JP6595010B2 - Fuel nozzle assembly having a premix flame stabilizer - Google Patents

Description

  The present invention relates generally to a fuel nozzle assembly for use in a gas turbine combustor. More particularly, the invention relates to a fuel nozzle assembly having a baffle plate for flame stabilization downstream of the fuel injection location.

  A typical gas turbine includes an inlet portion, a compressor portion, a combustion portion, a turbine portion, and an exhaust portion. The inlet portion cleans and regulates the working fluid (eg, air) and supplies the working fluid to the compressor portion. The compressor portion gradually increases the pressure of the working fluid and supplies the compressed working fluid to the combustion portion. The compressed working fluid and fuel are mixed in the combustion section and burned in the combustion chamber to produce combustion gas having a high temperature and high pressure. The combustion gases are sent along the hot gas path to the turbine section where they expand and produce work. For example, combustion gas expansion in the turbine section can generate electricity by rotating a shaft connected to a generator.

  The combustion portion generally includes one or more combustors that are arranged in an annular fashion between the compressor portion and the turbine portion. Various parameters affect the design and operation of the combustor. For example, gas turbine manufacturers are constantly being sought to increase the efficiency of gas turbines without producing undesirable air pollution emissions. The major air pollution emissions typically produced by gas turbines that burn conventional hydrocarbon fuels are nitrogen oxides (NOx), carbon monoxide (CO), and unburned hydrocarbons (UHC). The oxidation of molecular nitrogen and thus the formation of NOx in an air-breathing engine such as a gas turbine is an exponential function of temperature. The higher the temperature of the combustion gas, the higher the rate of formation of undesirable NOx emissions.

  One way to reduce the temperature of the combustion gas and thus suppress the formation of NOx is to use a premixed fuel injector or fuel nozzle assembly, such as a swirler or swozzle type fuel nozzle assembly, Premixing fuel and air upstream of the combustion reaction zone in the combustion chamber. In this type of fuel nozzle assembly, fuel is injected into a compressed air stream in an annular flow path or premix passage defined in the fuel nozzle assembly. The fuel and compressed air mix in an annular passage and then are sent from the downstream end of the fuel nozzle assembly to the combustion chamber. During combustion, the heat capacity or thermal capacitance of excess air present in the air-rich or fuel-lean flammable mixture reduces the temperature of the combustion gas by absorbing the heat in the combustion chamber, thereby reducing NOx emissions. Reduce or prevent formation.

  The flow field of the lean combustible mixture that exits the premixing passage and enters the combustion chamber at the point of injection must be uniform or symmetrical to reduce the possibility of flame retention and achieve the desired emission performance. Thus, continuous improvements in current fuel nozzle assembly technology are considered useful.

US Patent Application Publication No. 2013/219849

  Aspects and advantages of the present invention are set forth in the following description, or may be obvious from the description, or may be understood through practice of the invention.

  One embodiment of the present invention is a fuel nozzle assembly for a gas turbine. The fuel nozzle assembly includes a central body, an outer tube at least partially surrounding the central body, a premixing channel defined radially between the central body and the outer tube, and the central body within the premixing channel. And a plurality of fuel ports disposed between the outer tube and the outer tube. The fuel nozzle assembly further includes a baffle plate that extends radially outward from the central body to the outer tube across the downstream end portion of the fuel nozzle assembly. The baffle plate includes an upstream side that is spaced apart in the axial direction from the downstream side, and a plurality of passages. The passage provides fluid flow from the premix flow path through the baffle plate.

  Another embodiment of the invention is a combustor for a gas turbine. A combustor generally includes a combustion chamber defined within the combustor and a fuel nozzle assembly disposed upstream of the combustion chamber. The fuel nozzle assembly includes a central body coaxially aligned with an axial centerline of the fuel nozzle assembly, an outer tube concentric with the central body and at least partially surrounding the central body, and the central body and the outer tube in the radial direction. A premixing channel defined therebetween, and a plurality of fuel ports disposed in the premixing channel. A ring manifold concentric with the central body includes a plurality of fuel ports in communication with the fuel circuit of the fuel nozzle assembly. The fuel nozzle assembly further includes a baffle plate that extends radially and circumferentially across the downstream end portion of the fuel nozzle assembly. The baffle plate includes an upstream side that is spaced apart in the axial direction from the downstream side, and a plurality of passages. Each passage has an inlet defined along the upstream side and an outlet defined along the downstream side. Each passage provides a flow of fluid through the baffle plate from the premix channel to the combustion chamber.

