Burner for combustor with ammonia injection downstream of swozzle assembly and related method

Abstract

A burner includes an outer member and a center member inside the outer member and defining a fuel-air mixing passage therebetween. A swozzle assembly, which is positioned in the fuel-air mixing passage, includes a plurality of turning vanes configured to impart a swirl to an air flow flowing through the mixing passage. An ammonia injector system is downstream of the swozzle assembly to form an ammonia-air mixture for combustion in a combustion reaction zone in a combustion liner of the combustor. The ammonia injector system includes a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow and, optionally, a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow. Each ammonia injector has an injection axis aimed upstream from a radial position toward the air flow flowing through the mixing passage downstream of the swozzle assembly.

Description

TECHNICAL FIELD

[0001] The disclosure relates generally to gas turbine system combustors and, more specifically, to a burner for a combustor having ammonia injection downstream of a swozzle assembly, a combustor including the burner, and a related method.BACKGROUND

[0002] Gas turbine systems include a combustion section including a plurality of combustors in which fuel is combusted to create a flow of combustion gas that is converted to kinetic energy in a downstream turbine section. Conventional combustors include a head end assembly including a plurality of burners for combusting fuel in a combustion zone. Typically, such combustors are fueled with hydrocarbon fuels (e.g., methane or diesel fuel), which contribute to various emissions that can have a detrimental environmental effect.

[0003] One of the issues with conventional combustors is that the combustion of these hydrocarbons commonly 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 sought to use alternate fuel sources, including hydrogen and / or ammonia, which remove carbon from the combustion products. However, current combustors present challenges relative to using ammonia as a fuel. In particular, ammonia suffers from low flammability and has a low heating value and may not stabilize very well causing at least part of the combustion reaction to extinguish.BRIEF DESCRIPTION

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

[0005] An aspect of the disclosure includes a burner for a combustor of a gas turbine system, the burner comprising: an outer member; a center member inside the outer member and defining a fuel-air mixing passage therebetween; a swozzle assembly positioned in the fuel-air mixing passage, the swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage; and an ammonia injector system downstream of the swozzle assembly, the ammonia injector system configured to form an ammonia-air mixture for combustion in a combustion reaction zone in a combustion liner of the combustor, the ammonia injector system including: a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow, wherein each of the first plurality of ammonia injectors has an injection axis aimed upstream from a radial position toward the air flow flowing through the fuel-air mixing passage downstream of the swozzle assembly.

[0006] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes a first ammonia supply line conveying the first ammonia flow to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow; and a second ammonia supply line conveying the second ammonia flow to the second plurality of ammonia injectors; wherein each of the second plurality of ammonia injectors has an injection axis aimed upstream from a radial position toward the air flow.

[0007] Another aspect of the disclosure includes any of the preceding aspects, and further comprising a controller configured to selectively control ammonia flow to one or both of the first plurality of ammonia injectors and the second plurality of ammonia injectors depending on a combustor load, wherein the controller is configured to selectively control flow to one or both of the first ammonia supply line and the second ammonia supply line depending on the combustor load.

[0008] Another aspect of the disclosure includes any of the preceding aspects, and the second plurality of ammonia injectors is axially downstream from the first plurality of ammonia injectors.

[0009] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes: a first body axially downstream of the swozzle assembly and having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors; and a second body axially downstream of the first body, the second body having a second ring manifold defined therein in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0010] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes a single body having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring manifold defined therein adjacent the first ring manifold and in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0011] Another aspect of the disclosure includes any of the preceding aspects, and each of the turning vanes includes an internal fuel flow passage in fluid communication with at least one fuel injector, and further comprising a fuel supply introducing a fuel other than ammonia into the internal fuel flow passage for injection into the air flow, wherein a fuel-air mixture generated by the swozzle assembly is directed into the combustion reaction zone in the combustion liner of the combustor.

[0012] Another aspect of the disclosure includes any of the preceding aspects, and further comprising a central fuel supply line defined within the center member, and a central fuel injector at a downstream end of the central fuel supply line, the central fuel injector configured to mix a fuel other than ammonia with another air flow to generate a fuel-air mixture for combusting in the combustion reaction zone in the combustion liner of the combustor.

[0013] Another aspect of the 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 positioned in the cap assembly and directed into the combustion liner, at least one burner of the plurality of burners including: an outer member; a center member inside the outer member and defining a fuel-air mixing passage therebetween; a swozzle assembly positioned in the fuel-air mixing passage, the swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage; and an ammonia injector system downstream of the swozzle assembly, the ammonia injector system configured to form an ammonia-air mixture for combustion in a combustion reaction zone in the combustion liner, the ammonia injector system including: a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow; and a controller configured to selectively control ammonia flow to the first plurality of ammonia injectors depending on a combustor load, wherein each of the first plurality of ammonia injectors has an injection axis aimed upstream from a radial position toward the air flow flowing through the fuel-air mixing passage downstream of the swozzle assembly.

[0014] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes a first ammonia supply line conveying the first ammonia flow to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow; and a second ammonia supply line conveying the second ammonia flow to the second plurality of ammonia injectors, wherein the controller is configured to selectively control flow to one or both of the first ammonia supply line and the second ammonia supply line depending on the combustor load.

[0015] Another aspect of the disclosure includes any of the preceding aspects, and the second plurality of ammonia injectors is axially downstream from the first plurality of ammonia injectors.

