Improved fuel distribution manifold

Abstract

To provide fuel distribution manifolds and combustors.SOLUTION: Fuel distribution manifolds and combustors are provided. A fuel distribution manifold includes a main body and a fuel circuit that is defined within the main body. The fuel circuit includes an inlet section extending generally axially from an inlet to a first branch section and a second branch section. The first branch section and the second branch section diverge circumferentially away from each other as they extend axially from the inlet section to respective first and second outlets.SELECTED DRAWING: Figure 8

Description

[Technical Field]

[0001] The present disclosure relates generally to combustors for gas turbines. More particularly, the present disclosure relates to a fuel distribution manifold for providing fuel to fuel injectors positioned downstream of a primary combustion zone defined within the combustor. [Background technology]

[0002] Turbomachines are utilized in various industries and applications for the purpose of energy transfer. For example, a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of a working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and combusted in a combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to produce work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator, to generate electricity. The combustion gases then exit the gas turbine through the exhaust section.

[0003] To balance overall emissions performance and facilitate turndown operation, certain combustor designs include multiple fuel injectors arranged around the liner and positioned generally downstream of the combustion zone. The fuel injectors typically extend radially to or through the liner and provide fluid communication to the combustion gas flow field. This type of system is commonly known in the art and / or gas turbine industry as axial fuel staging ("AFS"), or sometimes as distributed combustion.

[0004] During operation, a portion of the compressed working fluid is channeled through and / or around each of the fuel injectors and delivered to the combustion gas flow field. Liquid or gaseous fuel from the fuel injectors is injected into the compressed working fluid flow to provide a lean or air-enriched combustible mixture that combusts upon mixing with the hot combustion gases in the combustion gas flow field, thereby increasing the firing temperature of the combustor without a corresponding increase in the residence time of the combustion gases in the combustion zone. As a result, the overall thermodynamic efficiency of the combustor can be increased without sacrificing overall emissions performance.

[0005] Fuel manifolds are often used to distribute fuel received from an external source among one or more AFS injectors. Current fuel distribution manifolds contain multiple parts, joints, and sharp / aggressive turns that can cause fuel leaks and / or pressure drops across the fuel manifold. As a result, designers must use large-diameter fuel tubes that require one or more expensive fuel bellows to accommodate the pressure drop across the fuel manifold. Therefore, there is a need in the art for an improved fuel manifold that reduces the pressure drop, thereby increasing overall gas turbine performance and saving costs. Summary of the Invention

[0006] Aspects and advantages of the fuel distribution manifold and combustor according to the present disclosure will be set forth in part in the description which follows, or will be obvious from the description, or may be learned by practice of the present teachings.

[0007] According to one embodiment, a fuel distribution manifold for use in a combustor of a turbomachine is provided. The fuel distribution manifold includes a body and a fuel circuit defined within the body. The fuel circuit includes an inlet section extending generally axially from an inlet, a first branch section fluidly coupled to the inlet section and extending to a first outlet, and a second branch section fluidly coupled to the inlet section and extending to a second outlet. The first branch section and the second branch section diverge circumferentially away from each other as the first branch section and the second branch section extend axially from the inlet section to the first outlet and the second outlet, respectively.

[0008] According to another embodiment, a combustor is provided. The combustor includes a combustor casing and an end cover coupled to the combustor casing. The combustor also includes a primary fuel nozzle extending axially downstream from the end cover within the combustor casing. A primary combustion zone is defined downstream of the primary fuel nozzle. The combustor also includes a plurality of fuel injectors downstream of the primary combustion zone. A fuel distribution manifold is coupled to the combustor casing of the combustor and fluidly coupled to the plurality of fuel injectors. The fuel distribution manifold includes a body and a fuel circuit defined within the body. The fuel circuit includes an inlet section extending generally axially from an inlet, a first branch section fluidly coupled to the inlet section and extending to a first outlet, and a second branch section fluidly coupled to the inlet section and extending to a second outlet. The first branch section and the second branch section diverge circumferentially away from one another as the first branch section and the second branch section extend axially from the inlet section to the first outlet and the second outlet, respectively.

[0009] These and other features, aspects, and advantages of the present fuel distribution manifold and combustor will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present technology and, together with the description, serve to explain the principles of the technology.

