 even when the size of the through hole 65 in the flange portion 62 is constrained by the position of the casing 20 to which the top hat portion 60 is attached, or the radial size of the cavity 33.

[0049] In the gas turbine 1 according to one embodiment, a fuel supply pipe assembly 100 according to one embodiment is provided, so that the diameter of the fuel supply pipe 101 can be ensured and the flow rate of fuel supplied to the third fuel nozzle 70 can be ensured.

[0050] In one embodiment of the fuel supply pipe assembly 100, as shown in Figure 4A, the size of the virtual circumscribed circle VC1 that circumscribes the plurality of first bolt holes 112 when viewed from the axial direction is preferably larger than the size of the virtual inscribed circle VI1 that circumscribes the innermost radial position in the plurality of recesses 113 when viewed from the axial direction. This allows the position of the first bolt hole 112 to be set relatively radially outward. Furthermore, by positioning the second bolt hole 122 of the second flange portion 120 at the circumferential position of the recess 113 of the first flange portion 110, the pitch circle diameter PCD2 of the second bolt hole 122 can be made relatively small. This allows the second flange portion 120 to be attached to the top hat portion 60 even if the size of the top hat portion 60 cannot be made too large.

[0051] In a fuel supply pipe assembly 100 according to one embodiment, as shown in Figure 4A, the size of the virtual circle passing through the centers of the plurality of first bolt holes 112, i.e., the pitch circle diameter PCD1 of the first bolt holes 112, may be the same as the size of the virtual inscribed circle VI1, or it may be larger than the size of the virtual inscribed circle VI1. This allows the position of the first bolt hole 112 to be set further radially outward. Also, by positioning the second bolt hole 122 of the second flange portion 120 at the circumferential position of the recess 113 of the first flange portion 110, the PCD2 of this second bolt hole 122 can be made even smaller. This makes it possible to attach the second flange portion 120 to the top hat portion 60 even if the size of the top hat portion 60 cannot be made much larger.

[0052] In the fuel supply pipe assembly 100 according to one embodiment, as shown in Figures 4B and 4D, the second flange portion 120 is the second flange portion 120 Established in It is preferable to have multiple second bolt holes 122. This allows the second flange portion 120 to be fixed to the top hat portion 60 of the combustor 4 by bolts 151 inserted through multiple second bolt holes 122.

[0053] In one embodiment of the fuel supply pipe assembly 100, as shown in Figure 4B, the size of the virtual inscribed circle VI2 that is inscribed in the plurality of second bolt holes 122 when viewed from the axial direction is preferably smaller than the size of the virtual circumscribed circle VC2 that is circumscribed around the projection 111 when viewed from the axial direction. In Figure 4B, the virtual inscribed circle VI2 is shown as the inscribed circle for the inner diameter of the female thread portion formed in each second bolt hole 122, but it may also be the inscribed circle for the diameter of the root of the female thread portion, or the inscribed circle for the effective diameter. This prevents the diameter of the second flange portion 120 from increasing.

[0054] In one embodiment of the fuel supply pipe assembly 100, as shown in Figure 4B, the size of the virtual circle passing through the centers of the multiple second bolt holes 122, i.e., the pitch circle diameter PCD2 of the second bolt holes 122, is preferably smaller than the size of the virtual circumscribed circle VC2 that circumscribes the protrusion 111 when viewed from the axial direction. This further suppresses the increase in the diameter of the second flange portion 120.

[0055] In one embodiment of the fuel supply pipe assembly 100, as shown in Figure 4B, the size of the virtual inscribed circle VI2 that is inscribed in the plurality of second bolt holes 122 when viewed from the axial direction is preferably smaller than the size of the virtual circumscribed circle VC3 that is circumscribed in the plurality of first bolt holes when viewed from the axial direction. This allows the position of the first bolt hole 112 to be set relatively radially outward while suppressing an increase in the diameter of the second flange portion 120.