[0016] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes: a first body axially downstream of the swozzle assembly and having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors; and a second body axially downstream of the first body, the second body having a second ring manifold defined therein in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0017] Another aspect of the disclosure includes any of the preceding aspects, and the ammonia injector system includes a single body having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring manifold defined therein adjacent the first ring manifold and in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0018] Another aspect of the disclosure includes any of the preceding aspects, and each of the turning vanes includes an internal fuel flow passage in fluid communication with at least one fuel injector, and further comprising a fuel supply introducing a fuel other than ammonia into the internal fuel flow passage for injection into the air flow, wherein a fuel-air mixture generated by the swozzle assembly is directed into the combustion reaction zone in the combustion liner of the combustor.

[0019] Another aspect of the disclosure includes any of the preceding aspects, and further comprising a central fuel supply line defined within the center member, and a central fuel injector at a downstream end of the central fuel supply line, the central fuel injector configured to mix a fuel other than ammonia with another air flow to generate a fuel-air mixture for combusting in the combustion reaction zone in the combustion liner of the combustor.

[0020] Another aspect of the disclosure includes a method of operating a combustor of a gas turbine system, the method comprising: in a combustor including a combustor body including a combustion liner; and a head end assembly including: a cap assembly, and a plurality of burners positioned in the cap assembly and directed into the combustion liner, at least one burner of the plurality of burners including a fuel-air mixing passage having a swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage, performing the following: injecting ammonia with a plurality of ammonia injectors aimed upstream into the air flow in the fuel-air mixing passage at one or more axial locations downstream of the swozzle assembly to generate an ammonia-air mixture; and combusting the ammonia-air mixture formed by the plurality of burners in a combustion reaction zone in the combustion liner.

[0021] Another aspect of the disclosure includes any of the preceding aspects, and the injecting ammonia into the air flow in the fuel-air mixing passage downstream of the swozzle assembly occurs at two different axial locations.

[0022] Another aspect of the disclosure includes any of the preceding aspects, and the injecting ammonia into the air flow in the fuel-air mixing passage downstream of the swozzle 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 disclosure, including those described in this summary section, may be combined to form implementations not specifically described herein. That is, all embodiments described herein can be combined with each other.

[0024] The 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.BRIEF DESCRIPTION OF THE DRAWINGS

[0025] These and other features of this disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings that depict various embodiments of the disclosure, in which:

[0026] FIG. 1 shows a functional block diagram of an illustrative gas turbine system having a combustor capable of including a burner with an ammonia injector system, according to embodiments of the disclosure;

[0027] FIG. 2 shows a simplified cross-sectional side view of an illustrative combustor that may include a burner with an ammonia injector system, according to embodiments of the disclosure;

[0028] FIG. 3 shows an upstream view of a portion of the combustor shown in FIG. 2, according to embodiments of the disclosure;

[0029] FIG. 4 shows a cross-sectional side view of a burner including an ammonia injector system, according to embodiments of the disclosure;

[0030] FIG. 5 shows an enlarged view of an ammonia injector system, according to embodiments of the disclosure.

[0031] FIG. 6 shows a cross-sectional view of an ammonia injector, according to embodiments of the disclosure;

[0032] FIG. 7 shows a schematic view of an ammonia injection spray from a conventional fuel injector;

[0033] FIG. 8 shows a schematic view of an ammonia injection spray from an ammonia injector, according to embodiments of the disclosure;

[0034] FIG. 9 shows a cross-sectional perspective view of a single body with ring manifolds for ammonia injectors, according to embodiments of the disclosure; and

[0035] FIG. 10 shows a cross-sectional side view of a burner including an ammonia injector system including two bodies with ring manifolds for ammonia injectors, according to other embodiments of the disclosure.

[0036] It is noted that the drawings of the disclosure are not necessarily to scale. The drawings are intended to depict only typical aspects of the disclosure and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbering represents like elements between the drawings.DETAILED DESCRIPTION

[0037] As an initial matter, in order to clearly describe the current disclosure, it will become necessary to select certain terminology when referring to and describing relevant machine components within the illustrative application of a turbomachine combustor and a related ammonia injector system therefor. When doing this, if possible, common industry terminology will be used and employed in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of the present application and the scope of the appended claims. Those of ordinary skill in the art will appreciate that often a particular component may be referred to using several different or overlapping terms. What may be described herein as being a single part may include and be referenced in another context as consisting of multiple components. Alternatively, what may be described herein as including multiple components may be referred to elsewhere as a single part.

[0038] In addition, several descriptive terms may be used herein, and it should prove helpful to define these terms at the onset of this section. These terms and their definitions, unless stated otherwise, are as follows. As used herein, “downstream” and “upstream” are terms that indicate a direction relative to the flow of a fluid, such as the working fluid through a combustor of the turbomachine or, for example, the flow of air or ammonia through the combustor or heat exchanger, or coolant through one of the turbomachine's component systems. The term “downstream” corresponds to the direction of flow of the fluid, and the term “upstream” refers to the direction opposite to the flow. The terms “forward” and “aft,” without any further specificity, refer to directions, with “forward” referring to the front or compressor end of the turbomachine or combustor, and “aft” referring to the rearward or turbine end of the turbomachine or combustor.

[0039] The term “axial” refers to movement or position parallel to an axis, e.g., an axis of an ammonia injector, a burner, a combustor, or a turbomachine. The term “radial” refers to movement or position perpendicular to an axis, e.g., an axis of an ammonia injector, a burner, a combustor, or a turbomachine. In cases such as this, if a first component resides closer to the axis than a second component, it will be stated herein that the first component is “radially inward” or “inboard” of the second component. If, on the other hand, the first component resides further from the axis than the second component, it may be stated herein that the first component is “radially outward” or “outboard” of the second component. Finally, the term “circumferential” refers to movement or position around an axis, e.g., a circumferential interior surface of a combustor body or a circumferential interior of casing extending about a combustor. As indicated above, and depending on context, it will be appreciated that such terms may be applied in relation to the axis of the ammonia injector, the burner, the combustor, or the turbomachine.