[0010] A full and enabling disclosure of the present fuel distribution manifold and combustor, including the best mode of making and using the present system and method, directed to one of ordinary skill in the art, is set forth in this specification, which makes reference to the accompanying drawings. [Brief explanation of the drawings]

[0011] [Figure 1] 1 is a schematic diagram of a turbomachine according to an embodiment of the present disclosure; [Figure 2] FIG. 2 is a side view of a combustor according to an embodiment of the present disclosure. [Figure 3] 1 is a perspective view of a combustor according to an embodiment of the present disclosure; [Figure 4] FIG. 4 is a perspective view of an axial fuel staging system separated from the combustor of FIG. 3 in accordance with an embodiment of the present disclosure. [Figure 5] 1 is a perspective view of a combustor according to an embodiment of the present disclosure; [Figure 6] FIG. 6 is a perspective view of an axial fuel staging system separated from the combustor of FIG. 5 in accordance with an embodiment of the present disclosure. [Figure 7] FIG. 2 is a cross-sectional perspective view of a casing for a fuel line of an axial fuel staging system according to an embodiment of the present disclosure. [Figure 8] FIG. 5 is a perspective view of the fuel distribution manifold of FIGS. 3 and 4 according to one embodiment of the present disclosure. [Figure 9] FIG. 7 is a perspective view of the fuel distribution manifold of FIGS. 5 and 6 according to one embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0012] Reference will now be made in detail to the present fuel distribution manifold and combustor embodiments, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the present technology, not as a limitation thereof. Indeed, it will be apparent to those skilled in the art that modifications and variations can be made in the present technology without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used in another embodiment to yield still a further embodiment. Accordingly, the present disclosure is intended to cover such modifications and variations as come within the scope of the appended claims and their equivalents.

[0013] The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description are used to refer to like or similar parts of the invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to denote the location or importance of the individual components.

[0014] As used herein, the terms "upstream" (or "forward") and "downstream" (or "rearward") refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0015] The term "radially" refers to a relative direction substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction substantially parallel to and / or coaxially aligned with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction extending around the axial centerline of a particular component.

[0016] Approximate terms such as "generally" or "about" include values ​​within plus or minus 10 percent of the stated value. When used in the context of angles or directions, such terms include a range of plus or minus 10 degrees of the stated angle or direction. For example, "generally vertical" includes any direction, e.g., clockwise or counterclockwise, within 10 degrees of vertical.

[0017] Referring now to the drawings, Figure 1 shows a schematic diagram of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to industrial or land-based gas turbines unless otherwise stated in the claims. For example, the subject technology described herein may be used with any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0018] As shown, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream from the inlet section 12, a plurality of combustors 17 ( FIG. 2 ) in a combustor section 16 disposed downstream from the compressor section 14, a turbine section 18 disposed downstream from the combustor section 16, and an exhaust section 20 disposed downstream from the turbine section 18. Additionally, the gas turbine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0019] Compressor section 14 may generally include a plurality of rotor disks 24 (one of which is shown) and a plurality of rotor blades 26 extending radially outward from and connected to each rotor disk 24. Each rotor disk 24 may in turn be coupled to or form part of a portion of a shaft 22 that extends through compressor section 14.

[0020] Turbine section 18 may generally include a plurality of rotor disks 28 (one of which is shown) and a plurality of rotor blades 30 extending radially outward from and connected to each rotor disk 28. Each rotor disk 28 may in turn be coupled to or form a part of a portion of a shaft 22 that extends through turbine section 18. Turbine section 18 further includes an outer casing 31 circumferentially surrounding the portion of shaft 22 and rotor blades 30, thereby at least partially defining a hot gas path 32 through turbine section 18.

[0021] During operation, a working fluid, such as air, flows through the inlet section 12 and into the compressor section 14, where the air is progressively compressed, thereby providing compressed air 27 to the combustors 17 of the combustor section 16. The compressed air 27 is mixed with fuel and combusted in each combustor to generate combustion gases 33. The combustion gases 33 flow through the hot gas path 32 from the combustor section 16 to the turbine section 18, where energy (kinetic and / or thermal energy) is transferred from the combustion gases 33 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to power the compressor section 14 and / or generate electricity. The combustion gases 33 exiting the turbine section 18 may then be exhausted from the gas turbine 10 via the exhaust section 20.