[0056] In one embodiment of the combustor 4, as shown in Figures 3 and 4D, the second flange portion 120 is in contact with the flange portion 62 of the top hat portion 60 on the axially upstream surface 123 of the fuel supply pipe 101 and is preferably fixed to the flange portion 62 by bolts 151 inserted through the second bolt hole 122 and the third bolt hole 68. This allows the second flange portion 120 to be attached to the flange portion 62 even if the size of the through hole 65 in the flange portion 62 is constrained by the position of the casing 20 to which the top hat portion 60 is attached, or by the radial size of the cavity 33. Furthermore, with the above configuration, the through hole 65 in the flange portion 62 can be sealed by the second flange portion 120. This prevents compressed air inside the combustor chamber 32 from leaking out of the combustor chamber 32 through the through hole 65.

[0057] This disclosure is not limited to the embodiments described above, but also includes modified forms of the embodiments described above, as well as forms that combine these forms as appropriate.

[0058] 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 fuel nozzle (third fuel nozzle 70) provided on the side of a combustion cylinder 36 of a gas turbine combustor (combustor 4), comprising: a fuel supply pipe 101 for supplying fuel to the fuel nozzle (third fuel nozzle 70); a first flange portion 110 that can be coupled to a flange portion of a fuel pipe for supplying fuel to the fuel supply pipe 101; and a second flange portion 120 that can be coupled to a top hat portion 60 of the gas turbine combustor (combustor 4). The first flange portion 110 has a plurality of projections 111 that are spaced apart in the circumferential direction and protrude radially outward, and a plurality of first bolt holes 112 that penetrate the first flange portion 110 in the axial direction. Each of the plurality of first bolt holes 112 is formed at the same position as the circumferential position of the projections 111.

[0059] According to the configuration of (1) above, since each of the multiple first bolt holes 112 is formed at the same position as the circumferential position of the projection 111, the position of the first bolt holes 112 can be set relatively radially outward while suppressing an increase in the size of the first flange portion 110 other than the projection 111. This ensures that the diameter of the fuel supply pipe 101 is large and that the flow rate of fuel supplied to the fuel nozzle (third fuel nozzle 70) is secured.

[0060] (2) In some embodiments, in the configuration of (1) above, the first flange portion 110 may have a plurality of recesses 113 formed between two adjacent protrusions 111 in the circumferential direction, recessed radially inward, and spaced apart in the circumferential direction. The size of the virtual circumscribed circle VC1 that circumscribes the plurality of first bolt holes 112 when viewed from the axial direction may be larger than the size of the virtual inscribed circle VI1 that circumscribes the innermost radial position of the plurality of recesses 113 when viewed from the axial direction.

[0061] According to the configuration described in (2) above, the position of the first bolt hole 112 can be set relatively radially outward.

[0062] (3) In some embodiments, in the configuration of (2) above, the size of the virtual circle passing through the centers of the plurality of first bolt holes 112 (pitch circle diameter PCD1) may be the same as the size of the virtual inscribed circle VI1 or larger than the size of the virtual inscribed circle.

[0063] According to the configuration described in (3) above, the position of the first bolt hole 112 can be set further radially outward.

[0064] (4) In some embodiments, in any of the configurations (1) to (3) above, the second flange portion 120 is the second flange portion 120 Established in It is preferable to have multiple second bolt holes 122.

[0065] According to the configuration described in (4) above, the second flange portion 120 can be fixed to the top hat portion 60 of the gas turbine combustor (combustor 4) by bolts 151 inserted through a plurality of second bolt holes 122.

[0066] (5) In some embodiments, in the configuration of (4) above, the size of the virtual inscribed circle VI2 that is inscribed in the plurality of second bolt holes 122 when viewed from the axial direction is smaller than the size of the virtual circumscribed circle VC2 that is inscribed around the projection 111 when viewed from the axial direction.

[0067] According to the configuration in (5) above, it is possible to suppress the increase in the diameter of the second flange portion 120.

[0068] (6) In some embodiments, in the configuration of (5) above, the size of the virtual circle passing through the centers of the multiple second bolt holes 122 (pitch circle diameter PCD2) is smaller than the size of the virtual circumscribed circle VC2 that circumscribes the protrusion 111 when viewed from the axial direction.

[0069] According to the configuration in (6) above, the increase in the diameter of the second flange portion 120 can be further suppressed.