[0040] In addition, several descriptive terms may be used regularly herein, as described below. The terms “first,”“second,” and “third,” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0041] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms “a,”“an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and / or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. “Optional” or “optionally” means that the subsequently described event may or may not occur or that the subsequently described feature may or may not be present and that the description includes instances where the event occurs, or the feature is present and instances where the event does not occur, or the feature is not present.

[0042] Where an element or layer is referred to as being “on,”“engaged to,”“connected to,”“coupled to,” or “mounted to” another element or layer, it may be directly on, engaged, connected, coupled, or mounted to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being “directly on,”“directly engaged to,”“directly connected to,” or “directly coupled to” another element or layer, there are no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., “between” versus “directly between,”“adjacent” versus “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items. The verb forms of “couple” and “mount” may be used interchangeably herein.

[0043] Embodiments of the disclosure provide a burner for a combustor of a gas turbine system, a combustor, and a related method. The burner includes an outer member and a center member inside the outer member and defining a fuel-air mixing passage therebetween. A swozzle assembly is positioned in the fuel-air mixing passage. The swozzle assembly includes a plurality of turning vanes configured to, among other things, impart a swirl to an air flow flowing through the fuel-air mixing passage. An ammonia injector system is downstream of the swozzle assembly and is configured to form an ammonia-air mixture for combustion in a combustion reaction zone defined within a combustion liner of the combustor. The ammonia injector system includes a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow and a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow. Each ammonia injector has an injection axis aimed upstream from a radial position toward the air flow flowing through the fuel-air mixing passage downstream of the swozzle assembly.

[0044] The ammonia injector system provides an efficient way of injecting liquid ammonia with the ammonia injectors inclined relative to, and oriented towards, the air flow path to prevent film formation on walls of the fuel-air mixing passage. The sets of ammonia injectors allow different amounts of ammonia injection based on different combustor loads to ensure fine ammonia droplet formation occurs. At lower combustor loads, one set of ammonia injectors will be used for injection of liquid ammonia and the other set of ammonia injectors may operate on purge (just air). Burners as described herein provide ammonia injection at different volumes based on different loads of the combustor, providing more precise and stable combustion. In addition, the angling (alternatively “inclining”) of ammonia injectors provides improved dispersion of the ammonia that is more efficient to avoid film formation on the fuel-air mixing passage and that does not destabilize the combustion reaction.

[0045] Referring now to the drawings, FIG. 1 provides a schematic diagram of an illustrative gas turbine system 100 (GT system 100). GT system 100 generally includes an inlet section 112, a compressor 114 disposed downstream of inlet section 112, a combustion system 116 including at least one combustor 118 disposed downstream of the compressor 114, a turbine 120 (i.e., an expansion turbine) disposed downstream of combustor 118, and an exhaust section 122 disposed downstream of turbine 120. Additionally, GT system 100 may include one or more shafts 124 that couple compressor 114 to turbine 120. During operation, air 126 flows through inlet section 112 and into compressor 114 where air 126 is progressively compressed, thus providing compressed air 128 to combustor 118. One or more fuels 130 from a fuel supply or supplies 132 is / are injected into combustor 118, mixed with a portion of compressed air 128 and burned to produce combustion gases 134. Combustion gases 134 flow from combustor 118 into turbine 120, wherein energy (kinetic and / or thermal) is transferred from combustion gases 134 to rotor blades (not shown), thus causing shaft 124 to rotate. The mechanical rotational energy may then be used for various purposes such as to power compressor 114 and / or to generate electricity. Combustion gases 134 exiting turbine 120 may then be exhausted from GT system 100 via exhaust section 122.

[0046] In one embodiment, GT system 100 may be applicable to a current engine model commercially available from GE Vernova of Cambridge, MA. The present disclosure is not limited to any one particular GT system and may be implemented in connection with other engines including, for example, any HA, F, B, LM, GT, TM and E-class engine models of GE Vernova, and engine models of other companies.

[0047] FIG. 2 provides a cross-sectioned schematic of an illustrative combustor 118 as may incorporate various embodiments of the present disclosure. As shown in FIG. 2, combustor 118 may be at least partially surrounded by an outer casing 136, such as a compressor discharge casing. Outer casing 136 may at least partially define a high-pressure plenum 138 that at least partially surrounds various components of combustor 118. High-pressure plenum 138 may be in fluid communication with compressor 114 (FIG. 1) to receive at least a portion of compressed air 128 therefrom. High-pressure plenum 138 may provide compressed air 128 to various parts of multiple-fuel burners 200, described herein.

[0048] An end cover 140 may be coupled to outer casing 136. End cover 140 may include any necessary passages or openings to deliver fuel such as natural gas, liquid fuel, ammonia, or compressed air 128 therethrough, as will be described herein. For example, end cover 140 may include any necessary passages or openings therein for fuel supply lines 280, 282 (FIGS. 4-5) and 320 (FIG. 10) to pass therethrough. End cover 140 may be configured to removably position multiple-fuel burners 200, 202 (hereafter “burner 200” or “center burner 202” unless otherwise necessary for differentiation) in head end assembly 143 of combustor 118, e.g., which includes a cap assembly 150 having openings in which the aft ends of burners 200 are positioned. In this manner, removal of burners 200 can be attained by removing part of end cover 140 and / or burner 200 from connection to head end assembly143, and slidingly removing burner(s) 200.