[0022] 2 illustrates an exemplary embodiment of one of the combustors 17. As illustrated, the combustor 17 defines an axial centerline 35 extending therethrough. In this regard, the combustor 17 defines an axial direction A, a radial direction R, and a circumferential direction C. Generally, the axial direction A extends parallel to the axial centerline 35, the radial direction R extends orthogonally outward from the axial centerline 35, and the circumferential direction C extends concentrically about the axial centerline 35.

[0023] As shown in FIG. 2 , the combustor 17 includes a combustor casing 34 having a first flange 36. In particular, the first flange 36 extends radially outward from the combustor casing 34 and couples to a compressor discharge casing 38. The combustor casing 34 and the compressor discharge casing 38 collectively define at least a portion of a high-pressure plenum 40 in fluid communication with the compressor 14 ( FIG. 1 ). As such, the combustor casing 34 and the compressor discharge casing 38 contain the compressed air 27 entering the combustor 17 from the compressor 14. The combustor casing 34 also includes a second flange 42 that couples to an end cover 44. As shown in FIG. 2 , the combustor casing 34 and the end cover 44 collectively define a head end portion 46 of the combustor 17. The head end portion 46 is in fluid communication with the high-pressure plenum 40 and / or the compressor 14. One or more primary fuel injectors 48 extend axially downstream from the end cover 44.

[0024] The combustor 17 also includes a liner 50 that at least partially defines a hot gas path 52 extending from the one or more primary fuel injectors 48 to an inlet 54 of the turbine section 18 ( FIG. 1 ). In this regard, the liner 50 at least partially defines a primary or first combustion or reaction zone 56 in which a first fuel-air mixture is combusted. The one or more primary fuel injectors 48 supply fuel to the first combustion zone 56. The liner 50 also at least partially defines a secondary combustion or reaction zone 58 positioned axially downstream from the first combustion zone 56 of the combustor 17. A second fuel-air mixture is combusted in the second combustion zone 58. In the embodiment shown in FIG. 2 , the liner 50 may be formed to include a tapered or transition portion. In certain embodiments, the liner 50 may be formed from a single or continuous body having a generally cylindrical upstream portion and a tapered downstream portion. A flow sleeve 60 circumferentially surrounds and is radially spaced from at least a portion of the liner 50 to define a cooling flow annulus 62 therebetween. The combustor 17 may have different configurations in other embodiments.

[0025] 2 , the combustor 17 includes an axial fuel staging system 64 (“AFS system 64”). More specifically, the AFS system 64 includes one or more axial fuel staging injectors 66 (“AFS injectors 66”) spaced axially from the one or more primary fuel injectors 48. In particular, the one or more AFS injectors 66 are positioned downstream from the one or more primary fuel injectors 48 and upstream of the inlet 54 to the turbine 18. In this regard, the one or more AFS injectors 66 supply fuel to the secondary combustion zone 58. The combustor 17 may include one, two, three, four, or more AFS injectors 66 spaced circumferentially around the liner 50.

[0026] FIG. 3 illustrates a perspective view of a combustor 17 having an AFS system 64 coupled thereto, according to one embodiment of the present disclosure. In particular, the AFS system 64 may include one or more fuel distribution manifolds 68. As shown, the fuel distribution manifolds 68 may be coupled to the combustor casing 34. In many embodiments, the fuel distribution manifolds 68 may be coupled to the second flange 42 of the combustor casing 34 via one or more bolts 74. In the embodiment illustrated in FIGS. 3 and 4, the AFS system 64 includes four fuel distribution manifolds 68 that are circumferentially spaced apart from one another and positioned radially outward from the combustor casing 34 and the end cover 44. However, in alternative embodiments, the AFS system 64 may include a greater or lesser number of fuel distribution manifolds 68, and / or each fuel distribution manifold 68 may be positioned elsewhere around the combustor 17.

[0027] 4 illustrates the AFS system 64 shown in FIG. 3 separated from the combustor 17 in accordance with one or more embodiments of the present disclosure. As shown, each fuel distribution manifold 68 may distribute fuel to one or more associated fuel lines 70 for ultimate delivery to one or more of the AFS injectors 66 (FIG. 2). As shown, the fuel lines 70 may each extend in opposite circumferential directions from the fuel distribution manifold 68. Thus, each fuel line 70 transports fuel from one of the fuel distribution manifolds 68 to one of the AFS injectors 66.