  Another embodiment of the invention includes a gas turbine. A gas turbine generally includes a compressor, a combustor disposed downstream of the compressor, and a turbine disposed downstream of the combustor. The combustor includes an end cover coupled to the outer casing and a combustion chamber defined inside the outer casing. A fuel nozzle assembly extends from downstream of the end cover and ends upstream of the combustion chamber. The fuel nozzle assembly includes a central body, an outer tube at least partially surrounding the central body, a premixing passage defined between the central body and the outer tube, and the central body and the outer tube within the premixing passage. And a plurality of fuel ports arranged between the two. The plurality of fuel ports communicate with the premixing passage. The fuel nozzle assembly further includes a baffle plate that extends radially and circumferentially across the downstream end portion of the fuel nozzle assembly. The baffle plate includes an upstream side that is spaced apart in the axial direction from the downstream side, and a plurality of passages. Each passage has an inlet defined along the upstream side and an outlet defined along the downstream side. Each passage provides a flow of fluid through the baffle plate from the premix channel to the combustion chamber.

  Those skilled in the art will better understand the features and aspects of such embodiments and the like in consideration of the specification.

  For those skilled in the art, the full disclosure of the invention, including the best mode of the invention, will be described in further detail in the remainder of this specification, including reference to the accompanying drawings.

1 is a functional block diagram of a typical gas turbine included in the technical scope of the present invention. FIG. 1 is a simplified side cross-sectional view of an exemplary combustor that may incorporate various embodiments of the present invention. FIG. 1 is a perspective view of an exemplary fuel nozzle assembly according to at least one embodiment of the invention. FIG. 4 is a cross-sectional perspective view of the exemplary fuel nozzle assembly shown in FIG. 3 in accordance with at least one embodiment of the invention. FIG. 4 is a cross-sectional perspective view of the exemplary fuel nozzle assembly shown in FIG. 3 in accordance with at least one embodiment of the invention. FIG. FIG. 4 is an enlarged side cross-sectional view of a portion of an exemplary baffle plate of the exemplary fuel nozzle assembly shown in FIG. 3 in accordance with an embodiment of the present invention. FIG. 4 is an enlarged side cross-sectional view of a portion of an exemplary baffle plate of the exemplary fuel nozzle assembly shown in FIG. 3 in accordance with an embodiment of the present invention. FIG. 4 is a downstream perspective view of a cross-sectional portion of the fuel nozzle assembly shown in FIG. 3, providing an operational flow diagram of a portion of the fuel nozzle assembly according to at least one embodiment of the invention.

  Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. In the detailed description, numerical and letter symbols are used to refer to features in the drawings. In the drawings and description, the same or similar symbols are used to refer to the same or similar parts of the present invention.

  In this specification, the terms "first", "second", and "third" can be used interchangeably to distinguish one component from another component, It is not intended to indicate the location or importance of any of the components. The terms “upstream”, “downstream”, “radial”, and “axial” refer to the direction relative to the fluid flow in the fluid path. For example, “upstream” refers to the direction in which the fluid flows, and “downstream” refers to the direction in which the fluid flows. Similarly, “radial” refers to a relative direction that is substantially perpendicular to the fluid flow, and “axial” is a relative direction that is substantially parallel to the fluid flow. Point to. The term “circumferential” refers to the relative direction extending around the axial centerline of a particular component.

  Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, the present invention is intended to embrace alterations and modifications that fall within the scope of the appended claims and their equivalents.

