Improved fuel distribution manifold

Abstract

The invention is entitled "Improved fuel distribution manifold." The invention provides a fuel distribution manifold and a combustor. 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 to a first branch section and a second branch section. The first branch section and the second branch section are circumferentially dispersed away from each other as the first branch section and the second branch section extend axially from the inlet section to a respective first outlet and a respective second outlet.

Description

Technical Field

[0001] This disclosure relates generally to a combustor for a gas turbine. More specifically, it relates to a fuel distribution manifold for supplying fuel to a fuel injector disposed downstream of a primary combustion zone defined within the combustor. Background Technology

[0002] Turbines are used in a variety of industries and applications for energy transfer purposes. 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 the working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) mix in the combustion section and are burned in the combustion chamber to produce high-pressure, high-temperature combustion gases. The combustion gases flow from the combustion section into the turbine section, where they expand to do work. For example, the expansion of the combustion gases in the turbine section can cause a rotor shaft connected to, for example, a generator to rotate to generate electricity. The combustion gases then exit the gas turbine via the exhaust section.

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

[0004] In operation, a portion of the compressed working fluid is directed through and / or around each fuel injector and into the combustion gas flow field. Liquid or gaseous fuel from the fuel injectors is injected into the flow of compressed working fluid to provide a lean or air-rich combustible mixture, which combusts upon mixing with hot combustion gases in the combustion gas flow field, thereby increasing the burner's ignition temperature without a corresponding increase in the residence time of the combustion gases within the combustion zone. Therefore, the overall thermodynamic efficiency of the burner can be increased without sacrificing overall launch performance.

[0005] Fuel manifolds are typically used to distribute fuel received from an external source between one or more AFS injectors. Current fuel distribution manifolds include multiple components, joints, and sharp / forceful bends that can cause fuel leaks and / or pressure drops across the manifold. Therefore, designers must use fuel lines with large diameters, requiring one or more expensive fuel bellows to accommodate the pressure drops across the manifold. Consequently, there is a need in the art for improved fuel manifolds that reduce pressure drops, thereby increasing overall gas turbine performance and achieving cost savings. Summary of the Invention

[0006] According to this disclosure, aspects and advantages of the fuel combustion manifold and burner will be set forth in part in the following description, or may be apparent from the description, or may be learned through practice of the art.

[0007] According to one embodiment, a fuel distribution manifold for use in a turbine combustor 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. 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, the first branch section and the second branch section are circumferentially dispersed away from each other.

[0008] According to another embodiment, a burner is provided. The burner includes a burner housing and an end cap coupled to the burner housing. The burner also includes a primary fuel nozzle extending axially within the burner housing downstream of the end cap. A primary combustion zone is defined downstream of the primary fuel nozzle. The burner also includes a plurality of fuel injectors located downstream of the primary combustion zone. A fuel distribution manifold is coupled to the burner housing 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. 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, the first branch section and the second branch section are circumferentially dispersed away from each other.

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

[0010] This specification sets forth, with reference to the accompanying drawings, a complete and feasible disclosure of the fuel distribution manifold and burner of the present invention, which would be of ordinary skill in the art, including the best mode of manufacturing and using the systems and methods of the present invention, in which:

[0011] Figure 1This is a schematic diagram of a turbine according to an embodiment of this disclosure;

[0012] Figure 2 A side view of a burner according to an embodiment of the present disclosure is shown;

[0013] Figure 3 A perspective view of a burner according to an embodiment of the present disclosure is shown;

[0014] Figure 4 The embodiments of the present disclosure are shown. Figure 3 A perspective view of the axial fuel grading system separated by the burner;

[0015] Figure 5 A perspective view of a burner according to an embodiment of the present disclosure is shown;

[0016] Figure 6 The embodiments of the present disclosure are shown. Figure 5 A perspective view of the axial fuel grading system separated by the burner;

[0017] Figure 7 A cross-sectional perspective view of the housing of a fuel line for an axial fuel grading system according to an embodiment of the present disclosure is shown;

[0018] Figure 8 An embodiment according to this disclosure is shown. Figure 3 and Figure 4 A transparent diagram of the fuel distribution manifold; and