[0070] (7) In some embodiments, in any of the configurations (4) to (6) above, the size of the virtual inscribed circle VI2 that is inscribed in the plurality of second bolt holes 122 when viewed from the axial direction is smaller than the size of the virtual circumscribed circle VC3 that is inscribed around the plurality of first bolt holes 112 when viewed from the axial direction.

[0071] According to the configuration described in (7) above, the position of the first bolt hole 112 can be set relatively radially outward while suppressing an increase in the diameter of the second flange portion 120.

[0072] (8) A gas turbine combustor according to at least one embodiment of the present disclosure is The fuel supply pipe assembly 100 comprises one of the configurations (1) to (7) above, the combustion cylinder 36, the fuel nozzle (third fuel nozzle 70), and the top hat portion 60. The top hat portion 60 includes a top hat body (flange portion 62) through which the first flange portion 110 can pass in the axial direction. The top hat body (flange portion 62) has a plurality of top hat projections 67 that are spaced apart in the circumferential direction and project radially inward toward the center of the through hole 65, and a plurality of third bolt holes 68 that penetrate the top hat body (flange portion 62) in the axial direction. Each of the plurality of third bolt holes 68 is formed at the same position as the circumferential position of the top hat projection 67.

[0073] According to the configuration of (8) above, the fuel supply pipe assembly 100 is provided with any of the configurations of (1) to (7) above, so that the size of the first flange portion 110 other than the protrusion 111 does not increase, and the position of the first bolt hole 112 can be set relatively radially outward. This ensures that the diameter of the fuel supply pipe 101 is large and that the flow rate of fuel supplied to the fuel nozzle (third fuel nozzle 70) is secured. Furthermore, according to the configuration described in (8) above, the position of the third bolt hole 68 can be set relatively radially inward. This makes it easier to provide the third bolt hole 68 even when the size of the through hole 65 in the top hat body (flange portion 62) is restricted.

[0074] (9) In some embodiments, in the configuration of (8) above, the second flange portion 120 is the second flange portion 120 Established in It is preferable that there be multiple second bolt holes 122. The second flange portion 120 abuts against the top hat body (flange portion 62) on the upstream surface 123 of the fuel supply pipe 101 and is preferably fixed to the top hat body (flange portion 62) by connecting bolts (bolts 151) inserted through the second bolt holes 122 and the third bolt holes 68.

[0075] According to the configuration in (9) above, the second flange portion 120 can be attached to the top hat body (flange portion 62) even if the size of the through hole 65 in the top hat body (flange portion 62) is restricted. Furthermore, according to the configuration in (9) above, the through hole 65 in the top hat body (flange portion 62) can be sealed by the second flange portion 120. This prevents compressed air inside the combustor chamber 32 from leaking out of the combustor chamber 32 through the through hole.

[0076] (10) A gas turbine 1 according to at least one embodiment of the present disclosure comprises a compressor 2, a gas turbine combustor (combustor 4) having the configuration of (8) or (9) above, and a turbine 6 configured to be driven by combustion gas from the gas turbine combustor (combustor 4).

[0077] According to the configuration described in (10) above, the diameter of the fuel supply pipe 101 can be ensured, and the flow rate of fuel supplied to the fuel nozzle (third fuel nozzle 70) can be ensured. [Explanation of symbols]

[0078] 1 Gas Turbine 2 Compressor 4. Combustor (Gas Turbine Combustor) 20 Casing 32 Combustion chamber 33 Blanks 40. No. 1 Fuel Nozzle 60 Top Hat Section 62 Flange section (top hat body) 65 Through hole 67 Top hat projection 68 Third bolt hole 69 Top hat recess 46. ​​Second fuel nozzle 70 Third fuel nozzle 100 Fuel supply pipe assemblies 101 Fuel supply pipe 110 First flange section 111 Protrusion 112 First bolt hole 113 Recess 120 Second flange section 122 Second bolt hole