  Referring now to the drawings, wherein like numerals indicate like components throughout the views, FIG. 1 is a functional block diagram of a typical gas turbine 10 that may incorporate various embodiments of the invention. Is shown. As shown, the gas turbine 10 generally purifies and otherwise regulates a series of filters, cooling coils, moisture separators, and / or working fluid (eg, air) 14 entering the gas turbine 10. It includes an inlet portion 12 that may include other devices. The working fluid 14 flows to the compressor portion, where the compressor 16 gradually imparts kinetic energy to the working fluid 14 to produce a compressed working fluid 18 in a high energy state.

  The compressed working fluid 18 is mixed with the fuel 20 from the fuel supply system 22 to form a combustible mixture in one or more combustors 24. The combustible mixture burns and produces high temperature and high pressure combustion gas 26. Combustion gas 26 flows through turbine 28 in the turbine section and produces work. For example, the turbine 28 can be connected to the shaft 30 such that the compressor 16 is driven by the rotation of the turbine 28 to produce a compressed working fluid 18. Alternatively or in addition, the shaft 30 can connect the turbine 28 to a generator 32 for power generation. Exhaust gas 34 from turbine 28 flows through an exhaust portion 36 that connects turbine 28 to an exhaust stack 38 downstream of turbine 28. The exhaust portion 36 may include, for example, a heat recovery steam generator (not shown) for purification of the exhaust gas 34 and extraction of additional heat from the exhaust gas 34 prior to release to the environment.

  The combustor 24 may be any type of combustor known in the art, and the present invention is limited to any particular combustor design unless specifically recited in the claims. Not. For example, the combustor 24 may be a can-annular combustor. FIG. 2 shows a simplified side cross-sectional view of an exemplary combustor 24 that may incorporate various embodiments of the present invention. As shown in FIG. 2, a casing 40 (such as a compressor discharge casing) and an end cover 42 are connected to the combustor casing 44 to contain the compressed working fluid 18 flowing from the compressor 16 (FIG. 1) to the combustor 24. Can be coupled to each other. The compressed working fluid 18 flows through a flow hole 46 in an annular flow sleeve 48, such as an impingement sleeve or combustion flow sleeve, along the outside of the tether duct 50 and / or liner 52 to the front end 54 of the combustor 24. be able to.

  The front end 54 is at least partially defined by the end cover 42 and / or the combustor casing 44. The compressed working fluid 18 can provide convective and / or conductive cooling to the tether duct 50 and / or liner 52 as it flows toward the front end 54. At the front end 54, the compressed working fluid 18 reverses the direction of flow and flows through one or more fuel nozzle assemblies 56. The fuel 20 flows from the fuel supply system 22 through one or more fuel circuits (not shown) defined in the end cover 42 to each or a portion of the fuel nozzle assembly 56. The fuel supply system 22 can supply gaseous and / or liquid fuel to the combustor 24. As the compressed working fluid 18 passes through the fuel nozzle assembly 56 and / or passes around the fuel nozzle assembly 56, it is premixed with the fuel 20 to form a combustible mixture 58. The combustible mixture 58 flows from the fuel nozzle assembly 56 to the combustion chamber 60 for combustion.

  FIG. 3 shows a perspective view of an exemplary fuel nozzle assembly 100 of one or more fuel nozzle assemblies 56 shown in FIG. 2 according to one embodiment of the invention. FIG. 4 shows a side cross-sectional view of the fuel nozzle assembly 100 shown in FIG. 3 according to one embodiment of the invention. In various embodiments, as shown in FIG. 4, the fuel nozzle assembly 100 includes an annular central body 102, an annular outer tube 104 that at least partially surrounds the central body 102, and a central body 102 in the radial direction. A premixing channel 106 defined between the outer tube 104, a plurality of fuel ports 108 disposed in the premixing channel 106 between the central body 102 and the outer tube 104, and the fuel nozzle assembly 100. A baffle plate 110 extending radially outward from the central body 102 to the outer tube 104 at the downstream end portion 112. As shown in FIG. 3, the baffle plate 110 extends circumferentially and radially across the downstream end portion 112 of the fuel nozzle assembly 100 relative to the axial centerline 114 of the fuel nozzle assembly 100.