[0019] Figure 9 An embodiment according to this disclosure is shown. Figure 5 and Figure 6 A transparent diagram of the fuel distribution manifold. Detailed Implementation

[0020] Reference will now be made in detail to embodiments of the fuel distribution manifold and burner of the present invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided by way of explanation of the inventive technique and not as a limitation thereof. Indeed, it will be apparent to those skilled in the art that modifications and variations may be made to the inventive technique without departing from the scope or spirit of the technique protected by the claims. For example, a feature shown or described as part of one embodiment may be used in another embodiment to produce yet another embodiment. Therefore, this disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0021] The detailed description uses numbers and letters to refer to feature structures in the drawings. Similar or analogous names in the drawings and description have been used to refer to similar or analogous parts of the invention. As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one part from another and are not intended to indicate the location or importance of the various parts.

[0022] As used herein, the terms “upstream” (or “upward”) and “downstream” (or “downward”) refer to the relative directions of fluid flow within a fluid pathway. For example, “upstream” refers to the direction from which fluid flows, and “downstream” refers to the direction from which fluid flows.

[0023] The term “radial” refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component; the term “axial” refers to a relative direction that is substantially parallel to and / or coaxially aligned with the axial centerline of a particular component; and the term “circumferential” refers to a relative direction that extends around the axial centerline of a particular component.

[0024] Approximate terms, such as “generally” or “about,” include values ​​that are greater than or less than ten percent of the specified value. When used in the context of angles or directions, such terms include values ​​that are greater than or less than ten degrees of the angle or direction. For example, “generally vertical” includes directions that are within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0025] Now refer to the attached diagram, Figure 1 A schematic diagram of one embodiment of a turbine is shown, which in the illustrated embodiment is a gas turbine 10. Although industrial or land-based gas turbines are shown and described herein, this disclosure is not limited to industrial or land-based gas turbines unless otherwise specified in the claims. For example, the inventive techniques described herein can be used in any type of turbine, including but not limited to steam turbines, aircraft gas turbines, or marine gas turbines.

[0026] As shown in the figure, the gas turbine 10 typically includes an inlet section 12, a compressor section 14 located downstream of the inlet section 12, and multiple burners 17 located in a burner section 16 located downstream of the compressor section 14. Figure 2 The gas turbine 10 may include a turbine section 18 located downstream of the compressor section 14 and an exhaust section 20 located downstream of the turbine section 18. Additionally, the gas turbine 10 may include one or more shafts 22 connected between the compressor section 14 and the turbine section 18.

[0027] The 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 each rotor disk 24 and connected to each rotor disk. Each rotor disk 24 may then be coupled to or form part of a shaft 22 extending through the compressor section 14.

[0028] 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. Each rotor disk 28 may then be coupled to or form a portion of a shaft 22 extending through turbine section 18. Turbine section 18 also includes an outer housing 31 that circumferentially surrounds a portion of shaft 22 and rotor blades 30, thereby at least partially defining a hot gas path 32 through turbine section 18.

[0029] During operation, a working fluid, such as air, flows through inlet section 12 and into compressor section 14, where the air is gradually compressed, thereby supplying pressurized air 27 to burners 17 in burner section 16. The pressurized air 27 mixes with fuel and burns in each burner to produce combustion gases 33. The combustion gases 33 flow from burner section 16 into turbine section 18 via hot gas path 32, where energy (kinetic and / or thermal) is transferred from the combustion gases 33 to rotor blades 30, causing shaft 22 to rotate. This mechanical rotational energy can then be used to power and / or generate electricity in compressor section 14. The combustion gases 33 exiting turbine section 18 can then be discharged from gas turbine 10 via exhaust section 20.

[0030] Figure 2 An exemplary embodiment of a burner in burner 17 is shown. As depicted, burner 17 defines an axial centerline 35 extending therethrough. In this regard, burner 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 32, the radial direction R extends orthogonally outward from the axial centerline 32, and the circumferential direction C extends concentrically around the axial centerline 32.