Claims

1. A fuel supply pipe assembly for supplying fuel to a fuel nozzle located on the side of the combustion chamber of a gas turbine combustor, A fuel supply pipe for supplying the fuel to the fuel nozzle, A first flange portion that can be connected to the flange portion of a fuel pipe for supplying the fuel to the fuel supply pipe, A second flange portion that can be connected to the top hat portion of the gas turbine combustor, Equipped with, The aforementioned top hat portion has a through hole in which a plurality of top hat projections are formed that protrude radially inward toward the center of the through hole. The first flange portion is, Multiple protrusions are provided at intervals in the circumferential direction and project outward in the radial direction, A plurality of recesses are formed between two adjacent protrusions in the circumferential direction so as to be recessed radially inward, and which can pass through the through hole while avoiding interference with the plurality of top-hat protrusions, Multiple first bolt holes that penetrate the first flange portion in the axial direction, It has, Each of the aforementioned plurality of first bolt holes is formed at the same position as the circumferential position of the projection. Fuel supply pipe assembly.

2. A fuel supply pipe assembly for supplying fuel to a fuel nozzle provided on the side of a combustion chamber of a gas turbine combustor, A fuel supply pipe for supplying the fuel to the fuel nozzle, A first flange portion that can be connected to the flange portion of a fuel pipe for supplying the fuel to the fuel supply pipe, A second flange portion that can be connected to the top hat portion of the gas turbine combustor, Equipped with, The first flange portion has multiple projections that are spaced apart in the circumferential direction and protrude radially outward, and multiple first bolt holes that penetrate the first flange portion in the axial direction. Each of the aforementioned plurality of first bolt holes is formed at the same position as the circumferential position of the projection. The first flange portion is formed between two adjacent protrusions in the circumferential direction and is recessed radially inward, and has a plurality of recesses spaced apart in the circumferential direction. The size of the virtual circumscribed circle that circumscribes the plurality of first bolt holes when viewed from the axial direction is larger than the size of the virtual inscribed circle that circumscribes the innermost radial position in the plurality of recesses when viewed from the axial direction. Fuel supply pipe assembly.

3. The size of the virtual circle passing through the centers of the plurality of first bolt holes is the same as the size of the virtual inscribed circle, or larger than the size of the virtual inscribed circle. The fuel supply pipe assembly according to claim 2.

4. The second flange portion has a plurality of second bolt holes provided in the second flange portion, Each of the aforementioned plurality of second bolt holes is positioned at the same location as the circumferential position of the plurality of recesses in the first flange portion. A fuel supply pipe assembly according to any one of claims 1 to 3.

5. The size of the virtual inscribed circle that inscribes the plurality of second bolt holes when viewed from the axial direction is smaller than the size of the virtual circumscribed circle that inscribes the protrusion when viewed from the axial direction. The fuel supply pipe assembly according to claim 4.

6. The size of the virtual circle passing through the centers of the plurality of second bolt holes is smaller than the size of the virtual circumscribed circle that circumscribes the protrusion when viewed from the axial direction. The fuel supply pipe assembly according to claim 5.

7. The size of the virtual inscribed circle that inscribes the plurality of second bolt holes when viewed from the axial direction is smaller than the size of the virtual circumscribed circle that inscribes the plurality of first bolt holes when viewed from the axial direction. The fuel supply pipe assembly according to claim 4.

8. A fuel supply pipe assembly according to any one of claims 1 to 3, The combustion chamber and, The fuel nozzle and, The aforementioned top hat portion, Equipped with, The top hat portion includes a top hat body having a through hole through which the first flange portion can pass in the axial direction. The top hat body has a plurality of top hat projections provided at intervals in the circumferential direction and projecting radially inward toward the center of the through hole, and a plurality of third bolt holes that penetrate the top hat body in the axial direction. Each of the aforementioned plurality of third bolt holes is formed at the same position as the circumferential position of the top hat projection. Gas turbine combustor.

9. The second flange portion is, The second flange portion has a plurality of second bolt holes, The fuel supply pipe abuts against the top hat body on its upstream side and is fixed to the top hat body by connecting bolts inserted through the second bolt hole and the third bolt hole. The gas turbine combustor according to claim 8.

10. Compressor and, A gas turbine combustor according to claim 8, A turbine configured to be driven by combustion gas from the aforementioned gas turbine combustor, Equipped with Gas turbine.

Images