Burner for a combustor having an ammonia injection section downstream of a swozle assembly and related method

Abstract

The present invention provides a burner for a gas turbine system combustor, which has an ammonia injection section downstream of the swozle assembly. [Solution] The burner 200 comprises an outer member 212 and a central member 210 located inside the outer member, defining a fuel-air mixing passage 214 between them. A swozle assembly 220 positioned within the fuel-air mixing passage comprises a plurality of turning vanes 222 configured to give a swirling motion to the airflow through the fuel-air mixing passage. An ammonia injector system 260 is located downstream of the swozle assembly and forms an ammonia-air mixture for combustion in the combustion reaction zone in the combustion liner of the combustor. The ammonia injector system comprises a first plurality of ammonia injectors 276 configured to inject a first ammonia flow into the airflow, and optionally a second plurality of ammonia injectors configured to inject a second ammonia flow into the airflow.

Description

Technical Field

[0001] The present disclosure generally relates to gas turbine system combustors, and more specifically, to burners for combustors having an ammonia injection section downstream of a swirler assembly, combustors equipped with such burners, and related methods.

Background Art

[0002] A gas turbine system includes a combustion section having a plurality of combustors in which a flow of combustion gases is generated where fuel is burned and converted to kinetic energy in a downstream turbine section. Conventional combustors include a head end assembly having a plurality of burners for burning fuel within a combustion zone. Typically, such combustors use hydrocarbon fuels (e.g., methane or diesel fuel) that contribute to various emissions that can have a harmful impact on the environment.

[0003] One problem associated with conventional combustors is that the combustion of these hydrocarbons generally results in the formation of carbon dioxide (CO2) and nitrogen oxides (NOx), which are costly to mitigate. To reduce the amount of CO2 produced, some manufacturers have attempted to use alternative fuel sources that include hydrogen and / or ammonia, which remove carbon from the combustion products. However, current combustors present challenges regarding the use of ammonia as a fuel. Specifically, ammonia has low flammability, a low heat of combustion, and may not be sufficiently stabilized and could cause at least part of the combustion reaction to cease.

Summary of the Invention

[0004] All aspects, examples, and features described below can be combined in any technically possible form.

[0005] One aspect of the present disclosure includes a burner for a combustor of a gas turbine system, the burner comprising an outer member, a central member located inside the outer member and defining a fuel-air mixture passage between them, a swozle assembly disposed within the fuel-air mixture passage and comprising a plurality of turning vanes configured to give a swirling motion to the airflow through the fuel-air mixture passage, and an ammonia injector system located downstream of the swozle assembly and configured to form an ammonia-air mixture for combustion in a combustion reaction zone in the combustion liner of the combustor, the ammonia injector system comprising a first plurality of ammonia injectors configured to inject a first ammonia flow into an airflow, each of the first plurality of ammonia injectors having an injection axis directed upstream from a radial position toward the airflow flowing through the fuel-air mixture passage downstream of the swozle assembly.

[0006] Another aspect of the present disclosure includes the aforementioned aspect, wherein the ammonia injector system comprises a first ammonia supply line for transporting a first ammonia flow to a first plurality of ammonia injectors; a second plurality of ammonia injectors configured for injecting a second ammonia flow into an airflow; and a second ammonia supply line for transporting the second ammonia flow to a second plurality of ammonia injectors, each of which has an injection axis directed upstream toward the airflow from a radial position.

[0007] Another aspect of the present disclosure includes any of the above-described aspects, wherein the burner is configured to selectively control the flow of ammonia to one or both of a first plurality of ammonia injectors and a second plurality of ammonia injectors in response to the combustor load, and further comprises a controller configured to selectively control the flow to one or both of a first ammonia supply line and a second ammonia supply line in response to the combustor load.

[0008] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the second plurality of ammonia injectors are located axially downstream from the first plurality of ammonia injectors.

[0009] Another aspect of the present disclosure includes any of the preceding aspects, wherein the ammonia injector system comprises a first body located axially downstream of a swozle assembly, having a first ring manifold defined internally to fluidly communicate with a first ammonia supply line and a first plurality of ammonia injectors; and a second body located axially downstream of the first body, having a second ring manifold defined internally to fluidly communicate with a second ammonia supply line and a second plurality of ammonia injectors.

[0010] Another aspect of the present disclosure includes any of the above-described aspects, wherein the ammonia injector system comprises a unit having a first ring manifold defined internally to be in fluid communication with a first ammonia supply line and a first plurality of ammonia injectors, and a second ring manifold defined internally adjacent to the first ring manifold to be in fluid communication with a second ammonia supply line and a second plurality of ammonia injectors.

[0011] Another aspect of the present disclosure includes any of the embodiments described above, wherein each turning vane comprises an internal fuel passage in fluid communication with at least one fuel injector, the burner further comprises a fuel supply unit for introducing a fuel other than ammonia into the internal fuel passage for injection into the airflow, and the fuel-air mixture produced by the swozle assembly is directed to a combustion reaction zone in the combustion liner of the combustor.

[0012] Another aspect of the present disclosure includes any of the above-described aspects, wherein the burner further comprises a central fuel supply line defined within a central member, and a central fuel injector located at the downstream end of the central fuel supply line, the central fuel injector configured to produce a fuel-air mixture for combustion in the combustion reaction zone in the combustion liner of the combustor by mixing a fuel other than ammonia with another airflow.

[0013] Another aspect of the present disclosure includes a combustor for a gas turbine system, the combustor comprising a combustor body having a combustion liner, a head end assembly having a cap assembly, and a plurality of burners disposed within the cap assembly and directed toward the combustion liner, at least one of the plurality of burners comprising an outer member, a central member located inside the outer member and defining a fuel-air mixture passage between them, a swozle assembly disposed within the fuel-air mixture passage and comprising a plurality of turning vanes configured to give a swirling motion to the airflow through the fuel-air mixture passage, and downstream of the swozle assembly, and combustion An ammonia injector system configured to form an ammonia-air mixture for combustion in a combustion reaction zone in a liner, comprising a first plurality of ammonia injectors configured to inject a first ammonia flow into an air flow, and a controller configured to selectively control the ammonia flow to the first plurality of ammonia injectors in accordance with the combustor load, wherein each of the first plurality of ammonia injectors has an injection axis directed upstream from its radial position toward an air flow that flows through a fuel-air mixture passage downstream of the swozle assembly.

[0014] Another aspect of the present disclosure includes the aforementioned aspect, wherein the ammonia injector system comprises a first ammonia supply line for transporting a first ammonia flow to a first plurality of ammonia injectors, a second plurality of ammonia injectors configured to inject a second ammonia flow into an air flow, and a second ammonia supply line for transporting the second ammonia flow to a second plurality of ammonia injectors, wherein the controller is configured to selectively control the flow to one or both of the first and second ammonia supply lines in response to the combustor load.

[0015] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the second plurality of ammonia injectors are located axially downstream from the first plurality of ammonia injectors.