  As shown in FIG. 4, the central body 102 is coaxially aligned with the axial centerline 114 of the fuel nozzle assembly 100. The central body 102 includes an upstream end portion 116 that is axially spaced from the downstream end portion 118. The central body 102 can be formed from one or more annular tubes. In certain embodiments, the central body 102 at least partially defines a central passage 120 that extends axially through the fuel nozzle assembly 100. The central passage 120 can be configured to receive a cartridge or insert (not shown). For example, the central passage 120 may contain a gaseous fuel only cartridge, a liquid fuel cartridge, and / or a purge air cartridge. The cartridge can provide the dual fuel and / or purge air capability of the fuel nozzle assembly 100.

  In certain embodiments, the central body 102 includes a converging portion 122, as shown in FIG. The converging portion 122 converges radially inward along the axial center line 114 in the axial direction toward the baffle plate 110 and / or the downstream end portion 118 of the central body 102. The converging unit 122 determines the flow cross-sectional area of the central passage 120 from the first flow cross-sectional area 124 measured upstream of the converging unit 122, and the second cross-sectional area measured from the point located along the converging unit 122. It gradually decreases to a smaller flow cross-sectional area 126. Further, the converging unit 122 measures the cross-sectional area of the flow of the premix channel 106 at a point located along the converging unit 122 from the cross-sectional area 128 of the first flow measured upstream of the converging unit 122. And gradually increase to a second larger flow cross-sectional area 130.

  In certain embodiments, as shown in FIG. 4, at least a portion of the plurality of fuel ports 108 can be defined along the ring manifold 132. The ring manifold 132 may be substantially concentric with the central body 102 and may be disposed in the premix channel 106 between the central body 102 and the outer tube 104. The ring manifold 132 includes and / or can be defined with various fuel circuits or plenums 134 (this number is not visible in some views) in communication with the fuel port 108. In certain embodiments, the fuel plenum 134 may be separated with respect to fluid and may be operated or filled with fuel independently of each other. In certain embodiments, the fuel ports 108 may be axially spaced with respect to the axial centerline 114 to provide axially multi-staged fuel injection in the premix channel 106.

  In certain embodiments, a plurality of struts or vanes 136 extend radially from the central body 102. In one embodiment, the struts 136 extend radially from the central body 102 to the ring manifold 132. The struts 136 can define various fuel passages or circuits 138 within the struts 136. In various embodiments, the fuel passage 138 is in communication with one or more fuel circuits 140 defined within the central body 102. The fuel circuit 140 can be configured to provide gaseous fuel and / or liquid fuel to the fuel port 108. The ring manifold 132 and / or strut 136 may be shaped and / or configured to minimize aerodynamic impact on the compressed air flowing across the ring manifold 132 in the premix channel 106. it can. In certain embodiments, at least a portion of the plurality of fuel ports 108 can be disposed or defined along the strut 136. The fuel port 108 provides communication between the fuel passage 138 defined in the strut 136 and the premix channel 106.

  FIG. 5 illustrates a side cross-sectional view of a fuel nozzle assembly 100 according to another embodiment of the present invention. As shown in FIG. 5, the struts 136 can extend radially between the central body 102 and the outer tube 104 within the premix channel 106. At least a portion of the plurality of fuel ports 108 may be disposed or defined along the strut 136. In one embodiment, as shown in FIG. 5, at least a portion of the plurality of fuel ports 108 may be disposed along the central body 102 downstream of the struts 136.

  In certain embodiments, as shown in FIGS. 3, 4, and 5, the fuel nozzle assembly 100 includes a plurality of fuel ports 108 and / or a flow conditioning portion that is disposed or defined upstream of the premix passage 106. 142 is further included. In certain embodiments, as shown in FIGS. 4 and 5, the flow conditioning portion 142 can generally include one or more concentric vanes 144 that are coaxially aligned with the central body 102. The vane 144 provides a flow characteristic or flow of the compressed air 18 as the compressed air 18 (FIG. 2) flows from the front end 54 of the combustor 24 to the premixing passage 106 upstream of the plurality of fuel ports 108. You can manipulate your profile. In certain embodiments, as shown in FIG. 4, the fuel nozzle assembly 100 is defined by an outer sleeve 148 and / or end plate 150, or a plurality of defined within the outer sleeve 148 and / or end plate 150. An opening 146 may be included. The plurality of openings 146 provide a flow characteristic of the compressed air 18 as the compressed air 18 (FIG. 2) flows from the front end 54 of the combustor 24 to the premixing passage 106 upstream of the plurality of fuel ports 108. Or you can manipulate the flow profile.