[0031] like Figure 2 As shown, the burner 17 includes a burner housing 34 having a first flange 36. Specifically, the first flange 36 extends radially outward from the burner housing 34 and is coupled to a compressor discharge housing 38. The burner housing 34 and the compressor discharge housing 38 together define the compressor 14 ( Figure 1 At least a portion of the high-pressure booster chamber 40 is in fluid communication. Therefore, the burner housing 34 and the compressor discharge housing 38 contain compressed air 27 entering the burner 17 from the compressor 14. The burner housing 34 also includes a second flange 42 coupled to the end cap 44. Figure 2As shown, the burner housing 34 and end cap 44 together define the head portion 46 of the burner 17. The head portion 46 is in fluid communication with the high-pressure booster chamber 40 and / or the compressor 14. One or more primary fuel injectors 48 extend axially downstream of the end cap 44.

[0032] The burner 17 also includes a liner 50 that at least partially defines an extension from one or more primary fuel injectors 48 to the turbine section 18. Figure 1 The liner 50 is the hot gas path 52 of the inlet 54. 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 burned. One or more main 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 axially positioned downstream of the first combustion zone 56 of the burner 17. A second fuel-air mixture is burned in the second combustion zone 58. Figure 2 In the illustrated embodiments, the liner 50 may be formed to include a tapered or transitional portion. In a particular embodiment, 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 at least a portion of the liner 50 and is radially spaced from said at least a portion to form a cooling flow annulus 62 between them. In other embodiments, the burner 17 may have a different configuration.

[0033] exist Figure 2 In the illustrated embodiment, combustor 17 includes an axial fuel staging system 64 (“AFS system 64”). More specifically, AFS system 64 includes one or more axially spaced-apart axial fuel staging injectors 66 (“AFS injectors 66”) from one or more primary fuel injectors 48. Specifically, the one or more AFS injectors 66 are located downstream of the one or more primary fuel injectors 48 and upstream of the turbine inlet 54. In this respect, the one or more AFS injectors 66 supply fuel to the secondary combustion zone 58. Combustor 17 may include one, two, three, four or more AFS injectors 66 circumferentially spaced around liner 50.

[0034] Figure 3 A perspective view of a burner 17 coupled with an AFS system 64 according to an embodiment of the present disclosure is shown. Specifically, the AFS system 64 may include one or more fuel distribution manifolds 68. As shown, the fuel distribution manifold 68 may be coupled to the burner housing 34. In many embodiments, the fuel distribution manifold 68 may be coupled to a second flange 42 of the burner housing 34 via one or more bolts 74. Figure 3 and Figure 4In the illustrated embodiment, the AFS system 64 includes four fuel distribution manifolds 68 circumferentially spaced from each other and radially outwardly positioned from the burner housing 34 and end cap 44. However, in an alternative embodiment, the AFS system 64 may include more or fewer fuel distribution manifolds 68, and / or each fuel distribution manifold 68 may be positioned at other locations around the burner 17.

[0035] Figure 4 The diagram illustrates an isolation from burner 17 according to one or more embodiments of this disclosure. Figure 3 The AFS system 64 is shown. As illustrated, each fuel distribution manifold 68 distributes fuel to one or more fuel lines 70 coupled thereto for final delivery to one or more AFS injectors in the AFS injectors 66. Figure 2 As shown, fuel lines 70 may each extend from fuel distribution manifold 68 in opposite circumferential directions. Thus, each fuel line 70 delivers fuel from one fuel distribution manifold in fuel distribution manifold 68 to one AFS injector in AFS injector 66.

[0036] In some embodiments, two fuel lines 70 are coupled to each fuel distribution manifold 68. Each of these fuel lines 70 may then be coupled to a different AFS injector 66. In such embodiments, each fuel distribution manifold supplies fuel to two AFS injectors 66. However, in alternative embodiments, one, three, four, or more fuel lines 70 may be coupled to each fuel distribution manifold 68. 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 once or more before reaching the AFS injector 66. For example, each fuel line may extend generally circumferentially from the fuel distribution manifold 68 and bend around one or more bends to extend generally axially to the AFS injector 66.