[0016] Another aspect of the present disclosure includes any of the preceding aspects, wherein the ammonia injector system comprises a first body located axially downstream of a swozle assembly, having a first ring manifold defined internally to fluidly communicate with a first ammonia supply line and a first plurality of ammonia injectors; and a second body located axially downstream of the first body, having a second ring manifold defined internally to fluidly communicate with a second ammonia supply line and a second plurality of ammonia injectors.

[0017] Another aspect of the present disclosure includes any of the above-described aspects, wherein the ammonia injector system comprises a unit having a first ring manifold defined internally to be in fluid communication with a first ammonia supply line and a first plurality of ammonia injectors, and a second ring manifold defined internally adjacent to the first ring manifold to be in fluid communication with a second ammonia supply line and a second plurality of ammonia injectors.

[0018] Another aspect of the present disclosure includes any of the embodiments described above, wherein each turning vane comprises an internal fuel passage in fluid communication with at least one fuel injector, the burner further comprises a fuel supply unit for introducing a fuel other than ammonia into the internal fuel passage for injection into the airflow, and the fuel-air mixture produced by the swozle assembly is directed to a combustion reaction zone in the combustion liner of the combustor.

[0019] Another aspect of the present disclosure includes any of the above-described aspects, wherein the burner further comprises a central fuel supply line defined within a central member, and a central fuel injector located at the downstream end of the central fuel supply line, the central fuel injector configured to produce a fuel-air mixture for combustion in the combustion reaction zone in the combustion liner of the combustor by mixing a fuel other than ammonia with another airflow.

[0020] Another aspect of the present disclosure includes a method for operating a combustor of a gas turbine system, the method comprising a combustor body having a combustion liner, and a head-end assembly having a plurality of burners, the head-end assembly having a plurality of burners located within the cap assembly and directed toward the combustion liner, wherein at least one of the burners has a fuel-air-mixing passage having a swozle assembly with a plurality of turning vanes configured to cause a swirl in the airflow through the fuel-air-mixing passage, the method comprising generating an ammonia-air mixture by injecting ammonia into the airflow in the fuel-air-mixing passage at one or more axial positions downstream of the swozle assembly using a plurality of upstreamly directed ammonia injectors, and burning the ammonia-air mixture formed by the plurality of burners in a combustion reaction zone in the combustion liner.

[0021] Another aspect of the present disclosure includes the aforementioned aspect, wherein the injection of ammonia into the airflow in a fuel-air mixing passage downstream of the swozle assembly is performed at two different axial positions.

[0022] Another aspect of the present disclosure includes any of the foregoing aspects, and injecting ammonia into an air stream within a fuel-air mixing passage downstream of a swirler assembly includes injecting a first volume of ammonia at a first combustor load and a second, larger volume of ammonia at a second, larger combustor load.

[0023] Two or more aspects described in this summary section, including those described above, may be combined to form implementations not specifically described herein. That is, all embodiments described herein may be combined with each other.

[0024] Details of one or more implementations are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.

[0025] These and other features of the present disclosure will be more readily understood by considering the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings that illustrate various embodiments of the present disclosure.

Brief Description of the Drawings

[0026] [Figure 1] FIG. 1 is a functional block diagram showing an exemplary gas turbine system having a combustor capable of including a burner having an ammonia injector system, according to an embodiment of the present disclosure. [Figure 2] FIG. 2 is a simplified cross-sectional side view showing an exemplary combustor that may include a burner having an ammonia injector system, according to an embodiment of the present disclosure. [Figure 3] FIG. 3 is an upstream view showing a portion of the combustor shown in FIG. 2, according to an embodiment of the present disclosure. [Figure 4] FIG. 4 is a cross-sectional side view showing a burner equipped with an ammonia injector system, according to an embodiment of the present disclosure. [Figure 5] FIG. 5 is an enlarged view showing an ammonia injector system, according to an embodiment of the present disclosure. [Figure 6] A cross-sectional view showing an ammonia injector according to an embodiment of the present disclosure. [Figure 7] A schematic view showing an ammonia injection spray from a conventional fuel injector. [Figure 8] A schematic view showing an ammonia injection spray from an ammonia injector according to an embodiment of the present disclosure. [Figure 9] A cross-sectional perspective view showing a single unit having a ring manifold for an ammonia injector according to an embodiment of the present disclosure. [Figure 10] A cross-sectional side view showing a burner including an ammonia injector system having two bodies with a ring manifold for an ammonia injector according to another embodiment of the present disclosure.

[0027] Note that the drawings of the present disclosure are not necessarily to scale. The drawings are intended to illustrate only typical aspects of the present disclosure and should not be considered as limiting the scope of the present disclosure. In the drawings, like reference numerals represent like elements among the drawings.

Mode for Carrying Out the Invention

[0028] Firstly, in order to clearly describe this disclosure, it is necessary to select specific terminology when referring to relevant mechanical components within exemplary applications of turbomachinery combustors and associated ammonia injector systems. Wherever this is done, common industrial terminology will be used and adopted in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that, in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single component may include multiple components and, in another context, be referred to as consisting of multiple components. Conversely, what may be described herein as including multiple components may, elsewhere, be referred to as a single component.

[0029] Furthermore, this specification may use several descriptive terms, and it will be useful to define these terms at the beginning of this section. Unless otherwise specified, these terms and their definitions are as follows: As used herein, “downstream” and “upstream” are terms indicating the direction of a fluid flow, such as a working fluid through a turbomachinery combustor, or a flow of air or ammonia through, for example, a combustor or heat exchanger, or a coolant through one of the turbomachinery component systems. The term “downstream” corresponds to the direction of the fluid flow, and the term “upstream” refers to the direction opposite to that flow. Unless otherwise specified, the terms “forward” and “rear” refer to directions, with “forward” referring to the front of the turbomachinery or combustor or the compressor end, and “rear” referring to the rear of the turbomachinery or combustor or the turbine end.

[0030] The term “axial direction” refers to movement or position parallel to an axis, for example, the axis of an ammonia injector, burner, combustor, or turbomachinery. The term “radial direction” refers to movement or position perpendicular to an axis, for example, the axis of an ammonia injector, burner, combustor, or turbomachinery. In such cases, if the first component is located closer to the axis than the second component, it is stated herein that the first component is “radially inward” or “inward” of the second component. On the other hand, if the first component is located further from the axis than the second component, it may also be stated herein that the first component is “radially outward” or “outward” of the second component. Finally, the term “circumferential direction” refers to movement or position around an axis, for example, the circumferential inner surface of the combustor body or the circumferential interior of the casing extending around the combustor. As mentioned above, depending on the context, it will be understood that such terms may be applied in relation to ammonia injectors, burners, combustors, or the axes of turbomachinery.

[0031] Furthermore, some descriptive terms may be used repeatedly in this specification, as described below. The terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, but are not intended to indicate the location or importance of any individual component.

[0032] The technical terms used herein are intended solely to describe specific embodiments and are not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural unless the context otherwise explicitly indicates. As used herein, the terms “comprise” and / or “comprising” express the existence of the described features, integers, steps, actions, elements, and / or components, but it will be further understood that this does not exclude the existence or addition of one or more other features, integers, steps, actions, elements, components, and / or sets thereof. “Optional” or “optional” means that the events described later may or may not occur, or the features described later may or may not exist, and that the description includes both instances in which the events occur or the features exist, and instances in which the events do not occur or the features do not exist.