  In various embodiments, the baffle plate 110 extends radially and circumferentially across the downstream end portion 112 of the fuel nozzle assembly 100, as shown in FIG. The baffle plate 110 generally provides a bluff body that traverses the premix channel 106 upstream of the combustion chamber 60 (FIG. 2). In certain embodiments, as shown in FIGS. 3, 4, and 5, the baffle plate 110 can include a central portion 152 that defines an opening 154. The opening 154 is coaxially aligned with the central body 102 and / or the central passage 120. In certain embodiments, the opening 154 can partially define the central passage 120 and is configured to receive a fuel or purge air cartridge (not shown) and / or a spark plug (not shown). It's okay.

  In various embodiments, as shown in FIGS. 4 and 5, the baffle plate 110 includes an upstream or inlet side 156 that is axially spaced from the downstream or outlet side 158. A plurality of passages 160 extend generally axially through the upstream side 156 and the downstream side 158. In various embodiments, the passage 160 is annularly disposed around the opening 154 of the baffle plate 110. The passages 160 can be arranged to form a plurality of circumferential rows, with each row positioned radially away from the next row. Although the passage 160 is shown as having a generally circular cross-sectional shape, it should be understood that the passage 160 is not limited to any particular cross-sectional shape unless specifically indicated in the claims. It is. For example, the passage 160 may have a circular, rectangular, triangular, or trapezoidal cross-sectional shape.

  As shown in FIGS. 4 and 5, each passage 160 includes an inlet 162 defined along the upstream side 156 and an outlet 164 defined along the downstream side 158. The inlet 162 communicates with the premixing channel 106. At least some of the passages 160 provide fluid flow from the premix channel 106 through the baffle plate 110 to the combustion chamber 60 (FIG. 2). Inlet 162 and outlet 164 may have various shapes such that the fuel-air mixture entering passage 160 is maximized at inlet 162 and a separate fuel-air jet is formed at outlet 164. In order to minimize the possibility of holding the flame, the transition from the shape of the inlet 162 to the shape of the outlet 164 is smooth. In one embodiment, the inlet shape 162 has a larger area than the outlet shape 164 to accelerate the flow of the fuel-air mixture through the baffle plate 110.

  FIG. 6 illustrates a downstream cross-sectional perspective view of the downstream portion 112 of the fuel nozzle assembly 100 including the baffle plate 110 illustrated in FIGS. 4 and 5 according to one embodiment of the present invention. As shown in FIG. 6, the upstream side 156 of the baffle plate 110 has a plurality of concentrically aligned rings that extend axially and radially with respect to the centerline 114 and extend circumferentially around the opening 154. Walls 166 can be included and / or such annular walls 166 can be defined. Each annular wall 166 is radially spaced from one or more adjacent annular walls 166. The annular wall 166 radially separates or isolates the inlets 162 of the radially adjacent passages 160. A plurality of circumferentially spaced radial walls 168 extend radially between adjacent annular walls 166 in the radial direction. The radial wall 168 circumferentially separates or isolates circumferentially adjacent passages 160 and / or inlets 162 to adjacent passages 160. Annular wall 166 and radial wall 168 surround the inlet 162 to each passageway and / or at least partially define it to maximize the area of inflow of the fuel-air mixture into the baffle plate 110; If a circular shape is continued from inlet 162 to outlet 164, the wasted space that can occur between adjacent passages is minimized.