[0049] End cover 140 can be selectively coupled in head end assembly 143 in any now known or later developed manner, such as but not limited to threaded fasteners (not shown). Outer casing 136 and end cover 140 may at least partially define a head end volume or chamber 142 within a head end assembly 143 of combustor 118. In particular embodiments, head end volume 142 is in fluid communication with high-pressure plenum 138 and / or compressor 114. One or more liners or ducts form combustion liner 144 that may at least partially define a combustion reaction zone or chamber 146 for combusting one or more fuel-air mixtures and may at least partially define a hot gas path 148 through combustor 118 for directing combustion gases 134 towards an inlet to turbine 120.

[0050] FIG. 3 provides an upstream view of a portion of combustor 118 as shown in FIG. 2. In various embodiments, as shown in FIGS. 2 and 3 collectively, combustor 118 includes a plurality of burners or fuel nozzles (e.g., 200) whose upstream ends are coupled to end cover 140 and which extend toward combustion reaction zone 146. The downstream ends of burners 200 are aligned with respective openings (not shown) in cap assembly 150, such that burners 200 deliver a fuel / air mixture to combustion reaction zone 146 defined by combustion liner 144.

[0051] Various embodiments of combustor 118 may include different numbers and arrangements of burners 200, and the presently described embodiments are not limited to any particular number of burners, unless otherwise specified in the claims. For example, in particular configurations, such as the configuration shown in FIG. 3, the one or more burners includes a plurality of multiple-fuel burners 200 annularly arranged about a center burner 202. In other embodiments, burners 200 may be annularly arranged about a centerline of end cover 140 without the use of center burner 202. Center burner 202 may also be a pre-mix, multiple-fuel (liquid fuel and gas fuel) type burner. Other types of burners may be used instead of center burner 202, where desired. Center burner 202 may be the same as burner 200, as described herein. Each burner 200 may be a pre-mix, multiple-fuel type burner. More particularly, each burner 200 may be used to burn a gaseous fuel, such as natural gas, and / or ammonia, the latter of which is liquid. Each burner 200 is configured to inject and premix a gaseous fuel and / or a liquid fuel with a flow of a portion of compressed air 128 from head end volume 142 (FIG. 2) in head end assembly 143 upstream from combustion reaction zone 146.

[0052] FIG. 4 provides a cross-sectioned side view of an illustrative burner 200 (or 202) with pre-mix and multiple-fuel capabilities, according to at least one embodiment of the present disclosure. In particular embodiments, such as the embodiment shown in FIG. 4, burner 200 includes a center member 210 and an outer member 212, each member having an annular or tube shape. More particularly, burner 200 may include outer member or burner tube 212 that extends circumferentially and concentrically around at least a portion of center member 210. As illustrated, center member 210 is inside outer member 212, and a fuel-air mixing passage 214 is defined therebetween. Burner 200 also includes a swozzle assembly 220 positioned in fuel-air mixing passage 214. Swozzle assembly 220 includes a plurality of turning vanes 222 configured to impart a swirl to an air flow 234 flowing through gaps between circumferentially adjacent turning vanes 222 and into fuel-air mixing passage 214. More particularly, plurality of turning vanes 222 extend between center member 210 and outer member 212. Turning vanes 222 are disposed within fuel-air mixing passage 214, which may be annular, and as noted may be defined radially between center member 210 and outer member 212.

[0053] Swozzle assembly 220 may be used to generate, as will be described herein, just a swirling air flow 234 for mixing with ammonia from an ammonia injector system 260, and / or it can be used to generate a fuel-air mixture. With regard to the latter function, one or more of the turning vanes 222 may include one or more fuel injectors 224 that is / are in fluid communication with a fuel plenum 226 defined within center member 210 or other gas fuel source. Fuel plenum 226 is fluidly coupled to a fuel supply 228 (FIG. 4) to receive, for example, a gas fuel 230 therefrom. More particularly, each turning vane 222 may include an internal fuel flow passage 232 in fluid communication with at least one fuel injector 224. Fuel supply 228 introduces a fuel 230, other than ammonia, (via fuel plenum 226) into internal fuel flow passage 232 for injection into air flow 234. A fuel-air mixture is thus generated by swozzle assembly 220 that is directed into combustion reaction zone 146 in combustion liner 144 of combustor 118. In one example, fuel 230 may be natural gas, which is mixed with air flow 234 to create a fuel-air mixture for combustion in combustion reaction zone 146. In certain cases, fuel 230 to swozzle assembly 220 may be turned off, e.g., using a control valve 235 controlled by a controller 236 (e.g., of combustor 118 or another system), such that only (swirling) air flow 234 exits swozzle assembly 220. Controller 236 will be further described herein. This arrangement may be used for, for example, where ammonia is being used as a fuel for combustion rather than natural gas, as will be described herein.

[0054] As shown in FIG. 4, center 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 center member 210 and burner 200. Axial centerline 242 of center burner 202 is also coincident with an axial centerline of cap assembly 150. Burner 200 may be connected to an inner surface of end cover 140 via mechanical fasteners or by other connecting means (not shown). In particular embodiments, and as shown in FIG. 4, an upstream end portion 244 of outer member 212 may at least partially define an inlet 246 to fuel-air mixing passage 214 and a downstream end portion 248 of outer member 212 may at least partially define an outlet 250 of fuel-air mixing passage 214, i.e., to combustion reaction zone 146. In at least one embodiment, inlet 246 is in fluid communication with head end volume 142 (FIG. 2) in head end assembly 143 of combustor 118 to receive compressed air 128 therein.