[0028] In some embodiments, two fuel lines 70 couple to each fuel distribution manifold 68. Each of these fuel lines 70 may then couple to a different AFS injector 66. In such embodiments, each fuel distribution manifold provides fuel to two AFS injectors 66. Nevertheless, one, three, four, or more fuel lines 70 may be coupled to each fuel distribution manifold 68 in alternative embodiments. Furthermore, multiple fuel lines 70 may be coupled to the same AFS injector 66. The fuel lines 70 may be rigid (e.g., extruded metal) or flexible (e.g., braided metal). In many embodiments, the fuel lines 70 may change direction one or more times before reaching the AFS injectors 66. For example, each fuel line may extend generally circumferentially from the fuel distribution manifold 68, curve around one or more corners, and extend generally axially to the AFS injectors 66.

[0029] As shown in FIGS. 3 and 4 , each of the fuel distribution manifolds 68 may include a body 84 having a radially outer surface 86, a radially inner surface 88, a first side surface 90, and a second side surface 92. In some embodiments, the radially outer surface 86 may be a generally flat surface extending axially and circumferentially. Similarly, the radially inner surface 88 may also be a generally flat surface substantially parallel to and spaced apart from the radially outer surface 86. In many embodiments, the radially outer surface 86 may have a circumferential length that is longer than the circumferential length of the radially inner surface 88. As shown, the first side surface 90 may extend at an angle from the radially outer surface 86 toward the axial centerline 35 of the combustor 17. Similarly, the second side surface 92 may be circumferentially spaced from the first side surface 90 and may extend at an angle from the radially outer surface 86 toward the axial centerline 35. In many embodiments, the first side 90 and the second side 92 may each extend from the radially outer surface 86 to the radially inner surface 88 and may converge toward each other.

[0030] FIG. 5 illustrates a perspective view of a combustor 17 having another AFS system 64 coupled thereto in accordance with another embodiment of the present disclosure. In particular, the AFS system 64 may include one or more fuel distribution manifolds 68. As shown, the fuel distribution manifolds 68 may be coupled to the combustor casing 34. In many embodiments, the fuel distribution manifolds 68 may be coupled to the second flange 42 of the combustor casing 34 via one or more bolts 74. In the embodiment illustrated in FIGS. 5 and 6, the AFS system 64 may include one or more fuel distribution manifolds 68 positioned radially outward from the combustor casing 34 and the end cover 44. However, in alternative embodiments, the AFS system 64 may include a greater or lesser number of fuel distribution manifolds 68, and / or each fuel distribution manifold 68 may be positioned elsewhere around the combustor 17.

[0031] 6 illustrates the AFS system 64 shown in FIG. 5 separated from the combustor 17 in accordance with one or more embodiments of the present disclosure. As shown, each fuel distribution manifold 68 may distribute fuel to one or more associated fuel lines 70 for ultimate delivery to one or more of the AFS injectors 66 (FIG. 2). As shown, the fuel lines 70 may each extend in opposite circumferential directions from the fuel distribution manifold 68. Thus, each fuel line 70 transports fuel from one of the fuel distribution manifolds 68 to one of the AFS injectors 66.

[0032] In some embodiments, two fuel lines 70 couple to each fuel distribution manifold 68. Each of these fuel lines 70 may then couple to a different AFS injector 66. In such embodiments, each fuel distribution manifold provides fuel to two AFS injectors 66. Nevertheless, one, three, four, or more fuel lines 70 may be coupled to each fuel distribution manifold 68 in alternative embodiments. Furthermore, multiple fuel lines 70 may be coupled to the same AFS injector 66. The fuel lines 70 may be rigid (e.g., extruded metal) or flexible (e.g., braided metal). As shown, the fuel lines 70 may each extend from the fuel distribution manifold 68 in a direction oblique to the axial direction A of the combustor 17 ( FIG. 2 ). In many embodiments, the fuel lines 70 may change direction one or more times before reaching the AFS injectors 66. For example, as shown in FIG. 6 , each fuel line 70 may extend from the fuel distribution manifold 68 and curve around one or more corners in a serpentine or sinusoidal path before extending generally axially to one or more AFS injectors 66.