[0033] When an element or layer is referred to as “on top of,” “engaged,” “connected,” “joined,” or “attached” to another element or layer, it may be directly on top of, engaged with, connected to, joined to, or attached to the other element or layer, or there may be an intervening element or layer. In contrast, when an element is referred to as “directly on top of,” “directly engaged,” “directly connected,” or “directly joined,” there is no intervening element or layer. Other words used to describe the relationship between elements should be interpreted similarly (e.g., “between” and “directly between,” “adjacent” and “directly adjacent”). As used herein, the term “and / or” includes any combination of one or more of the related enumerated items. The verb forms “join” and “attach” may also be used interchangeably herein.

[0034] Embodiments of the present disclosure provide a burner, combustor, and associated method for a combustor of a gas turbine system. The burner comprises an outer member and a central member located inside the outer member and defining a fuel-air mixture passage between them. A swozle assembly is positioned within the fuel-air mixture passage. The swozle assembly comprises, among other things, a plurality of turning vanes configured to give a swirling motion to the airflow through the fuel-air mixture passage. An ammonia injector system is located downstream of the swozle assembly and is configured to form an ammonia-air mixture for combustion in a combustion reaction zone defined within the combustion liner of the combustor. The ammonia injector system comprises a first plurality of ammonia injectors configured to inject a first ammonia flow into the airflow and a second plurality of ammonia injectors configured to inject a second ammonia flow into the airflow. Each ammonia injector has an injection axis directed upstream from its radial position toward the airflow through the fuel-air mixture passage downstream of the swozle assembly.

[0035] This ammonia injector system provides an efficient method for injecting liquid ammonia using ammonia injectors that are inclined and oriented toward the airflow path to prevent film formation on the walls of the fuel-air mixture passage. This set of ammonia injectors allows for the injection of varying amounts of ammonia based on different combustor loads, ensuring the formation of fine ammonia droplets. At lower combustor loads, one set of ammonia injectors can be used for liquid ammonia injection, while the other set can operate for purging (air only). The burners described herein provide ammonia injection in varying volumes based on different combustor loads, resulting in more precise and stable combustion. Furthermore, the angling (or "tilting") of the ammonia injectors is more efficient in avoiding film formation on the fuel-air mixture passage and results in improved ammonia dispersion that does not destabilize the combustion reaction.

[0036] Referring here to the drawings, Figure 1 shows a schematic diagram of an exemplary gas turbine system 100 (GT system 100). The GT system 100 generally comprises an inlet section 112, a compressor 114 located downstream of the inlet section 112, a combustion system 116 having at least one combustor 118 located downstream of the compressor 114, a turbine 120 (i.e., an expansion turbine) located downstream of the combustor 118, and an exhaust section 122 located downstream of the turbine 120. Furthermore, the GT system 100 may include one or more shafts 124 connecting the compressor 114 to the turbine 120. During operation, air 126 flows through the inlet section 112 to the compressor 114, where the air 126 is gradually compressed, thereby supplying compressed air 128 to the combustor 118. One or more fuels 130 from one or more fuel supply units 132 are injected into the combustor 118 and mixed with a portion of the compressed air 128 to burn, producing combustion gases 134. The combustion gases 134 flow from the combustor 118 to the turbine 120, where (kinetic and / or thermal) energy is transferred from the combustion gases 134 to the rotor blades (not shown), thereby causing the shaft 124 to rotate. This mechanical rotational energy can then be used for various purposes, such as supplying power to the compressor 114 and / or generating electricity. The combustion gases 134 then exiting the turbine 120 can be exhausted from the GT system 100 through the exhaust section 122.

[0037] In one embodiment, the GT system 100 may be applicable to current engine models commercially available from GE Vernova in Cambridge, Massachusetts. This disclosure is not limited to any one specific GT system and may be implemented in relation to other engines, including, for example, any HA, F, B, LM, GT, TM, and E-class engine models from GE Vernova, as well as engine models from other companies.

[0038] Figure 2 shows a schematic cross-sectional view of an exemplary combustor 118 that may incorporate various embodiments of the present disclosure. As shown in Figure 2, the combustor 118 may be at least partially enclosed by an outer casing 136, such as a compressor discharge casing. The outer casing 136 may at least partially define a high-pressure plenum 138 that at least partially encloses various components of the combustor 118. The high-pressure plenum 138 may receive at least a portion of compressed air 128 from a compressor 114 (Figure 1) by fluid communication with it. The high-pressure plenum 138 may supply compressed air 128 to various parts of the multi-fuel burner 200 described herein.

[0039] An end cover 140 may be coupled to the outer casing 136. The end cover 140 may have any passages or openings necessary for delivering fuel, such as natural gas, liquid fuel, ammonia, or compressed air 128, through it, as described herein. For example, the end cover 140 may have any passages or openings necessary for fuel supply lines 280, 282 (Figures 4-5) and 320 (Figure 10) to pass through it. The end cover 140 may be configured to detachably house multi-fuel burners 200, 202 (hereinafter referred to as "burner 200" or "central burner 202" for distinction unless otherwise specified) within a head end assembly 143 of the combustor 118, which includes, for example, a cap assembly 150 in which the rear end of a burner 200 is positioned at an opening. In this way, the removal of the burner 200 can be achieved by detaching the end cover 140 and / or a portion of the burner 200 from its connection to the head end assembly 143, and then sliding the burner 200 off.

[0040] The end cover 140 can be selectively coupled to the head-end assembly 143 by any known or future-developed method, including but not limited to screw fasteners (not shown). The outer casing 136 and the end cover 140 can at least partially define the head-end volume, i.e., chamber 142, within the head-end assembly 143 of the combustor 118. In certain embodiments, the head-end volume 142 is in fluid communication with the high-pressure plenum 138 and / or compressor 114. One or more liners or ducts can form a combustion liner 144, which can at least partially define a combustion reaction zone, i.e., chamber 146, for burning one or more fuel-air mixtures, and can at least partially define a high-temperature gas path 148 through the combustor 118 for directing the combustion gases 134 toward an inlet leading to the turbine 120.

[0041] Figure 3 shows an upstream view of a portion of the combustor 118 shown in Figure 2. In various embodiments, as shown collectively in Figures 2 and 3, the combustor 118 comprises a plurality of burners or fuel nozzles (e.g., reference numeral 200) having an upstream end coupled to an end cover 140 and extending toward a combustion reaction zone 146. The downstream end of a burner 200 is aligned with a corresponding opening (not shown) in a cap assembly 150 so that the burner 200 delivers a fuel / air mixture to a combustion reaction zone 146 defined by a combustion liner 144.