  FIG. 7 shows a cross-sectional perspective view in the downstream direction of the downstream portion 112 of the fuel nozzle assembly 100 including the baffle plate 110 shown in FIGS. 4 and 5 according to one embodiment of the present invention. As shown in FIG. 7, the upstream side 156 of the baffle plate 110 at least partially defines and / or surrounds one or more peaks 170 and one or more of an inlet 162 to one or more passages 160. Can be included. The peaks 170 and valleys 172 may be alternating such that the valleys 172 are located between adjacent peaks 170 and the peaks 170 are located between adjacent valleys 172. In one exemplary embodiment, the cross-sectional profile of the baffle plate 110 may be generally corrugated with arcuate peaks 170 and valleys 172. Alternatively, the peaks 170 and valleys 172 may be straight, with triangles having small radii at the peaks (ie, the highest point in the axial direction) and / or valleys 172 (ie, the lowest point in the axial direction). It can be or have any other suitable cross-sectional profile. In certain embodiments, the array 174 of outer peaks 170 may melt into the inner surface 176 of the baffle plate 110 or blend into the inner surface 176 of the baffle plate 110.

  FIG. 8 illustrates a downstream perspective view of a cross-sectional portion of the fuel nozzle assembly 100 according to one embodiment of the present invention, and also illustrates an operational flow diagram of a portion of the fuel nozzle assembly 100. In operation, as shown in FIG. 8, the compressed air 18 from the front end 54 of the combustor 24 (FIG. 2) is routed through the flow conditioning portion 142 while the fuel 20 is within the central body 102. To the plurality of fuel ports 108 through various fuel circuits 140 (FIGS. 4 and 5) defined in FIG. In certain embodiments, the compressed air 18 is passed through a plurality of fuel ports 108 via vanes 144 and / or openings 146 in the flow conditioning portion 142 of the fuel nozzle assembly 100, as shown in FIGS. Pre-adjusted upstream of the compressed air 18 when the compressed air 18 flows from the front end 54 of the combustor 24 into the premixing passage 106 upstream of the plurality of fuel ports 108, or You can manipulate the flow profile.

  Next, fuel is injected into the compressed air stream 18 upstream of the inlet 162 of the baffle plate 110 as indicated by arrow 20 in FIG. The fuel 20 and compressed air 18 mix in the premixing passage 106, resulting in a fuel-air mixture upstream as shown by the arrow 174 upstream of the inlet 162. Defined along the upstream or inlet side 156 of the baffle plate 110, such as an annular wall 166 and a radial wall 168 as shown in FIGS. 6 and 8, or peaks 170 and valleys 172 as shown in FIG. Various surface features provide an inlet 162 to the generally aerodynamically smooth passage 160 to provide flame stabilization downstream of the outlet 160 and / or outlet 164 of the passage 160. In addition or alternatively, the passage 160 facilitates further or more complete premixing of the fuel-air mixture 174 upstream of the combustion chamber 60, thereby increasing the overall emissions performance of the combustor 24. Can be increased. The fuel-air mixture 174 burns in a flow direction that is substantially axial (ie, without the vortex or tangential flow direction typically associated with swirler or swozzle type premix fuel nozzles). Enter the chamber 60. As a result, the flame front is shortened and shows good flame stability.

  This specification, including the best mode, discloses several aspects of the invention to enable those skilled in the art to practice the invention, including the making and use of any apparatus or system, and the execution of any related methods. An example is used. 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 embodiments include structural elements that do not differ from the language of the claims, or equivalent structural elements that do not substantially differ from the language of the claims. Be within range.