[0033] 3-6 , the AFS system 64 may include one or more fuel supply lines 72 fluidly coupled to a fuel distribution manifold 68. The fuel supply lines 72 may function to provide fuel from a fuel supply source to the fuel distribution manifold 68 for use by one or more of the AFS injectors 66. In many embodiments, the fuel supply lines 72 are rigidly coupled to the fuel distribution manifold 68, and may be, for example, brazed, welded, or otherwise fixedly coupled to the fuel distribution manifold 68.

[0034] In many embodiments, as shown in FIGS. 3-6 , the AFS system 64 may include one or more flanges 76 and one or more fuel line casings 78 downstream of the fuel distribution manifold 68. As shown in FIG. 7 , the flanges 76 may couple each of the fuel lines 70 to the first flange 36 of the combustor casing 34. In many embodiments, the fuel line casings 78 may be positioned annularly around each of the fuel lines 70 and may extend downstream from each of the flanges 76. In many embodiments, the fuel line casings 78 may be positioned downstream of the flanges 76 and upstream of the AFS injectors 66 relative to the direction of fuel passing through the fuel lines 70. The fuel line casings 78 surround a portion of the fuel lines 70 proximate the flanges 76 without extending the entire length between the flanges 76 and the AFS injectors 66.

[0035] FIG. 7 illustrates a cross-sectional perspective view of a fuel line casing 78 surrounding the fuel line 70. As shown, the fuel line 70 may extend through the first flange 36 of the combustor casing 34, the flange 76, and the fuel line casing 78. A bellows tube 80 may be disposed radially between the casing 78 and the fuel line 70. As shown, the bellows tube 80 may extend axially between the flange 76 and a bellows stop 82 to provide increased material compliance for the fuel line 70 during thermal expansion / contraction of the combustor 17. In many embodiments, the bellows tube 80 may be directly adjacent to both the fuel line casing 78 and the fuel line 70. In some embodiments, only a single bellows tube 80 may be disposed within the fuel line casing 78. In other embodiments (not shown), multiple bellows tubes 80 may be disposed within the fuel line casing 78.

[0036] FIG. 8 illustrates an enlarged, see-through view of the fuel distribution manifold 68 shown in FIGS. 3 and 4 . As shown in FIG. 8 , the body 84 of the fuel distribution manifold 68 may define a fuel circuit 94 therein. As shown, the fuel circuit 94 may include an inlet 96 disposed on the radially outer surface 86, a first outlet 98 disposed on the first side 90 downstream from the inlet 96, and a second outlet 100 disposed on the second side 92 downstream from the inlet 96. The inlet 96 may be fluidly coupled to the fuel supply line 72 to provide fuel to the fuel distribution manifold 68. Similarly, the first outlet 98 and the second outlet 100 may each be fluidly coupled directly to the fuel line 70 to provide fuel to one or more AFS injectors 66.

[0037] As shown in FIG. 8 , the fuel circuit 94 may also include an inlet section 102 extending generally axially from the inlet 96 to a first branch section 104 and a second branch section 106. The inlet section 102 may be disposed upstream of and in direct fluid communication with the first branch section 104 and the second branch section 106. In some embodiments, the first branch section 104 and the second branch section 106 may each be directly fluidly coupled to and continuous with the inlet section 102. In many embodiments, the inlet section 102, the first branch section 104, and the second branch section 106 may each extend seamlessly and / or continuously between one another so that fuel can easily transition between the inlet section 102 and the branch sections 104, 106 without a pressure drop. In some embodiments, the inlet section 102 may extend seamlessly between the branch sections 104, 106 so that no joints, e.g., welded joints, brazed joints, etc., are formed between the sections. In many embodiments, the fuel circuit 94 can transition between the inlet section 102 and the branch sections 104, 106 without abrupt changes in angle or direction, thereby allowing the fuel to be split into multiple streams without a drop in pressure.

[0038] In many embodiments, the inlet section 102 may taper from the inlet 96 to the first branch section 104 and the second branch section 106. In some embodiments, the inlet section 102 may diverge radially outward as it extends in the axial direction A from the inlet 96 to the first branch section 104 and the second branch section 106 (as shown in FIG. 8 ). In other embodiments, the inlet section 102 may converge radially inward from the inlet 96 to the first branch section 104 and the second branch section 106 (as shown in FIG. 9 ).