[0055] FIG. 5 provides an enlarged view of an ammonia injector system 260 of burner 200 as shown in FIG. 4. In various embodiments, examples of which are shown in FIGS. 4 and 5 collectively, burner 200 includes ammonia injector system 260 downstream of swozzle assembly 220. Ammonia injector system 260 is configured to form an ammonia-air mixture 262 for combustion in combustion reaction zone 146 in combustion liner 144 of combustor 118. In certain cases, ammonia-air mixture 262 may be mixed with a mixture of fuel 230 (FIG. 4) and air flow 234 (i.e., a natural gas and air, fuel-air mixture) from swozzle assembly 220, but this is not necessary in all cases.

[0056] Ammonia injector system 260 includes a first plurality or set of ammonia injectors 272 configured to inject a first ammonia flow 274 into air flow 234 (from swozzle assembly 220), and a second plurality or set of ammonia injectors 276 configured to inject a second ammonia flow 278 into air flow 234. FIGS. 6-8 show various views of ammonia injectors 272, 276, according to embodiments of the disclosure, and will be described further herein. Continuing with FIGS. 4 and 5, ammonia injector system 260 includes a first ammonia supply line 280 conveying first ammonia flow 274 to first plurality of ammonia injectors 272 and a second ammonia supply line 282 conveying second ammonia flow 278 to second plurality of ammonia injectors 276. Ammonia supply lines 280, 282 may include any appropriate conduit or tube appropriate for conveying ammonia and capable of withstanding the high temperature environment of burner 200.

[0057] Ammonia injector system 260 may also include a controller 236 configured to selectively control flow of ammonia to one or both of first set of ammonia injectors 272 and second set of ammonia injectors 276 depending on a combustor load. Controller 236 may be part of any now known or later developed combustor control or GT system 100 (FIG. 1) control system and may include any hardware and / or software configured to carry out the functions described herein. For example, controller 236 is configured to selectively control flow to one or both of first ammonia supply line 280 and second ammonia supply line 282, e.g., by controlling valve(s) 283, from an ammonia supply 285 and thus the respective sets of ammonia injectors 272, 276 fluidly coupled thereto. Whether to use one or both sets of ammonia injectors 272, 276 depends on a combustor load. As used herein, “combustor load” is an amount of combustion required to be generated by combustor 118 based on needs of turbine 120 (FIG. 1) or other operational parameters such as, but not limited to, air flow 234, environmental conditions, and flow rate and can be calculated in any desired manner based on data provided to controller 236.

[0058] Returning to FIG. 4, pluralities of ammonia injectors 272, 276 can be provided in different ways according to embodiments of the disclosure. In FIG. 4, ammonia injector system 260 includes a single body or manifold body 300 having a first ring manifold 302 defined therein in fluid communication with first ammonia supply line 280 and first plurality of ammonia injectors 272. First body 300 also includes a second ring manifold 304 defined therein adjacent first ring manifold 302 and in fluid communication with second ammonia supply line 282 and second plurality of ammonia injectors 276. Note, as used herein, while referred to as “ring manifolds,” it will be recognized that manifolds 302, 304 may extend any necessary circumferential extent in order to provide a fuel plenum to any desired ammonia injectors 272, 276, and may not extend in a complete circle within a respective body 300 (310, 316 (FIG. 10)) in which defined. Body 300 may be coupled to or integrated with center member 210 in any known manner.

[0059] FIG. 9 shows a cross-sectional view of single body 300 for ammonia injector system 260 according to certain embodiments. First plurality of ammonia injectors 272 and second plurality of ammonia injectors 276 may be circumferentially spaced about single body 300 in any manner but may be approximately equidistantly spaced within a given plurality to more evenly distribute ammonia. Each plurality of ammonia injectors 272, 276 may also be circumferentially uniformly spaced relative to each other, e.g., with every other ammonia injector belonging to one of the pluralities of ammonia injectors. Ring manifolds 302, 304 are adjacent to one another, meaning they are spaced so as to not interfere with one another. In some embodiments, ring manifolds 302, 304 may be axially spaced from one another within single body 300, i.e., relative to burner 200 centerline 242. For instance, second ring manifold 304 may be axially downstream from first ring manifold 302 in single body 300. In contrast, in FIGS. 4 and 9, ring manifolds 302, 304 are radially spaced from one another with a divider wall 306 therebetween. Passages 308 fluidly couple (inner) ring manifold 302 with first plurality of ammonia injectors 272, e.g., one passage for each ammonia injector 272. Ring manifold 304 is just radially inward of ammonia injectors 276 (or the openings they seat in), so no (or very short) passages in single body 300 may be necessary for ring manifold 304 to fluidly couple with ammonia injectors 276.

[0060] In any event, as shown in FIGS. 4 and 9, first ammonia supply line 280 and first plurality of ammonia injectors 272 are fluidly coupled by first ring manifold 302 (and passages 308) defined in single body 300, and second ammonia supply line 282 and second plurality of ammonia injectors 276 are fluidly coupled by second ring manifold 304 defined in single body 300. Controller 236 can thus control which ammonia injectors 272, 276 inject ammonia by controlling valve(s) 283 that control ammonia flow to each ammonia supply line 280, 282. Controller 236 can direct ammonia to first plurality of ammonia injectors 272 and / or second plurality of ammonia injectors 276. Controller 236 may also control an open / close level of valve(s) 283 to control a volume of ammonia delivered to each plurality of ammonia injectors 272, 276. In this manner, a volume of ammonia injected into fuel-air mixing passage 214 can be controlled based on combustor load.