[0037] like Figure 3 and Figure 4As shown, each fuel distribution manifold in fuel distribution manifold 68 may include a body 84 having a radial outer surface 86, a radial inner surface 88, a first side 90, and a second side 92. In some embodiments, the radial outer surface 86 may be a generally flat surface extending in both axial and circumferential directions. Similarly, the radial inner surface 88 may also be a generally flat surface substantially parallel to and spaced apart from the radial outer surface 86. In many embodiments, the circumferential length of the radial outer surface 86 may be longer than the circumferential length of the radial inner surface 88. As shown, the first side 90 may extend at an angle from the radial outer surface 86 of the burner 17 toward the axial centerline 35. Similarly, the second side 92 may be circumferentially spaced from the first side 90 and may also extend at an angle from the radial 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 radial outer surface 86 to the radial inner surface 88 and may converge toward each other.

[0038] Figure 5 A perspective view of a burner 17 coupled to another AFS system 64, according to another embodiment of this disclosure, is shown. Specifically, the AFS system 64 may include one or more fuel distribution manifolds 68. As shown, the fuel distribution manifold 68 may be coupled to the burner housing 34. In many embodiments, the fuel distribution manifold 68 may be coupled to a second flange 42 of the burner housing 34 via one or more bolts 74. Figure 5 and Figure 6 In the illustrated embodiment, the AFS system 64 may include one or more fuel distribution manifolds 68 positioned radially outward from the burner housing 34 and end cap 44. However, in an alternative embodiment, the AFS system 64 may include more or fewer fuel distribution manifolds 68, and / or each fuel distribution manifold 68 may be located at other locations around the burner 17.

[0039] Figure 6 The diagram illustrates an isolation from burner 17 according to one or more embodiments of this disclosure. Figure 5 The AFS system 64 is shown. As illustrated, each fuel distribution manifold 68 distributes fuel to one or more fuel lines 70 coupled thereto for final delivery to one or more AFS injectors in the AFS injectors 66. Figure 2 As shown, fuel lines 70 may each extend from fuel distribution manifold 68 in opposite circumferential directions. Thus, each fuel line 70 delivers fuel from one fuel distribution manifold in fuel distribution manifold 68 to one AFS injector in AFS injector 66.

[0040] In some embodiments, two fuel lines 70 are coupled to each fuel distribution manifold 68. Each of these fuel lines 70 may then be coupled to a different AFS injector 66. In such embodiments, each fuel distribution manifold supplies fuel 28 to two AFS injectors 66. However, in alternative embodiments, one, three, four, or more fuel lines 70 may be coupled to each fuel distribution manifold 68. 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, each fuel line 70 may extend from the fuel distribution manifold 68 in the axial direction A relative to the burner 17. Figure 2 It extends in an inclined direction. In many embodiments, the fuel line 70 may change direction once or more before reaching the AFS injector 66. For example, as Figure 6 As shown, each fuel line 70 may extend from the fuel distribution manifold 68 and bend around one or more corners in a spiral or sinusoidal path before extending generally axially to one or more AFS injectors 66.

[0041] like Figures 3 to 6 As shown, the AFS system 64 may include one or more fuel supply lines 72 fluidly coupled to a fuel distribution manifold. The fuel supply lines 72 may be used to supply fuel from the fuel supply to the fuel distribution manifold 68 for use in one or more AFS injectors in the AFS injectors 66. In many embodiments, the fluid supply lines 72 may be rigidly coupled to the fuel distribution manifold 68, for example, by brazing, welding, or other means.

[0042] In many implementations, such Figures 3 to 6 As shown, the AFS system 64 may include one or more flanges 76 and one or more fuel line housings 78 located downstream of the fuel distribution manifold 68. Figure 7 As shown, flange 76 couples each fuel line in fuel line 70 to a first flange 36 of combustor housing 34. In many embodiments, fuel line housing 78 is circumferentially positioned around each fuel line in fuel line 70 and extends downstream from each flange in flange 76. In many embodiments, fuel line housing 78 is positioned downstream of flange 76 and upstream of AFS injector 66 relative to the direction in which fuel passes through fuel line 70. Fuel line housing 78 surrounds a portion of fuel line 70 near flange 76, rather than extending over the entire length between flange 76 and AFS injector 66.