[0039] 8 , the first branch section 104 and the second branch section 106 may each include an angled portion 108 and a circumferential portion 110. The angled portion 108 of each of the first branch section 104 and the second branch section 106 may extend directly from the inlet section 102 in a direction oblique to the axial direction A of the combustor 17, i.e., at an angle rather than parallel or perpendicular to the axial direction A. In many embodiments, the angled portion 108 may taper along its length from a larger diameter at the inlet section 102 to a smaller diameter at the circumferential portion 110, as shown.

[0040] As shown, the circumferential portion 110 of each of the first branch section 104 and the second branch section 106 can extend directly from the angled portion 108 in the circumferential direction C. Each of the circumferential portions 110 can be continuous with and / or seamlessly connected to the respective angled portion 108. In various embodiments, the circumferential portion 110 of the first branch section 104 and the second branch section 106 can each extend in opposite circumferential directions from the angled portion 108 to the outlets 98, 100. For example, the circumferential portion 110 of the first branch section 104 can extend in a first circumferential direction from the angled portion 108 of the first branch section 104, and the circumferential portion 110 of the second branch section 106 can extend in a second circumferential direction opposite the first circumferential direction from the angled portion 108 of the second branch section 106. In various embodiments, the circumferential portion 110 of the first branch section 104 and the second branch section 106 may have a constant diameter 112 defined therein.

[0041] FIG. 9 illustrates an enlarged, see-through view of the fuel distribution manifold 68 illustrated in FIGS. 5 and 6 . As illustrated, the first branch section 104 and the second branch section 106 may be fully angled relative to the axial direction A of the combustor, i.e., may not include a circumferential portion 110. In such an embodiment, the first branch section 104 and the second branch section 106 may each extend directly from the inlet section 102 to the first outlet 98 and the second outlet 100, respectively, in a direction angled relative to the axial direction A of the combustor. In many embodiments, the first outlet 98 and the second outlet 100 may each be fluidly coupled to a respective fuel line 70 to provide fuel to the AFS injector 66. As illustrated in FIG. 9 , the first branch section 104 and the second branch section 106 may each have a constant diameter 112 defined therein.

[0042] In many embodiments, the constant diameter 112 of the first branch section 104 and the second branch section 106 may be up to about 1.5 inches. In other embodiments, the constant diameter 112 of the first branch section 104 and the second branch section 106 may be from about 0.3 inches to about 1.2 inches. In various embodiments, the constant diameter 112 of the first branch section 104 and the second branch section 106 may be from about 0.5 inches to about 1 inch. In some embodiments, the constant diameter 112 of the first branch section 104 and the second branch section 106 may be from about 0.6 inches to about 0.8 inches. In certain embodiments, the constant diameter 112 of the first branch section 104 and the second branch section 106 may be about 0.75 inches.

[0043] As shown, the first branch section 104 and the second branch section 106 diverge circumferentially away from one another as they extend axially from the inlet section 102 to the first outlet 98 and the second outlet 100, respectively. As shown in FIGS. 8 and 9 , an angle 114 may be defined between the first branch section 104 and the second branch section 106. This angle 114 advantageously provides a smooth, continuous transition from the single fuel stream 116 flowing within the inlet section 102 to the first fuel portion 118 and the second fuel portion 120 flowing within the first branch section 104 and the second branch section 106, respectively. The branch sections 104, 106 of the fuel circuit 94 equally divide the single fuel stream 116 received by the fuel supply line 72 into the first fuel portion 118 and the second fuel portion 120 for distribution to the AFS injectors 66 positioned downstream.

[0044] In many embodiments, the angle 114 between the first branch section 104 and the second branch section 106 may be up to about 150°. In other embodiments, the angle 114 between the first branch section 104 and the second branch section 106 may be between about 30° and about 120°. In some embodiments, the angle 114 between the first branch section 104 and the second branch section 106 may be between about 40° and about 100°. In various embodiments, the angle 114 between the first branch section 104 and the second branch section 106 may be between about 50° and about 90°.

[0045] 8 and 9, the fuel circuit 94 may function to receive a single fuel stream 116 from the inlet 96 and split the single fuel stream 116 into two or more fuel streams 118, 120. The fuel circuit 94 may be a single, integral circuit seamlessly and / or continuously defined within the body 84 such that the single fuel stream 116 flowing through the inlet section can easily transition into the two or more fuel streams 118, 120 in the branch sections 104, 106.