[0061] Referring to FIG. 10, in another embodiment, second plurality of ammonia injectors 276 may be axially downstream from first plurality of ammonia injectors 272 in a separate second body 316. Here, ammonia injector system 260 includes a first body 310 axially downstream of swozzle assembly 220. First body 310 has a first ring manifold 314 defined therein in fluid communication with first ammonia supply line 280 and first plurality of ammonia injectors 272. In addition, ammonia injector system 260 includes second body 316 axially downstream of first body 310. Second body 316 has a second ring manifold 318 defined therein in fluid communication with second ammonia supply line 282 and second plurality of ammonia injectors 276. First plurality of ammonia injectors 272 and second plurality of ammonia injectors 276 may be circumferentially spaced about each respective body 310, 316 in any manner but are typically equidistantly spaced within a given plurality to ensure even distribution of ammonia. Ammonia injectors in each of plurality of ammonia injectors 272, 276 may also be circumferentially offset relative to each other in respective bodies 310, 316 such that ammonia injectors 272 do not inject ammonia along the same axial line as any of downstream ammonia injectors 276. However, any circumferential arrangement is possible to achieve the desired ammonia-air mixture 262. Further, first body 310 and second body 316 may be axially spaced in any manner, e.g., immediately adjacent one another (in contact), or any desired distanced axial spacing, i.e., within center member 210, to set the different pluralities of ammonia injectors 272, 276 at different axial locations. Any axial spacing arrangement is possible to achieve the desired ammonia-air mixture 262.

[0062] As shown in FIG. 10, first ammonia supply line 280 and first plurality of ammonia injectors 272 are fluidly coupled by first ring manifold 314 defined in first body 310, and second ammonia supply line 282 and second plurality of ammonia injectors 276 are fluidly coupled by second ring manifold 318 defined in second body 316. Controller 236 can control which ammonia injectors 272, 276 inject ammonia by controlling valve(s) 283 that control ammonia flow to each ammonia supply line 280, 282. As noted, controller 236 can direct ammonia to first plurality of ammonia injectors 272 and / or second plurality of ammonia injectors 276. Controller 236 may also control an open / close level of valve(s) 283 to control a volume of ammonia delivered to each plurality of ammonia injectors 272, 276. In this manner, a volume of ammonia injected into fuel-air mixing passage 214 is controllable based on combustor load.

[0063] With further reference to FIGS. 5 and 10, burner 200 may also optionally include a central fuel supply line 320 defined within center member 210, and a central fuel injector 322 at a downstream end 324 of central fuel supply line 320. Note, the FIG. 4 version omits the central fuel passage and injector, but it could also include them. As illustrated, central fuel supply line 320 and central fuel injector 322 may be positioned within center member 210. Central fuel injector 322 is configured to mix a fuel 328, other than ammonia, with another air flow 128 (from, e.g., passages in center member 210 from fuel-air mixing passage 214 or swozzle assembly 220) to generate a fuel-air mixture 330 for combusting in combustion reaction zone 146 in combustion liner 144 of combustor 118. Fuel 328 may be, for example, a liquid fuel such as fuel oil. Central fuel injector 322 is axially oriented with respect to axial centerline 242 and is in fluid communication with fuel supply 332 via central fuel supply line 320. In operation, central fuel injector 322 injects atomized liquid fuel 328 into combustion zone 146 at a location that is downstream from swozzle assembly 220 and downstream from the plurality of ammonia injectors 272, 276. In particular embodiments, central fuel injector 322 may be screwed into, threaded into, or otherwise removably attached within center member 210 to facilitate maintenance (e.g., cleaning) and / or replacement, as needed.

[0064] In various embodiments, as shown in FIGS. 5 and 10, a portion of central fuel supply line 320 that is disposed within center member 210 and downstream of body 300 (FIG. 5) or bodies 310, 316 (FIG. 10) may extend helically about axial centerline 242 of burner 200. In operation, the helical portion of central fuel supply line 320 acts as a spring to allow the fuel passage to grow and contract due to thermal differences between various parts of burner 200. Central fuel supply line 320 may be fluidly coupled to a fuel supply 332 (FIG. 10) to receive, for example, liquid fuel 328 therefrom. Controller 236 may control any number of valves 334 to control liquid fuel 328 flow. Central fuel supply line 320 may be routed in any manner with ammonia supply lines 280, 282. For example, single body 300 (FIGS. 4-5) or first and second bodies 310, 316 (FIG. 10) may each include a central opening 338 to allow passage of central fuel supply line 320. Central opening 338 also allow compressed air 128 to pass therethrough for creating fuel-air mixture 330. Central fuel injector 322 may include any now known or later developed fuel injector structure for the fuel used.

[0065] With further regard to supplying ammonia to ammonia injector system 260, as shown in FIGS. 4 and 10, manifolds 302, 304, 314, 318 are fluidly coupled to an ammonia supply 228 via fuel supply lines 280, 282. At least a portion of ammonia supply lines 280, 282 may extend at least partially helically within center member 210 about or around central fuel supply line 320 (where provided) and about or around each other forward of the most upstream single body 300 (FIG. 4) or first body 310 (FIG. 10). Ammonia supply lines 280, 282 are also disposed radially inwardly from gas fuel plenum 226. In FIGS. 4 and 5, an aft end of first ammonia supply line 280 is fluidly coupled to single body 300 and ring manifold 302 therein, and in FIG. 10, an aft end of second ammonia supply line 280 is fluidly coupled to first body 310 and ring manifold 314 therein. In FIGS. 4 and 5, an aft end of second ammonia supply line 282 is fluidly coupled to single body 300 and ring manifold 302 therein, and in FIG. 10, an aft end of second ammonia supply line 282 is fluidly coupled to second body 316 and ring manifold 318 therein. In FIG. 10, second ammonia supply line 282 extends through first body 310 in a manner not interfering with ring manifold 314 or ammonia injectors 272 in first body 310. Any extent of second ammonia supply line 282 required to reach second body 316 may be used between first body 310 and second body 316.