[0043] Figure 7A cross-sectional perspective view of a fuel line housing 78 surrounding a fuel line 70 is shown. As shown, the fuel line 70 may extend through a second flange 36, flange 76, and fuel line housing 78 of a burner housing 34. A bellows 80 may be radially disposed between the housing 78 and the fuel line 70. As shown, the bellows 80 may extend axially between flange 76 and bellows stop 82 to provide increased material compliance for the fuel line 70 during thermal expansion / contraction of the burner 17. In many embodiments, the bellows 80 may be directly adjacent to both the fuel line housing 78 and the fuel line 70. In some embodiments, only a single bellows 80 may be disposed within the fuel line housing 78. In other embodiments (not shown), multiple bellows 80 may be disposed within the fuel line housing 78.

[0044] Figure 8 It shows Figure 3 and Figure 4 A magnified transparent view of the fuel distribution manifold 68 shown. Figure 8 As shown, the body 84 of the fuel distribution manifold 68 may define a fuel circuit 94 therein. As illustrated, the fuel circuit 94 may include an inlet 96 disposed on a radially outer surface 86, a first outlet 98 disposed on a first side 90 downstream of the inlet 96, and a second outlet 100 disposed on a second side 92 downstream of the inlet 96. The inlet 96 may be fluidly coupled to a fuel supply line 72 to supply fuel to the fuel distribution manifold 68. Similarly, the first outlet 98 and the second outlet 100 may each be directly fluidly coupled to a fuel line 70 to supply fuel to one or more AFS injectors 66.

[0045] like Figure 8 As shown, the fuel circuit 94 may further include an inlet section 102 extending generally axially from the inlet 96 to the first branch section 104 and the second branch section 106. The inlet section 102 may be located 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 connected to 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 each other, allowing fuel to 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, preventing the formation of joints, such as welded joints, brazed joints, etc., between the sections. In many implementations, the fuel circuit 94 can transition between the inlet section 102 and the branch sections 104, 106 without any sharp angles or sudden changes in direction, thereby allowing the fuel to be split into multiple streams without a drop in pressure.

[0046] 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 radially disperse 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 (e.g., Figure 8 (As shown). In other embodiments, the entrance section 102 may converge radially inward from the entrance 96 to the first branch section 104 and the second branch section 106 (e.g. Figure 9 (As shown).

[0047] like Figure 8 As shown, the first branch section 104 and the second branch section 106 may each include an inclined portion 108 and a circumferential portion 110. The inclined 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 inclined relative to the axial direction A of the burner 17 (i.e., not parallel or perpendicular to the axial direction A, but at an angle). In many embodiments, as shown, the inclined 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.

[0048] As shown, the circumferential portion 110 of each of the first branch segment 104 and the second branch segment 106 may extend directly from the inclined portion 108 in the circumferential direction C. Each circumferential portion 110 may be continuously and / or seamlessly connected to the corresponding inclined portion 108. In various embodiments, the circumferential portions 110 of the first branch segment 104 and the second branch segment 106 may each extend from the inclined portion 108 to the outlets 98, 100 in opposite circumferential directions. For example, the circumferential portion 110 of the first branch segment 104 may extend from the inclined portion 108 of the first branch segment 104 in a first circumferential direction, and the circumferential portion 110 of the second branch segment 106 may extend from the inclined portion 108 of the second branch segment 106 in a second circumferential direction opposite to the first circumferential direction. In various embodiments, the circumferential portions 110 of the first branch segment 104 and the second branch segment 106 may have a constant diameter 112 defined therein.

[0049] Figure 9 It shows Figure 5 and Figure 6The diagram shows an enlarged transparent view of the fuel distribution manifold 68. As shown, the first branch section 104 and the second branch section 106 may be fully inclined relative to the axial direction A of the burner, i.e., excluding the circumferential portion 110. In such embodiments, 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 inclined relative to the axial direction A of the burner. In many embodiments, each of the first outlet 98 and the second outlet 100 may be fluidly coupled to a corresponding fuel line 70 to supply fuel to the AFS injector 66. Figure 9 As shown, the first branch segment 104 and the second branch segment 106 may each have a constant diameter 112 defined therein.