[0046] In many embodiments, the fuel circuit 94 may be integrally formed with the body 84. It should be understood that integrally forming includes any suitable method of forming each component to comprise a single, integral whole. For example, the inlet section 102, the first branch section 104, and the second branch section 106 may each be part of a single, integral fuel circuit 94 defined within the body 84 of the fuel distribution manifold 68. In many embodiments, the body 84 of the fuel distribution manifold 68 may be formed with the fuel circuit 94 integrally formed therein, thus having a one-piece, seamless construction. In this manner, the fuel circuit 94 may be seamless, eliminating the need for joints and / or welds, advantageously minimizing pressure drop across the fuel circuit 94. Suitable methods of integrally forming may include additive manufacturing, such as direct metal laser melting, selective laser sintering, or other suitable additive techniques. As another example, the body 84 of the fuel distribution manifold 68 may be formed by casting a part and having the fuel circuit integrally defined within the body 84.

[0047] This written description uses examples to disclose the invention, including the best mode, and to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they contain structural elements that do not differ from the literal language of the claims, or equivalent structural elements that do not differ substantially from the literal language of the claims.

[0048] The following numbered clauses may define the scope of the subject matter described herein: Clause 1. A fuel distribution manifold coupled to a combustor casing of a combustor, comprising: The main body and a fuel circuit defined within the body, an inlet section extending generally axially from the inlet; a first branch section fluidly coupled to the inlet section and extending to a first outlet; and a second branch section fluidly coupled to the inlet section and extending to a second outlet; a fuel circuit comprising: Equipped with the first branch section and the second branch section diverge circumferentially away from one another as the first branch section and the second branch section extend axially from the inlet section to the first outlet and the second outlet, respectively. Fuel distribution manifold. Clause 2. The fuel distribution manifold of clause 1, wherein the fuel circuit is configured to receive fuel at the inlet. Clause 3. The fuel distribution manifold of clause 1, wherein the inlet section is in direct fluid communication with both the first branch section and the second branch section. Clause 4. The fuel distribution manifold of clause 1, wherein each of the first branch section and the second branch section extends at an oblique angle relative to an axial direction of the combustor. Clause 5. The fuel distribution manifold of clause 1, wherein the fuel circuit extends seamlessly between the inlet, the first outlet, and the second outlet. Clause 6. The fuel distribution manifold of clause 1, wherein the fuel circuit is integrally formed with the body. Clause 7. The fuel distribution manifold of clause 1, wherein the inlet section tapers from the inlet to the first branch section and the second branch section. Clause 8. The fuel distribution manifold of clause 1, wherein the inlet section splits from the inlet into the first branch section and the second branch section. Clause 9. The fuel distribution manifold of clause 1, wherein the body comprises a radially outer surface, a first side extending from the radially outer surface, and a second side spaced from the first side and extending from the radially outer surface. Clause 10. The fuel distribution manifold of clause 9, wherein the inlet is disposed on the radially outer surface, the first outlet is disposed on the first side surface, and the second outlet is disposed on the second side surface. Article 11. Combustors, a combustor casing and an end cover coupled to the combustor casing; a primary fuel nozzle extending axially downstream from the end cover within the combustor casing; a primary combustion zone defined downstream of the primary fuel nozzle; a plurality of fuel injectors downstream of the primary combustion zone; a fuel distribution manifold coupled to the combustor casing of the combustor and fluidly coupled to the plurality of fuel injectors, The main body and a fuel circuit defined within the body, an inlet section extending generally axially from the inlet; a first branch section fluidly coupled to the inlet section and extending to a first outlet; and a second branch section fluidly coupled to the inlet section and extending to a second outlet; a fuel circuit comprising: Equipped with the first branch section and the second branch section diverge circumferentially away from one another as the first branch section and the second branch section extend axially from the inlet section to the first outlet and the second outlet, respectively. Fuel distribution manifold and A combustor comprising: Clause 12. The combustor of clause 11, wherein the fuel circuit is configured to receive fuel at the inlet. Clause 13. The combustor of clause 11, wherein the inlet section is in direct fluid communication with both the first branch section and the second branch section. Clause 14. The combustor of clause 11, wherein each of the first branch section and the second branch section extends at an oblique angle relative to an axial direction of the combustor. Clause 15. The combustor of clause 11, wherein the fuel circuit extends seamlessly between the inlet, the first outlet, and the second outlet. Clause 16. The combustor of clause 11, wherein the fuel circuit is integrally formed with the body. Clause 17. The combustor of clause 11, wherein the inlet section tapers from the inlet to the first branch section and the second branch section. Clause 18. The combustor of clause 11, wherein the inlet section splits from the inlet into the first branch section and the second branch section. Clause 19. The combustor of clause 11, wherein the body comprises a radially outer surface, a first side extending from the radially outer surface, and a second side spaced from the first side and extending from the radially outer surface. Clause 20. The combustor of clause 19, wherein the inlet is disposed on the radially outer surface, the first outlet is disposed on the first side, and the second outlet is disposed on the second side. [Explanation of symbols]