[0066] Body 300 or bodies 310, 316 are attached to center member 210 in any desired manner. Central opening 338 in single body 300 (FIGS. 4-5) or first and second bodies 310, 316 (FIG. 10) is detached from central fuel supply line 320 and allows compressed air 128 to pass therethrough. Thus, in particular embodiments, central fuel supply line 320 passing through central opening 338 is unrestrained in its thermal growth or movement.

[0067] First ammonia supply line 280 and / or second ammonia supply line 282 may include portion(s) that are helical or coiled to act like a spring. In the illustrated embodiment, lines 280, 282 are coiled in the same direction (e.g., clockwise or counter-clockwise). The coiling of ammonia supply lines 280, 282 accommodates thermal differences between the various parts of burner 200, and transfers heat to the ammonia flow therein. First and second supply lines 280, 282 do not intersect, but rather are radially outward of, axial centerline 242 of burner 200.

[0068] Referring to FIG. 6, details of ammonia injectors 272, 276 will now be described. As noted, FIG. 6 shows a cross-sectional view of an ammonia injector 272, 276, according to embodiments of the disclosure. Ammonia injectors 272, 276 may be circumferentially spaced about / within a respective body 300 (FIGS. 4-5) or bodies 310, 316 (FIG. 10), and each is in fluid communication with a respective ring manifold 302, 304 (FIG. 4-5) or 314, 318 (FIG. 10). In order to prevent film formation of ammonia (NH3) on the walls of fuel-air mixing passage 214, each of first plurality of ammonia injectors 272 and each of second plurality of ammonia injectors 276 have an injection axis Ai aimed upstream from a radial position R (with respect to centerline 242 of burner 200) toward air flow 234 flowing through fuel-air mixing passage 214 downstream of swozzle assembly 220. Injection axis Ai may be offset by an angle α relative to radial position R. Angle α may be in a range of, for example, 15° to 65°, from radius R. Angle α may be chosen based on, for example, characteristics of air flow 234 and / or the liquid ammonia and the desired atomization of the ammonia. Hence, each ammonia injector 272, 276 is non-radially oriented with respect to axial centerline 242 to inject an atomized jet of ammonia 274, 278 into fuel-air mixing passage 214 at a location that is downstream from swozzle assembly 220, turning vanes 222 and / or gas fuel injectors 224. Although first plurality of ammonia injectors 272 and second plurality of ammonia injectors 276 are illustrated as having injection axes Ai at the same angle α, it should be understood that first plurality of ammonia injectors 272 may have an injection axis Ai at a first angle that is different from a second angle of the injection axis Ai of the second plurality of ammonia injectors 276. Each angle may be in the range of 15° to 65° from radius R.

[0069] Ammonia injectors 272, 276 may be screwed into, threaded into, or otherwise removably attached within a corresponding opening 340 of single body 300 (FIGS. 4-5) or bodies 310, 316 (FIG. 10) to facilitate maintenance (e.g., cleaning) and / or replacement, as needed. Openings 340 are also shown in FIG. 9. Fuel injectors 272, 276 and / or openings 340 may be structured and / or arranged to create the desired injection axis Ai, e.g., with an angled nozzle passage in the injector body or a straight passage in the injector body positioned within an angled opening 340. Fuel injectors 272, 276 may otherwise take the form of any nozzle or atomizer capable of converting liquid ammonia into a mist of very fine droplets.

[0070] FIG. 7 shows a schematic representation of conventional ammonia injection with a radially extending (R) injection axis perpendicular to air flow 234, and FIG. 8 shows a schematic representation of ammonia injection with an injection axis Ai directed at angle α relative to a radial position R according to embodiments of the disclosure. In FIG. 7, the leeward side or downstream side of ammonia spray 344 is shielded by the windward or upstream side of ammonia spray 346, which creates a dense region 348 that impedes atomization of ammonia and can lead to film 350 formation on walls of fuel-air mixing passage 214. Film 350 prevents efficient combustion of ammonia-air mixture in combustion reaction zone 146. In contrast, in FIG. 8, the leeward or downstream side 352 of ammonia spray 274, 278 and the windward or upstream side 354 of ammonia spray 274, 278 are directed into air flow 234 in a more even manner, which allows ammonia to be better atomized in ammonia-air mixture 262 and results in little or no film 350 (FIG. 7) and more efficient combustion of ammonia-air mixture 262 in combustion reaction zone 146.

[0071] In certain embodiments, as shown in FIGS. 4, 5 and 10, burner 200 may include an air shield or deflector 342 that extends circumferentially around central fuel supply line 320 and ammonia supply lines 280, 282. As shown in FIGS. 4, 5 and 10, air shield 342 is positioned upstream from a forward side wall of body 300 (FIGS. 4-5) or body 310 (FIG. 10).