[0042] Various embodiments of the combustor 118 may include various numbers and arrangements of burners 200, and the embodiments described herein are not limited to any particular number of burners unless otherwise specified in the claims. For example, in certain configurations such as the one shown in Figure 3, one or more burners comprise a plurality of multi-fuel burners 200 arranged in a ring around a central burner 202. In other embodiments, the burners 200 may be arranged in a ring around the centerline of the end cover 140 without using a central burner 202. The central burner 202 may also be a premixed multi-fuel (liquid and gaseous fuel) type burner. If desired, other types of burners may be used instead of the central burner 202. As described herein, the central burner 202 may be the same as the burners 200. Each of the burners 200 may be a premixed multi-fuel type burner. More specifically, each of the burners 200 may be used to burn a gaseous fuel such as natural gas and / or ammonia, where ammonia is liquid. Each burner 200 is configured to inject gaseous fuel and / or liquid fuel and premix with a portion of the flow of compressed air 128 from the head-end volume section 142 (Figure 2) in the head-end assembly 143 located upstream from the combustion reaction zone 146.

[0043] Figure 4 shows a cross-sectional side view of an exemplary burner 200 (or 202) having premixing and multi-fuel functions according to at least one embodiment of the present disclosure. In certain embodiments, such as the embodiment shown in Figure 4, the burner 200 comprises a central member 210 and an outer member 212, each exhibiting an annular or tubular shape. More specifically, the burner 200 may include an outer member, i.e., a burner tube 212, extending circumferentially and concentrically around at least a portion of the central member 210. As shown, the central member 210 is inside the outer member 212, with a fuel-air mixing passage 214 defined between them. The burner 200 also includes a swozle assembly 220 positioned in the fuel-air mixing passage 214. The swozle assembly 220 comprises a plurality of turning vanes 222 configured to give a swirling motion to the airflow 234 flowing into the fuel-air mixing passage 214 through gaps between circumferentially adjacent turning vanes 222. More specifically, a plurality of turning vanes 222 extend between the central member 210 and the outer member 212. The turning vanes 222 are arranged within the fuel-air mixing passage 214, which may be annular in shape and, as described above, can be defined radially between the central member 210 and the outer member 212.

[0044] The swozle assembly 220 may be used solely to generate a swirling airflow 234 for mixing with ammonia from the ammonia injector system 260, as described herein, and / or to generate a fuel-air mixture. With regard to the latter function, one or more of the turning vanes 222 may comprise one or more fuel injectors 224 that are in fluid communication with a fuel plenum 226 defined in the central member 210 or other gas fuel source. The fuel plenum 226 receives gas fuel 230, for example, by being fluidly coupled to a fuel supply unit 228 (Figure 4). More specifically, each turning vane 222 may comprise an internal fuel passage 232 that is in fluid communication with at least one fuel injector 224. The fuel supply unit 228 introduces fuel other than ammonia 230 into the internal fuel passage 232 (via the fuel plenum 226) for injection into the airflow 234. Thus, the swozle assembly 220 generates a fuel-air mixture that is directed into the combustion reaction zone 146 in the combustion liner 144 of the combustor 118. In one example, the fuel 230 may be natural gas, which, when mixed with the airflow 234, produces a fuel-air mixture for combustion in the combustion reaction zone 146. In certain cases, the fuel 230 to the swozle assembly 220 may be stopped using a control valve 235 controlled, for example, by a controller 236 (e.g., a controller for the combustor 118 or another system), so that only the (swirling) airflow 234 exits the swozle assembly 220. The controller 236 will be described further herein. This arrangement may be used, for example, when ammonia, rather than natural gas, is used as the fuel for combustion, as described herein.

[0045] As shown in Figure 4, the central member 210 may be formed from one or more sleeves or tubes 240 that are coaxially aligned with a common longitudinal axis or axial centerline 242 of the central member 210 and the burner 200. The axial centerline 242 of the central burner 202 also coincides with the axial centerline of the cap assembly 150. The burner 200 may be connected to the inner surface of the end cover 140 via mechanical fasteners or by other connecting means (not shown). In certain embodiments, as shown in Figure 4, the upstream end portion 244 of the outer member 212 may at least partially define an inlet 246 leading to the fuel-air mixing passage 214, and the downstream end portion 248 of the outer member 212 may at least partially define an outlet 250 leading to the fuel-air mixing passage 214, i.e., the combustion reaction zone 146. In at least one embodiment, the inlet 246 is in fluid communication with the head end volume section 142 (Figure 2) within the head end assembly 143 of the combustor 118, thereby receiving compressed air 128 within it.

[0046] Figure 5 shows an enlarged view of the ammonia injector system 260 of the burner 200 shown in Figure 4. In various embodiments, the examples of which are collectively shown in Figures 4 and 5, the burner 200 is equipped with the ammonia injector system 260 downstream of the swozle assembly 220. The ammonia injector system 260 is configured to form an ammonia-air mixture 262 for combustion in the combustion reaction zone 146 in the combustion liner 144 of the combustor 118. In certain cases, the ammonia-air mixture 262 may be mixed with a mixture of fuel 230 (Figure 4) from the swozle assembly 220 and airflow 234 (i.e., a mixture of natural gas and air, fuel and air), but this is not always necessary.

[0047] The ammonia injector system 260 comprises a first plurality or set of ammonia injectors 272 configured to inject a first ammonia flow 274 into an air flow 234 (from the swozle assembly 220), and a second plurality or set of ammonia injectors 276 configured to inject a second ammonia flow 278 into the air flow 234. Figures 6 to 8 show various diagrams of the ammonia injectors 272, 276 according to embodiments of the present disclosure, which are described in detail herein. Following Figures 4 and 5, the ammonia injector system 260 comprises a first ammonia supply line 280 that delivers the first ammonia flow 274 to the first plurality of ammonia injectors 272, and a second ammonia supply line 282 that delivers the second ammonia flow 278 to the second plurality of ammonia injectors 276. The ammonia supply lines 280 and 282 may be equipped with any suitable conduits or tubes that are suitable for transporting ammonia and can withstand the high-temperature environment of burner 200.

[0048] The ammonia injector system 260 may also include a controller 236 configured to selectively control the flow of ammonia to one or both of a first set of ammonia injectors 272 and a second set of ammonia injectors 276, depending on the combustor load. The controller 236 may be part of any known or hereafter developed combustor control system or GT system 100 (Figure 1) and may include any hardware and / or software configured to perform the functions described herein. For example, the controller 236 may be configured to selectively control the flow from the ammonia supply unit 285, and therefore from the corresponding set of ammonia injectors 272, 276 fluid-coupled to the ammonia supply unit, to one or both of a first ammonia supply line 280 and a second ammonia supply line 282, by, for example, controlling a valve 283. Whether to use one or both sets of ammonia injectors 272, 276 depends on the combustor load. As used herein, “combustor load” is the amount of combustion that needs to be produced by the combustor 118 based on the requirements of the turbine 120 (Figure 1), or other operating parameters such as airflow 234, environmental conditions, and flow rate, and can be calculated in any desirable way based on data provided to the controller 236.