DESCRIPTION OF SYMBOLS 10 Gas turbine 12 Inlet part 14 Working fluid 16 Compressor 18 Compressed working fluid, compressed air 20 Fuel 22 Fuel supply system 24 Combustor 26 Combustion gas 28 Turbine 30 Shaft 32 Generator 34 Exhaust gas 36 Exhaust part 38 Exhaust Stack 40 Casing 42 End cover 44 Combustor casing 46 Flow hole 48 Annular flow sleeve 50 Connecting duct 52 Liner 54 (combustor) front end 56 Fuel nozzle assembly 58 Combustible mixture 60 Combustion chamber 100 Fuel nozzle assembly 102 Central body 104 Outer tube 106 Premix channel, premix channel 108 Fuel port 110 Baffle plate 112 Downstream end portion (of fuel nozzle assembly), Downstream portion 114 Axis centerline 116 Upstream end portion 118 (of central body) Downstream end portion 12 (of central body) Central passage 122 Convergence section 124 First flow cross section 126 (Center passage) Second flow cross section 128 (Central passage) First flow cross section 130 (Premix channel) First flow cross section 130 (Premix) Second flow cross section 132 ring manifold 134 fuel circuit, plenum 136 strut, vane 138 fuel passage, circuit 140 fuel circuit 142 flow regulating portion 144 concentric vane 146 opening 148 outer sleeve 150 end plate 152 (baffle plate) Central portion 154 opening 156 upstream of baffle plate, inlet side 158 downstream of baffle plate, outlet side 160 passage 160 of baffle plate inlet 164 outlet 166 annular wall 168 radial wall 170 peak 172 Valley 174 Fuel-air mixture 176 (inside baffle plate)

Claims (17)