[0050] In many embodiments, the constant diameter 112 of the first branch segment 104 and the second branch segment 106 can be up to about 1.5 inches. In other embodiments, the constant diameter 112 of the first branch segment 104 and the second branch segment 106 can be between about 0.3 inches and about 1.2 inches. In various embodiments, the constant diameter 112 of the first branch segment 104 and the second branch segment 106 can be between about 0.5 inches and about 1 inch. In some embodiments, the constant diameter 112 of the first branch segment 104 and the second branch segment 106 can be between about 0.6 inches and about 0.8 inches. In a particular embodiment, the constant diameter 112 of the first branch segment 104 and the second branch segment 106 can be about 0.75 inches.

[0051] As shown in the figure, when the first branch segment 104 and the second branch segment 106 extend axially from the inlet segment 102 to the first outlet 98 and the second outlet 100, respectively, they are circumferentially dispersed away from each other. Figure 8 and Figure 9 As shown, an angle 114 can be defined between the first branch section 104 and the second branch section 106. This angle 114 advantageously provides a smooth and continuous transition from a single fuel flow 116 flowing within the inlet section 102 to a first fuel portion 118 and a 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 uniformly divide the single fuel flow 118 received by the fuel supply line 72 into the first fuel portion 118 and the second fuel portion 120 for distribution to the downstream AFS injector 66.

[0052] In many embodiments, the angle 114 between the first branch segment 104 and the second branch segment 106 can be as high as about 150°. In other embodiments, the angle 114 between the first branch segment 104 and the second branch segment 106 can be between about 30° and about 120°. In some embodiments, the angle 114 between the first branch segment 104 and the second branch segment 106 can be between about 40° and about 100°. In various embodiments, the angle 114 between the first branch segment 104 and the second branch segment 106 can be between about 50° and about 90°.

[0053] like Figure 8 and Figure 9 As shown, fuel circuit 94 can be used to receive a single fuel flow 116 from inlet 96 and branch the single fuel flow 116 into two or more fuel flows 118, 120. Fuel circuit 94 can be a single integral circuit that is seamlessly and / or continuously defined within body 84, such that the single fuel flow 116 flowing through the inlet section can easily transition into two or more fuel flows 118, 120 at branch sections 104, 106.

[0054] In many embodiments, the fuel circuit 94 may be integrally formed with the body 84. It should be understood that integral formation includes any suitable method of forming the respective components such that they comprise a single integral unit. 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 having a fuel circuit 94 integrally formed therein, thus having a one-piece seamless construction. In this way, the fuel circuit 94 can be seamless, eliminating the need for joints and / or welds, which advantageously minimizes the pressure drop across the fuel circuit 94. Suitable methods of integral formation may include additive manufacturing, such as direct laser melting, selective laser sintering, or other suitable additive technologies. Alternatively, the body 84 of the fuel distribution manifold 68 may be formed by casting components and integrally defining the fuel circuit within the body 84.

[0055] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combined methods. The patentable scope of the invention is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0056] The following numbered clauses may define the scope of the subject matter described in this invention:

[0057] 1. A fuel distribution manifold coupled to a burner housing, the fuel distribution manifold comprising:

[0058] main body;

[0059] A fuel circuit, defined within the body, comprising:

[0060] The entrance section extends approximately axially from the entrance;

[0061] A first branch section, which is fluidly coupled to the inlet section and extends to a first outlet; and

[0062] A second branch section, which is fluidly coupled to the inlet section and extends to a second outlet;

[0063] Wherein, when the first branch section and the second branch section extend axially from the entrance section to the first exit and the second exit respectively, the first branch section and the second branch section are circumferentially dispersed away from each other.

[0064] 2. The fuel distribution manifold as described in Clause 1, wherein the fuel circuit is configured to receive fuel at the inlet.

[0065] 3. The fuel distribution manifold as described in Clause 1, wherein the inlet section is in direct fluid communication with both the first branch section and the second branch section.

[0066] 4. The fuel distribution manifold as described in Clause 1, wherein each of the first branch section and the second branch section extends at an angle inclined relative to the axial direction of the burner.

[0067] 5. The fuel distribution manifold as described in Clause 1, wherein the fuel circuit extends seamlessly between the inlet, the first outlet, and the second outlet.