[0049] Returning to Figure 4, a plurality of ammonia injectors 272, 276 can be provided in various forms according to embodiments of the present disclosure. In Figure 4, the ammonia injector system 260 comprises a single unit, i.e., a manifold body 300, having a first ring manifold 302 defined internally to fluidly communicate with a first ammonia supply line 280 and a first plurality of ammonia injectors 272. The first body 300 also comprises a second ring manifold 304 defined internally adjacent to the first ring manifold 302 to fluidly communicate with a second ammonia supply line 282 and a second plurality of ammonia injectors 276. It should be noted that, as used herein, the manifolds 302, 304 are referred to as “ring manifolds,” but may extend over any necessary circumferential range to supply fuel plenum to any desired ammonia injectors 272, 276, and may not extend in a complete circle within a defined corresponding body 300 (310, 316 (Figure 10)). The main body 300 may be coupled to or integrated with the central member 210 by any known method.

[0050] Figure 9 shows a cross-sectional view of a single unit 300 of the ammonia injector system 260 according to a particular embodiment. The first plurality of ammonia injectors 272 and the second plurality of ammonia injectors 276 may be arranged circumferentially around the single unit 300 in any way, or they may be arranged at approximately equal distances within a given plurality of ammonia injectors to distribute ammonia more uniformly. The plurality of ammonia injectors 272, 276 may also be arranged uniformly circumferentially from each other, for example, every other ammonia injector may belong to one of the plurality of ammonia injectors. The ring manifolds 302, 304 are adjacent to each other, meaning they are arranged at a distance from each other so as not to interfere with each other. In some embodiments, the ring manifolds 302, 304 may be arranged axially within the single unit 300, i.e., axially with respect to the centerline 242 of the burner 200. For example, the second ring manifold 304 may be axially downstream from the first ring manifold 302 within the single unit 300. In contrast, in Figures 4 and 9, the ring manifolds 302 and 304 are arranged radially apart from each other with a partition wall 306 in between. The passage 308 fluid-couples the (inner) ring manifold 302 to a first group of ammonia injectors 272, for example, one passage to each ammonia injector 272. Because the ring manifold 304 is located just radially inward from the ammonia injectors 276 (or the openings in which they are seated), a passage within the unit 300 may not be required (or the passage may be very short) for the ring manifold 304 to fluid-couple to the ammonia injectors 276.

[0051] In both cases, as shown in Figures 4 and 9, the first ammonia supply line 280 and the first plurality of ammonia injectors 272 are fluid-coupled by a first ring manifold 302 (and passage 308) defined within unit 300, and the second ammonia supply line 282 and the second plurality of ammonia injectors 276 are fluid-coupled by a second ring manifold 304 defined within unit 300. Thus, the controller 236 can control which of the ammonia injectors 272 and 276 injects ammonia by controlling valves 283 that control the flow of ammonia to each ammonia supply line 280, 282. The controller 236 can direct ammonia to the first plurality of ammonia injectors 272 and / or the second plurality of ammonia injectors 276. The controller 236 can also control the volume of ammonia delivered to each of the plurality of ammonia injectors 272, 276 by controlling the open / closed level of valves 283. In this way, the volume of ammonia injected into the fuel-air mixing passage 214 can be controlled based on the combustor load.

[0052] Referring to Figure 10, in another embodiment, the second plurality of ammonia injectors 276 may be located axially downstream from the first plurality of ammonia injectors 272 in a separate second body 316. Here, the ammonia injector system 260 comprises a first body 310 axially downstream of the swozle assembly 220. The first body 310 has a first ring manifold 314 defined internally to fluidly communicate with a first ammonia supply line 280 and the first plurality of ammonia injectors 272. Furthermore, the ammonia injector system 260 comprises a second body 316 axially downstream of the first body 310. The second body 316 has a second ring manifold 318 defined internally to fluidly communicate with a second ammonia supply line 282 and the second plurality of ammonia injectors 276. The first plurality of ammonia injectors 272 and the second plurality of ammonia injectors 276 may be arranged in any way circumferentially around the corresponding bodies 310, 316, respectively, but typically they are arranged equidistant within a given plurality of ammonia injectors to ensure a more uniform distribution of ammonia. Each of the plurality of ammonia injectors 272, 276 may also be circumferentially offset from each other within the corresponding bodies 310, 316 so that ammonia injector 272 does not inject ammonia along the same axis as any of the downstream ammonia injectors 276. However, any circumferential arrangement is possible to achieve the desired ammonia-air mixture 262. Furthermore, the first body 310 and the second body 316 may be arranged axially in any way to set different plurality of ammonia injectors 272, 276 in different axial positions, for example, directly adjacent to (in contact with) each other, or at any desired axially separated distance, i.e., within the central member 210. Any axial spacing is possible to achieve the desired ammonia-air mixture 262.

[0053] As shown in Figure 10, the first ammonia supply line 280 and the first plurality of ammonia injectors 272 are fluid-coupled by a first ring manifold 314 defined within the first body 310, and the second ammonia supply line 282 and the second plurality of ammonia injectors 276 are fluid-coupled by a second ring manifold 318 defined within the second body 316. The controller 236 can control which of the ammonia injectors 272 and 276 injects ammonia by controlling valves 283 that control the flow of ammonia to each of the ammonia supply lines 280 and 282. As described above, the controller 236 can direct ammonia to the first plurality of ammonia injectors 272 and / or the second plurality of ammonia injectors 276. The controller 236 can also control the volume of ammonia delivered to each of the plurality of ammonia injectors 272 and 276 by controlling the open / closed level of valves 283. In this way, the volume of ammonia injected into the fuel-air mixing passage 214 can be controlled based on the combustor load.

[0054] Referring further to Figures 5 and 10, the burner 200 may also optionally include a central fuel supply line 320 defined within the central member 210 and a central fuel injector 322 located at the downstream end 324 of the central fuel supply line 320. Note that although the central fuel passage and injector are omitted in the diagram shown in Figure 4, they can also be included. As illustrated, the central fuel supply line 320 and the central fuel injector 322 may be located within the central member 210. The central fuel injector 322 is configured to mix a fuel other than ammonia 328 with another airflow 128 (e.g., an airflow from the fuel-air mixing passage 214 or a passage within the central member 210 from the swozle assembly 220) to produce a fuel-air mixture 330 for combustion in the combustion reaction zone 146 in the combustion liner 144 of the combustor 118. The fuel 328 may be a liquid fuel, such as fuel oil. The central fuel injector 322 is axially oriented with respect to the axial centerline 242 and is in fluid communication with the fuel supply unit 332 via the central fuel supply line 320. During operation, the central fuel injector 322 injects atomized liquid fuel 328 into the combustion zone 146 at a location downstream from the swozle assembly 220 and downstream from several ammonia injectors 272, 276. In certain embodiments, the central fuel injector 322 may be screwed, threaded, or otherwise removable within the central member 210 to facilitate maintenance (e.g., cleaning) and / or replacement as needed.

[0055] In various embodiments, as shown in Figures 5 and 10, a portion of the central fuel supply line 320 located within the central member 210 and downstream of the main body 300 (Figure 5) or the main bodies 310, 316 (Figure 10) may extend spirally around the axial centerline 242 of the burner 200. During operation, the spiral portion of the central fuel supply line 320 acts as a spring, expanding and contracting the fuel passage due to thermal differences between various parts of the burner 200. The central fuel supply line 320 may also be fluid-coupled to a fuel supply section 332 (Figure 10), from which it receives, for example, liquid fuel 328. The controller 236 can control the flow of liquid fuel 328 by controlling any number of valves 334. The central fuel supply line 320 may be piped in any way together with the ammonia supply lines 280, 282. For example, the individual unit 300 (Figures 4-5) or the first body 310 and the second body 316 (Figure 10) may each have a central opening 338 that allows the passage of the central fuel supply line 320. The central opening 338 also allows compressed air 128 to pass through to produce a fuel-air mixture 330. The central fuel injector 322 may have any known or future-developed fuel injector structure for the fuel used.