A fuel nozzle assembly (100) comprising:
A central body (102);
An outer tube (104) at least partially surrounding the central body (102);
A premixing channel (106) defined between the central body (102) and the outer tube (104) in a radial direction;
A plurality of fuel ports (108) disposed in the premixing channel (106) between the central body (102) and the outer tube (104);
A baffle plate (110) extending radially outward from the central body (102) to the outer tube (104) across the downstream end portion (112) of the fuel nozzle assembly (100);
The baffle plate (110) includes an upstream side (156) that is axially spaced from the downstream side (158) and a plurality of passages (160), and the passage (160) includes the baffle plate (160). passing through 110) cod also the flow of fluid from the premixed combined channel (106),
The upstream side (156) is spaced circumferentially extending radially between a plurality of concentrically aligned annular walls (166) and a radially adjacent annular wall (166). A plurality of radial walls (168) disposed, the annular wall (166) and the radial wall (168) at least partially providing an inlet (162) to each passageway (160). defining, fuel nozzle assembly (100).   The upstream side (156) includes one or more peaks (170) and one or more valleys (172) that at least partially define an inlet (162) to one or more of the passages (160). The fuel nozzle assembly (100) of clause 1. The peaks (170) and valleys (172) are alternated such that valleys (172) are defined between adjacent peaks (170) and peaks (170) are defined between adjacent valleys (172). The fuel nozzle assembly (100) of claim 2 , wherein the fuel nozzle assembly (100) is. The baffle plate (110) includes a central portion (152) that defines an opening (154), the opening (154) being coaxial with a central passageway (120) defined by the central body (102). The fuel nozzle assembly (100) of any preceding claim, wherein the fuel nozzle assembly (100) is aligned. The plurality of fuel ports (108) are concentrically disposed within the premix passage (106) and concentrically aligned with the central body (102) or the central body (102) and the outer tube (104). The fuel nozzle assembly (100) according to any of claims 1 to 4, wherein the fuel nozzle assembly (100) is disposed along at least one of the struts (136) extending radially therebetween. The fuel nozzle assembly (100) according to any of the preceding claims, wherein the central body (102) defines a central passage (120) configured to receive a cartridge. The fuel nozzle assembly (100) of any preceding claim, wherein the central body (102) includes a converging portion (122). The fuel nozzle assembly (100) of any preceding claim, further comprising a flow conditioning portion (142) disposed upstream of the plurality of fuel ports (108) and the premix passage (106). A combustor (24) for a gas turbine (10),
A combustion chamber (60) defined within the combustor (24);
A fuel nozzle assembly (100) disposed upstream of the combustion chamber (60),
The fuel nozzle assembly (100) includes:
A central body (102) coaxially aligned with an axial centerline (114) of the fuel nozzle assembly (100);
An outer tube (104) concentric with the central body (102) and at least partially surrounding the central body (102);
A premixing channel (106) defined between the central body (102) and the outer tube (104) in a radial direction;
A ring disposed concentrically with the central body (102) in the premixing channel (106) and defining a plurality of fuel ports (108) in communication with the fuel circuit (140) of the fuel nozzle assembly (100). A manifold (132);
A baffle plate (110) extending radially and circumferentially across the downstream end portion (112) of the fuel nozzle assembly (100);
The baffle plate (110) includes an upstream side (156) that is axially spaced from the downstream side (158), and a plurality of passages (160), each passage (160) having the upstream side. An inlet (162) defined along (156) and an outlet (164) defined along the downstream side (158), the passage (160) being connected to the premix channel (106). ) and cod also the flow of fluid through the baffle plate (110) and said combustion chamber (60) from,
The upstream side (156) of the fuel nozzle assembly (100) extends radially between a plurality of concentrically aligned annular walls (166) and a radially adjacent annular wall (166). A plurality of circumferentially spaced radial walls (168), the annular wall (166) and the radial wall (168) being an entrance to each passageway (160) defining a (162) at least partially, a combustor (24). The upstream side (156) of the fuel nozzle assembly (100) has one or more peaks (170) and one or more ones that at least partially define the inlet (162) of one or more of the passages (160). The combustor (24) of claim 9 , comprising a valley (172). The peaks (170) and valleys (172) are alternated such that valleys (172) are defined between adjacent peaks (170) and peaks (170) are defined between adjacent valleys (172). there, combustor of claim 1 0 (24). At least one strut (136) extends radially between the central body (102) and the ring manifold (132), the at least one strut (136) having a fuel passage (138) therein. The combustor (24) of claim 9 or 10, wherein the at least one strut (136) defines a fuel port (108) through the at least one strut (136). It said central body (102) defines a configured central passage (120) to receive a cartridge, combustor according to claim 1 2 (24). A combustor (24) according to any of claims 9 to 13 , further comprising a flow conditioning portion (142) disposed upstream of the plurality of fuel ports (108) and the premix passage (106). A compressor (16); a combustor (24) disposed downstream of the compressor (16); and a turbine (28) disposed downstream of the combustor (24), wherein the combustion The combustor (24) includes an end cover (42) coupled to an outer combustor casing (44), a combustion chamber (60) defined inside the outer combustor casing (44), and the end cover (42). A gas turbine (10) including a fuel nozzle assembly (100) extending downstream from and ending upstream of the combustion chamber (60),
The fuel nozzle assembly (100) includes:
A central body (102);
An outer tube (104) at least partially surrounding the central body (102);
A premixing channel (106) defined between the central body (102) and the outer tube (104);
A plurality of fuel ports (108) disposed between the central body (102) and the outer tube (104) in the premixing channel (106), and communicated with the premixing channel (106). A plurality of fuel ports (108) including a plurality of fuel ports (108),
A baffle plate (110) extending radially and circumferentially across the downstream end portion (112) of the fuel nozzle assembly (100);
The baffle plate (110) includes an upstream side (156) that is axially spaced from the downstream side (158), and a plurality of passages (160), each passage (160) having the upstream side. An inlet (162) defined along (156) and an outlet (164) defined along the downstream side (158), the passage (160) being connected to the premix channel (106). ) and cod also the flow of fluid through the baffle plate (110) and said combustion chamber (60) from,
The upstream side (156) of the fuel nozzle assembly (100) extends radially between a plurality of concentrically aligned annular walls (166) and a radially adjacent annular wall (166). A plurality of circumferentially spaced radial walls (168), wherein said annular wall (166) and said radial wall (168) are said to said respective passages (160). inlet defining a (162) at least partially, a gas turbine (10). The upstream side (156) of the fuel nozzle assembly (100) has one or more peaks (170) and one or more ones that at least partially define the inlet (162) of one or more of the passages (160). A valley (172), wherein the peaks (170) and valleys (172) are defined between the peaks (170) adjacent to the valley (172), and the peaks (170) are adjacent to the valley (172). The gas turbine (10) of claim 15 , wherein the gas turbine (10) is alternating, as defined in between. The plurality of fuel ports (108) are concentrically disposed within the premix passage (106) and concentrically aligned with the central body (102) or the central body (102) and the outer tube (104). 15. A combustor (24) according to any one of claims 9 to 14 , disposed along at least one of struts (136) extending radially between and.