[0068] 6. The fuel distribution manifold as described in Clause 1, wherein the fuel circuit is integrally formed with the main body.

[0069] 7. The fuel distribution manifold as described in Clause 1, wherein the inlet section tapers from the inlet to the first branch section and the second branch section.

[0070] 8. The fuel distribution manifold as described in Clause 1, wherein the inlet section extends from the inlet to the first branch section and the second branch section.

[0071] 9. The fuel distribution manifold according to Clause 1, wherein the body includes a radially outer side, a first side extending from the radially outer side, and a second side spaced apart from and extending from the first side.

[0072] 10. The fuel distribution manifold according to Clause 9, wherein the inlet is located on the radially outer side, the first outlet is located on the first side, and the second outlet is located on the second side.

[0073] 11. A burner, the burner comprising:

[0074] The burner housing and the end cap coupled to the burner housing;

[0075] A primary fuel nozzle that extends axially within the burner housing downstream of the end cap;

[0076] A primary combustion zone, the primary combustion zone being defined downstream of the primary fuel nozzle;

[0077] Multiple fuel injectors are located downstream of the primary combustion zone;

[0078] A fuel distribution manifold coupled to the burner housing of the burner and fluidly coupled to the plurality of fuel injectors, the fuel distribution manifold comprising:

[0079] main body;

[0080] A fuel circuit, defined within the body, comprising:

[0081] The entrance section extends approximately axially from the entrance;

[0082] A first branch section, which is fluidly coupled to the inlet section and extends to a first outlet; and

[0083] A second branch section, which is fluidly coupled to the inlet section and extends to a second outlet;

[0084] Wherein, when the first branch section and the second branch section extend axially from the entrance section to the first exit and the second exit respectively, the first branch section and the second branch section are circumferentially dispersed away from each other.

[0085] 12. The burner according to Clause 11, wherein the fuel circuit is configured to receive fuel at the inlet.

[0086] 13. The burner according to Clause 11, wherein the inlet section is in direct fluid communication with both the first branch section and the second branch section.

[0087] 14. The burner according to Clause 11, wherein each of the first branch section and the second branch section extends at an angle inclined relative to the axial direction of the burner.

[0088] 15. The burner according to Clause 11, wherein the fuel circuit extends seamlessly between the inlet, the first outlet and the second outlet.

[0089] 16. The burner according to Clause 11, wherein the fuel circuit is integrally formed with the body.

[0090] 17. The burner according to Clause 11, wherein the inlet section tapers from the inlet to the first branch section and the second branch section.

[0091] 18. The burner according to Clause 11, wherein the inlet section extends from the inlet to the first branch section and the second branch section.

[0092] 19. The burner according to Clause 11, wherein the body includes a radially outer surface, a first side extending from the radially outer surface, and a second side spaced apart from and extending from the first side.

[0093] 20. The burner according to Clause 19, wherein the inlet is disposed on the radially outer side, the first outlet is disposed on the first side, and the second outlet is disposed on the second side.

Claims

1. A fuel distribution manifold coupled to a burner housing, wherein, The burner defines an axial centerline extending therethrough and thereby defines axial, radial, and circumferential directions, and the fuel distribution manifold includes: main body; A fuel circuit, defined within the body, comprising: An entrance section that extends generally axially from the entrance; A first branch section, which is fluidly coupled to the inlet section and extends to a first outlet; and A second branch section, which is fluidly coupled to the inlet section and extends to a second outlet; Wherein, 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, the first branch section and the second branch section are circumferentially dispersed away from each other.

2. The fuel distribution manifold of claim 1, wherein the fuel circuit is configured to receive fuel at the inlet.

3. The fuel distribution manifold according to claim 1, wherein the inlet section is in direct fluid communication with both the first branch section and the second branch section.

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

5. The fuel distribution manifold of claim 1, wherein the fuel circuit extends seamlessly between the inlet, the first outlet, and the second outlet.

6. The fuel distribution manifold according to claim 1, wherein the fuel circuit is integrally formed with the body.

7. 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 of claim 1, wherein the inlet section extends from the inlet to the first branch section and the second branch section.

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

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

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