[0056] Furthermore, with respect to the supply of ammonia to the ammonia injector system 260, as shown in Figures 4 and 10, manifolds 302, 304, 314, and 318 are fluidly coupled to the ammonia supply section 228 via fuel supply lines 280 and 282. At least a portion of the ammonia supply lines 280 and 282 may extend at least partially helically within the central member 210, around or near the central fuel supply line 320 (if provided), and in front of the upstream unit 300 (Figure 4) or the first body 310 (Figure 10), around or near each other. The ammonia supply lines 280 and 282 are also arranged radially inward from the gas fuel plenum 226. In Figures 4 and 5, the rear end of the first ammonia supply line 280 is fluid-coupled to the unit 300 and ring manifold 302 located within it, and in Figure 10, the rear end of the first ammonia supply line 280 is fluid-coupled to the first body 310 and ring manifold 314 located within it. In Figures 4 and 5, the rear end of the second ammonia supply line 282 is fluid-coupled to the unit 300 and ring manifold 302 located within it, and in Figure 10, the rear end of the second ammonia supply line 282 is fluid-coupled to the second body 316 and ring manifold 318 located within it. In Figure 10, the second ammonia supply line 282 extends through the first body 310 so as not to interfere with the ring manifold 314 or ammonia injector 272 within the first body 310. A second ammonia supply line 282 of any extent necessary to reach the second body 316 may be used between the first body 310 and the second body 316.

[0057] The main body 300 or the main bodies 310, 316 are attached to the central member 210 in any desirable manner. The central opening 338 of the main body 300 (Figures 4-5) or the first main body 310 and the second main body 316 (Figure 10) is removed from the central fuel supply line 320, allowing the passage of compressed air 128. Thus, in certain embodiments, the central fuel supply line 320 passing through the central opening 338 is not restricted in its thermal expansion or movement.

[0058] The first ammonia supply line 280 and / or the second ammonia supply line 282 may include portions that are helical or wound to function like springs. In the illustrated embodiment, lines 280 and 282 are wound in the same direction (e.g., clockwise or counterclockwise). The winding of the ammonia supply lines 280 and 282 adjusts the temperature differences between the various parts of the burner 200 to transfer heat to the ammonia flow within it. The first supply line 280 and the second supply line 282 do not intersect the axial centerline 242 of the burner 200, but rather are radially outward.

[0059] The details of the ammonia injectors 272 and 276 will be described with reference to Figure 6. As mentioned above, Figure 6 shows a cross-sectional view of the ammonia injectors 272 and 276 according to an embodiment of the present disclosure. The ammonia injectors 272 and 276 may be arranged circumferentially around / inside the corresponding body 300 (Figures 4-5) or body 310, 316 (Figure 10), and are in fluid communication with the corresponding ring manifolds 302, 304 (Figures 4-5) or 314, 318 (Figure 10), respectively. To prevent the formation of an ammonia (NH3) film on the walls of the fuel-air mixing passage 214, each of the first plurality of ammonia injectors 272 and each of the second plurality of ammonia injectors 276 has an injection axis Ai directed upstream from a radial position R (with respect to the centerline 242 of the burner 200) toward the airflow 234 flowing through the fuel-air mixing passage 214 downstream of the swozle assembly 220. The injection axis Ai may be offset by an angle α with respect to the radial position R. The angle α may be in the range of, for example, 15° to 65° from the radius R. The angle α may be selected based, for example, on the properties of the airflow 234 and / or liquid ammonia and the desired atomization of ammonia. Therefore, the ammonia injectors 272 and 276 are oriented non-radially with respect to the axial centerline 242, injecting ammonia atomizing jets 274 and 278 into the fuel-air mixing passage 214 at a position downstream from the swozle assembly 220, the turning vane 222, and / or the gas fuel injector 224. Although the first plurality of ammonia injectors 272 and the second plurality of ammonia injectors 276 are exemplified as having injection axis Ai of the same angle α, it should be understood that the first plurality of ammonia injectors 272 may have an injection axis Ai of a first angle different from the second angle of the injection axis Ai of the second plurality of ammonia injectors 276. The angles may be in the range of 15° to 65° from the radius R.

[0060] The ammonia injectors 272, 276 may be screwed, threaded, or otherwise removable into corresponding openings 340 in the individual unit 300 (Figures 4-5) or the main body 310, 316 (Figure 10) to facilitate maintenance (e.g., cleaning) and / or replacement, if necessary. The openings 340 are also shown in Figure 9. The fuel injectors 272, 276 and / or openings 340 may be structured and / or arranged to produce a desired injection axis Ai, for example, by an angled nozzle passage within the injector body or a straight passage within the injector body positioned within the angled opening 340. The fuel injectors 272, 276 may also take the form of any nozzle or atomizer capable of converting liquid ammonia into a mist of very fine droplets.

[0061] Figure 7 shows a schematic diagram of a conventional ammonia injection in which the radially extending (R) injection axis is perpendicular to the airflow 234, and Figure 8 shows a schematic diagram of an ammonia injection according to an embodiment of the present disclosure in which the injection axis Ai is oriented at an angle α with respect to the radial position R. In Figure 7, the leeward or downstream side of the ammonia spray 344 is shielded by the leeward or upstream side of the ammonia spray 346, thereby preventing ammonia atomization and forming a high-density region 348 that can form a film 350 against the wall of the fuel-air mixing passage 214. The film 350 prevents efficient combustion of the ammonia-air mixture in the combustion reaction zone 146. In contrast, in Figure 8, the leeward side (downstream side) 352 of the ammonia sprays 274 and 278, and the leeward side (upstream side) 354 of the ammonia sprays 274 and 278 are directed more uniformly towards the airflow 234, which allows for better atomization of ammonia in the ammonia-air mixture 262, resulting in little to no film formation (Figure 7) and more efficient combustion of the ammonia-air mixture 262 in the combustion reaction zone 146.

[0062] In certain embodiments, as shown in Figures 4, 5, and 10, the burner 200 may include an air shield, or deflector 342, that extends circumferentially around the central fuel supply line 320 and the ammonia supply lines 280, 282. As shown in Figures 4, 5, and 10, the air shield 342 is positioned upstream from the front side wall of the body 300 (Figures 4-5) or the body 310 (Figure 10).