[0049] 10. Gas turbine 12 Entrance Section 14 Compressor section, compressor 16 Combustor Section 17 Combustor 18 Turbine section, turbine 20 Exhaust Section 22 shaft 24 rotor disc 26 rotor blades 27 Compressed air, pressurized air 28 rotor disc 30 rotor blades 31 outer casing 32 Hot gas path 33 Combustion Gas 34 Combustor casing 35 Axial centerline 36 First flange 38 Compressor discharge casing 40 High Pressure Plenum 42 Second flange 44 End cover 46 Head end part 48 Primary fuel injector 50 Liner 52 Hot Gas Path 54 Entrance 56 First combustion and reaction zone 58 Secondary combustion zone, second combustion zone, reaction zone 60 Flow Sleeve 62 Cooling flow annulus 64 Axial Fuel Staging System 66 Axial fuel staging injector 68 Fuel distribution manifold 70 fuel line 72 Fuel supply line 74 volts 76 flange 78 Fuel line casing 80 Bellows tube 82 Bellows stop 84 Main Unit 86 Radial outer surface 88 Radial inner surface 90 First Aspect 92 Second Aspect 94 Integrated fuel circuit 96 Entrance 98 Exit 1 100 Second Exit 102 Entrance Section 104 First Branch Section 106 Second Branch Section 108 Slope section 110 Circumference 112 Constant diameter 114 angle 116 Single Fuel Stream 118 first fuel portion, fuel flow 120 second fuel portion, fuel flow A axis direction C Circumferential direction R Radial direction

Claims

1. a fuel distribution manifold (68) coupled along a radially outer surface of a combustor casing (34) of a combustor (17), A main body (84); a fuel circuit (94) defined within said body (84), an inlet section (102) extending generally axially from the inlet (96); a first branch section (104) fluidly coupled to the inlet section (102) and extending to a first outlet (98); and a second branch section (106) fluidly coupled to the inlet section (102) and extending to a second outlet (100); a fuel circuit (94) comprising: Equipped with the first branch section (104) and the second branch section (106) diverge circumferentially away from one another as the first branch section (104) and the second branch section (106) extend axially from the inlet section (102) to the first outlet (98) and the second outlet (100), respectively; A fuel distribution manifold (68).

2. The fuel distribution manifold (68) of claim 1, wherein the fuel circuit (94) is configured to receive fuel at the inlet (96).

3. The fuel distribution manifold (68) of claim 1, wherein the inlet section (102) is in direct fluid communication with both the first branch section (104) and the second branch section (106).

4. 2. The fuel distribution manifold of claim 1, wherein each of the first branch section and the second branch section extends at an oblique angle relative to an axial direction of the combustor.

5. The fuel distribution manifold (68) of claim 1, wherein the fuel circuit (94) extends seamlessly between the inlet (96), the first outlet (98), and the second outlet (100).

6. The fuel distribution manifold (68) of claim 1, wherein the fuel circuit (94) is integrally formed with the body (84).

7. 2. The fuel distribution manifold of claim 1, wherein the inlet section tapers from the inlet to the first branch section and the second branch section.

8. The fuel distribution manifold (68) of claim 1, wherein the inlet section (102) splits from the inlet (96) into the first branch section (104) and the second branch section (106).

9. 2. The fuel distribution manifold of claim 1, wherein the body comprises a radially outer surface, a first side surface extending from the radially outer surface, and a second side surface spaced from the first side surface and extending from the radially outer surface.

10. 10. The fuel distribution manifold of claim 9, wherein the inlet is disposed on the radially outer surface, the first outlet is disposed on the first side surface, and the second outlet is disposed on the second side surface.

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