[0063] A method for operating the combustor 118 of the GT system 100 according to embodiments of the present disclosure is described. During operation, embodiments of the method include burning an ammonia-air mixture 262 formed by the burners 200 in a combustion reaction zone 146 in the combustion liner 144. As described above, the combustor 118 comprises a combustor body 141 with a combustion liner 144 and a head end assembly 143 with a cap assembly 150. The combustor 118 also comprises a plurality of burners 200 positioned within the cap assembly 150 and directed toward the combustion liner 144. Each burner 200 has a fuel-air mixture passage 214 having a swozle assembly 220 with a plurality of turning vanes 222 configured to give a swirling motion to the airflow 234 flowing through the fuel-air mixture passage 214. The method includes generating an ammonia-air mixture 262 by injecting ammonia using a plurality of ammonia injectors 272, 276 directed upstream toward the airflow 234 in the fuel-air mixing passage 214 at one or more axial positions downstream of the swozle assembly 220. During the injection of ammonia using the ammonia injector system 260, the injection of gaseous fuel 230 using the swozle assembly 220 may be stopped, and as a result the swozle assembly 220 will generate the ammonia-air mixture 262 by supplying only the airflow 234. Figures 4 and 5 show ammonia injectors 272, 276 at one axial position. As shown in Figure 10, the injection of ammonia into the airflow 234 in the fuel-air mixing passage 214 downstream of the swozle assembly 220 may be carried out using a first body 310 and a second body 316 having ammonia injectors 272, 276 at two different axial positions, i.e., one or more axial positions. The method also includes burning an ammonia-air mixture 262 formed by a plurality of burners 200 within a combustion reaction zone 146 in a combustion liner 144. Referring to Figures 4 and 10, in certain embodiments, the method may also include injecting ammonia into the airflow 234 in a fuel-air mixing passage 214 downstream of the swozle assembly 220 in varying volumes depending on the combustor load.For example, ammonia injection may include injecting a first volume of ammonia at a first combustor load and a second, larger volume of ammonia at a second, larger combustor load. The controller 236 may control the fuel flow of any fuel containing ammonia using valves 235, 283, and / or 334. In certain embodiments, ammonia may be injected at an air ratio of 1.1 to 1.5. In some embodiments, as shown in Figures 5 and 10, the method may further include injecting liquid fuel from a central fuel injector 322 located downstream of the ammonia injector system 260 so that the liquid fuel-air mixture is introduced into the combustion reaction zone 146 within the combustion liner 144.

[0064] The burner 200 and its components may be made of any known or hereafter developed flame-resistant and oxidation-resistant material. This material may be a metal, a pure metal, or an alloy. The burner 200 is typically used in turbine components such as turbine blades or nozzles and may contain metals that are more heat-resistant and oxidation-resistant than materials typically used in combustion hardware. In this case, the material may include, but is not limited to, cobalt-chromium-molybdenum (CoCrMo) alloys, stainless steel, austenitic nickel-chromium-based alloys such as nickel-chromium-molybdenum-niobium alloy (NiCrMoNb) (e.g., Inconel 625 or Inconel 718), nickel-chromium-iron-molybdenum alloy (NiCrFeMo) (e.g., Hastelloy® X, available from Haynes International, Inc.), nickel-chromium-cobalt-molybdenum alloy (NiCrCoMo) (e.g., Haynes 232 or Haynes 282, available from Haynes International, Inc.), or nickel-chromium-cobalt-titanium alloy (NiCrCoTi) (e.g., GTD 262, developed by General Electric Company), and other non-reactive metals made from non-explosive or non-conductive powders. Other candidates include, for example, Rene 108, CM 247, Mar M 247, and any precipitation-hardening (PH) nickel alloys.

[0065] In certain embodiments, the burner 200 may be additively manufactured using any known or future-developed technique capable of forming a single, integrated body. Thus, different components may comprise multiple parallel sintered metal layers. Other manufacturing methods are also possible.

[0066] As shown in Figure 2, embodiments of the present disclosure may also include a combustor 118 for the GT system 100. The combustor 118 comprises a combustor body 141 with a combustion liner 144. The combustor 118 also comprises a head-end assembly 143 with burners 200 as described herein, the central burner 202 optionally directed toward the combustion liner 144. The burners 200 may be as described herein and directed toward the combustion liner 144. The combustor 118 generally terminates at a point adjacent to the turbine 120. The first stage of the stationary nozzle at least partially defines the turbine inlet leading to the turbine 120. The combustor body 141, i.e., the combustion liner 144, at least partially defines a high-temperature gas path (HGP) for delivering combustion gases 134 from the combustion reaction zone 146 to the turbine 120 during the operation of the GT system 100.

[0067] Embodiments of the present disclosure may also include a GT system 100 having an inlet section 112, a combustion system 116 having a compressor 114 disposed downstream of the inlet section 112, at least one combustor 118 disposed downstream of the compressor 114, and a turbine 120 disposed downstream of the combustor 118, as shown in Figure 1. The combustor 118 is operably coupled to the compressor 114, and the turbine 120 is operably coupled to the combustor 118. As described herein, the combustor 118 includes a combustor body 141 with a combustion liner 144, and a head-end fuel nozzle assembly 143 at the front end of the combustor body 141. The combustor 118 may also include burners 200 as described herein. The head-end assembly 143 includes a plurality of burners 200 directed into the combustion liner 144, as described herein.

[0068] This disclosure offers various technical and commercial advantages, examples of which are discussed herein. The burners described herein provide ammonia injection at various volumes based on various combustor loads, resulting in more precise and stable combustion. Furthermore, the angle of the ammonia injector is efficient in avoiding film formation in the fuel-air mixture passage and results in improved ammonia dispersion without destabilizing the combustion reaction.

[0069] Throughout this specification and the claims, the approximation language used herein may be applied to modify any quantitative expression that is permitted to vary without altering the underlying function. Thus, values ​​modified by one or more terms such as “about,” “approximately,” and “substantially” are not limited to the exact values ​​specified. In at least some cases, the approximation language may correspond to the precision of the instrument used to measure the value. Herein, and throughout this specification and the claims, range limitations are combinatorial and / or substitutable, and unless otherwise indicated by context or language, such ranges are identified and include all subranges encompassed therein. “Approximately” or “about” applied to a particular value within a range may indicate + / - 10% of the stated value, unless applied to the values ​​at both ends and particularly dependent on the precision of the instrument used to measure that value.

[0070] All means or step-plus-function elements in the following claims are intended to include any structures, materials, or actions for performing a function in combination with any other claimed elements specifically claimed. The descriptions in this disclosure are presented for illustrative and explanatory purposes only, and are not intended to be exhaustive or to be limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. The embodiments have been selected and described to best illustrate the principles of this disclosure and the practical application of the art, and to enable those skilled in the art to understand this disclosure in order to consider various modifications to these embodiments that may be suitable for the particular use under consideration. [Explanation of Symbols]

[0071] 100 Gas Turbine (GT) System 112 Entrance Section 114 Compressor 116 Combustion System 118 Combustor 120 Turbine 122 Exhaust Section 124 shaft 126 Air 128 Compressed air, airflow 130 Fuel 132 Fuel supply section 134 Combustion gases 136 Outer casing 138 High-pressure plenum 140 End Cover 141 Combustion unit 142 Head end volume section, chamber 143 Head-end assembly, head-end fuel nozzle assembly 144 Combustion Liner 146 Combustion reaction zone, chamber 148 High-temperature gas pathway 150 Cap Assembly 200 Multi-fuel burners, burners 202 Multi-fuel burner, central burner 210 Central member 212 Outer components, burner tube 214 Fuel-air mixing passage 220 Swozle Assembly 222 Turning vane 224 Fuel Injector 226 Fuel Plenum, Gas Fuel Plenum 228 Fuel supply unit, ammonia supply unit 230 gas fuel, fuel 232 Internal fuel passage 234 Airflow 235 Control valves, valves 236 Controllers 240 sleeves, tubes 242 Axial center line, center line 244 Upstream end part 246 Entrance 248 Downstream end part 250 exit 260 Ammonia Injector System 262 Ammonia-air mixture 272 First set of multiple ammonia injectors, first set of ammonia injectors, ammonia injector, fuel injector 274 First ammonia stream, ammonia atomizing jet, ammonia spray 276 Second set of ammonia injectors, second set of ammonia injectors, ammonia injector 278 Second ammonia stream, ammonia atomizing jet, ammonia spray 280 Fuel supply line, first ammonia supply line, ammonia supply line 282 Fuel supply line, second ammonia supply line, ammonia supply line 283 valves 285 Ammonia Supply Unit 300 Unit, First main unit, Main unit 302 First ring manifold, ring manifold, manifold 304 Second ring manifold, ring manifold, manifold 306 Partition wall 308 Passage 310 First main body, main body 314 First ring manifold, ring manifold, manifold 316 Second main body, main body 318 Second ring manifold, ring manifold, manifold 320 Central Fuel Supply Line 322 Central Fuel Injector 324 Downstream end 328 Fuel, liquid fuel 330 Fuel-Air Mixture 332 Fuel supply section 334 valves 338 Central opening 340 opening 342 Air Shield, Deflector 344 Ammonia spray 346 Ammonia spray 348 High density area 350 membrane 352 Downwind side, downstream side 354 Upwind side, upstream side

Claims

1. A burner (200) for a combustor (118) of a gas turbine system (100), Outer member (212) and Located inside the aforementioned outer member (212), a central member (210) defines a fuel-air mixing passage (214) between them, A swozle assembly (220) disposed within the fuel-air mixing passage (214), comprising a plurality of turning vanes (222) configured to give a swirling motion to the airflow (234) flowing through the fuel-air mixing passage (214), An ammonia injector system (260) located downstream of the swozle assembly (220) and configured to form an ammonia-air mixture (262) for combustion in the combustion reaction zone (146) of the combustion liner (144) of the combustor (118), wherein the ammonia injector system (260) The system comprises a first plurality of ammonia injectors (272) configured to inject a first ammonia stream (274) into the air stream (234), Each of the first plurality of ammonia injectors (272) has an injection axis (Ai) directed upstream from its radial position toward the airflow (234) flowing through the fuel-air mixing passage (214) downstream of the swozle assembly (220), in an ammonia injector system (260) and A burner (200) equipped with this feature.

2. The ammonia injector system (260) comprises a first ammonia supply line (280) for transporting the first ammonia flow (274) to the first plurality of ammonia injectors (272), a second plurality of ammonia injectors (276) configured to inject a second ammonia flow (278) into the air flow (234), and a second ammonia supply line (282) for transporting the second ammonia flow (278) to the second plurality of ammonia injectors (276), wherein each of the second plurality of ammonia injectors (276) has an injection axis (Ai) directed upstream toward the air flow (234) from the radial position, the burner (200) according to claim 1.

3. A controller (236) configured to selectively control the ammonia flow to one or both of the first plurality of ammonia injectors (272) and the second plurality of ammonia injectors (276) in accordance with the combustor load, further comprising a controller (236) configured to selectively control the flow to one or both of the first ammonia supply line (280) and the second ammonia supply line (282) in accordance with the combustor load, the burner (200) according to claim 2.

4. The burner (200) according to claim 2, wherein the second plurality of ammonia injectors (276) are located axially downstream from the first plurality of ammonia injectors (272).

5. The ammonia injector system (260) A first body (300) located axially downstream of the swozle assembly (220), the first body (300) having a first ring manifold (302) defined inside to be in fluid communication with the first ammonia supply line (280) and the first plurality of ammonia injectors (272), A second body (316) located axially downstream of the first body (300), the second body (316) having a second ring manifold (318) defined inside to be in fluid communication with the second ammonia supply line (282) and the second plurality of ammonia injectors (276) The burner (200) according to claim 4, comprising the above.

6. The burner (200) according to claim 2, wherein the ammonia injector system (260) comprises a single unit (300) having a first ring manifold (302) defined internally to be in fluid communication with the first ammonia supply line (280) and the first plurality of ammonia injectors (272), and a second ring manifold (304) adjacent to the first ring manifold (302) and defined internally to be in fluid communication with the second ammonia supply line (282) and the second plurality of ammonia injectors (276).

7. Each of the turning vanes (222) is provided with an internal fuel passage (232) that is in fluid communication with at least one fuel injector (224), the burner (200) further comprises a fuel supply unit (228) that introduces a fuel other than ammonia (230) into the internal fuel passage (232) for injection into the airflow (234), the fuel-air mixture produced by the swozle assembly (220) is led to the combustion reaction zone (146) in the combustion liner (144) of the combustor (118), the burner (200) according to claim 1.

8. The burner (200) according to claim 1, further comprising a central fuel supply line (320) defined within the central member (210), and a central fuel injector (322) located at the downstream end (324) of the central fuel supply line (320), the central fuel injector (322) configured to produce a fuel-air mixture for combustion in the combustion reaction zone (146) in the combustion liner (144) of the combustor (118) by mixing a fuel other than ammonia (230) with another airflow.

9. A combustor (118) for a gas turbine system (100), A combustor body (141) having a combustion liner (144), A head end assembly (143) having a cap assembly (150), A plurality of burners (200) arranged within the cap assembly (150) and directed toward the combustion liner (144), wherein at least one of the burners is defined according to any one of claims 1 to 8. A combustion device (118) is provided with this.

10. A method for operating a combustor (118) of a gas turbine system (100), A combustor (118) comprising a combustor body (141) equipped with a combustion liner (144), a cap assembly (150), and a head end assembly (143) equipped with a plurality of burners (200) disposed within the cap assembly (150) and directed toward the combustion liner (144), wherein at least one of the burners is defined according to any one of claims 1 to 8, Multiple ammonia injectors (272, 276) directed upstream inject ammonia into the airflow (234) in the fuel-air mixing passage (214) at one or more axial positions downstream of the swozle assembly (220) to generate an ammonia-air mixture (262), and Combustion of the ammonia-air mixture (262) formed by the plurality of burners (200) in the combustion reaction zone (146) of the combustion liner (144) Methods that include...

11. The method according to claim 10, wherein ammonia is injected into the airflow (234) in the fuel-air mixing passage (214) downstream of the swozle assembly (220) at two different axial positions.

12. The method according to claim 10, wherein injecting ammonia into the airflow (234) in the fuel-air mixing passage (214) downstream of the swozle assembly (220) includes injecting a first volume of ammonia at a first combustor load and a second larger volume of ammonia at a second larger combustor load.

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