[0072] A method of operating combustor 118 of GT system 100 according to embodiments of the disclosure will now be described. In operation, embodiments of the method include combusting ammonia-air mixture 262 formed by burner 200 in combustion reaction zone 146 in combustion liner 144. As noted, combustor 118 includes a combustor body 141 including combustion liner 144, and head end assembly 143 including cap assembly 150. Combustor 118 also includes plurality of burners 200 positioned in cap assembly 150 and directed into combustion liner 144. Each burner 200 includes fuel-air mixing passage 214 having swozzle assembly 220 including a plurality of turning vanes 222 configured to impart a swirl to air flow 234 flowing through fuel-air mixing passage 214. The method includes injecting ammonia with plurality of ammonia injectors 272, 276 aimed upstream into air flow 234 in fuel-air mixing passage 214 at one or more axial locations downstream of swozzle assembly 220 to generate an ammonia-air mixture 262. During ammonia injection using ammonia injector system 260, gas fuel 230 injection using swozzle assembly 220 may be stopped, resulting in swozzle assembly 220 only providing air flow 234 to create ammonia-air mixture 262. FIGS. 4-5 show ammonia injectors 272, 276 at one axial location. As shown in FIG. 10, the injecting ammonia into air flow 234 in fuel-air mixing passage 214 downstream of swozzle assembly 220 may occur at two different axial locations, i.e., using first and second bodies 310, 316 with ammonia injectors 272, 276 at more than one axial location. The method also includes combusting ammonia-air mixture 262 formed by plurality of burners 200 in combustion reaction zone 146 in combustion liner 144. With reference to FIGS. 4 and 10, in certain embodiments, the method may also include injecting ammonia into air flow 234 in fuel-air mixing passage 214 downstream of swozzle assembly 220 in different volumes depending on combustor load. For example, the ammonia injecting 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. Controller(s) 236 may control fuel flow of any fuel, including ammonia, using valve(s) 235, 283 and / or 334. In certain embodiments, ammonia may be injected in a ratio of air from 1.1-1.5. In some embodiments, as shown in FIGS. 5 and 10, the method may further include injecting a liquid fuel from a central fuel injector 322 that is positioned downstream of ammonia injector system 260, such that a liquid fuel-air mixture is introduced into combustion reaction zone 146 in combustion liner 144.

[0073] Burner 200 and parts thereof may be made of any now known or later developed combustion tolerant and oxidation resistant materials. The material may be metal and can be a pure metal or an alloy. Burner 200 may include a metal that is typically used in turbine components such as turbine blades or nozzles and that has a higher temperature and higher oxidation tolerance than materials typically used for combustion hardware. In this case, the material may include a non-reactive metal, e.g., made from a non-explosive or non-conductive powder, such as but not limited to: a cobalt chromium molybdenum (CoCrMo) alloy, stainless steel, an austenite nickel-chromium based alloy such as a nickel-chromium-molybdenum-niobium alloy (NiCrMoNb) (e.g., Inconel 625 or Inconel 718), a nickel-chromium-iron-molybdenum alloy (NiCrFeMo) (e.g., Hastelloy® X available from Haynes International, Inc.), a nickel-chromium-cobalt-molybdenum alloy (NiCrCoMo) (e.g., Haynes 232 or Haynes 282 available from Haynes International, Inc.), or a nickel-chromium-cobalt-titanium alloy (NiCrCoTi) (e.g., GTD 262 developed by General Electric Company). Other possibilities include, for example, René 108, CM 247, Mar M 247, and any precipitation harden-able (PH) nickel alloy.

[0074] In certain embodiments, burner 200 may be additively manufactured using any now known or later developed technique capable of forming an integral body. Consequently, the different parts may include a plurality of parallel, sintered metal layers. Other forms of manufacture are also possible.

[0075] As shown in FIG. 2, embodiments of the disclosure may also include combustor 118 for GT system 100. Combustor 118 includes combustor body 141 including combustion liner 144. Combustor 118 also includes head end assembly 143 including burners 200, as described herein, possibly with center burner 202, directed into combustion liner 144. Burners 200 may be as described herein and are directed into combustion liner 144. Combustor 118 generally terminates at a point that is adjacent to turbine 120. A first stage of stationary nozzles at least partially defines a turbine inlet to turbine 120. Combustor body 141, i.e., combustion liner 144, at least partially defines a hot gas path (HGP) for routing combustion gases 134 from combustion reaction zone 146 to turbine 120 during operation of GT system 100.

[0076] Embodiments of disclosure may also include, as shown in FIG. 1, GT system 100 including inlet section 112, compressor 114 disposed downstream of inlet section 112, combustion system 116 including at least one combustor 118 disposed downstream of compressor 114, and a turbine 120 disposed downstream of combustor 118. Combustor(s) 118 are operatively coupled to compressor 114, and turbine 120 is operatively coupled to combustor(s) 118. As described herein, combustors 118 include combustor body 141 including combustion liner 144, and head end fuel nozzle assembly 143 at a forward end of combustor body 141. Combustor(s) 118 may also include burners 200 as described herein. Head end assembly 143 includes a plurality of burners 200 directed into combustion liner 144, as described herein.

[0077] The disclosure provides various technical and commercial advantages, examples of which are discussed herein. Burners as described herein provide ammonia injection at different volumes based on different loads of the combustor, providing more precise and stable combustion. In addition, the angling of ammonia injectors provides improved dispersion of the ammonia that is more efficient to avoid film formation on the fuel-air mixing passage and that does not destabilize the combustion reaction.

[0078] Approximating language, as used herein throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about,”“approximately” and “substantially,” are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be combined and / or interchanged; such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. “Approximately” or “about,” as applied to a particular value of a range, applies to both end values and, unless otherwise dependent on the precision of the instrument measuring the value, may indicate + / −10% of the stated value(s).

[0079] The corresponding structures, materials, acts, and equivalents of all means or step plus function elements in the claims below are intended to include any structure, material, or act for performing the function in combination with other claimed elements as specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description but is not intended to be exhaustive or limited to the disclosure in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the disclosure. The embodiments were chosen and described in order to best explain the principles of the disclosure and the practical application of the technology and to enable others of ordinary skill in the art to understand the disclosure for contemplating various modifications to the present embodiments, which may be suited to the particular use contemplated.

Claims

1. A burner for a combustor of a gas turbine system, the burner comprising:an outer member;a center member inside the outer member and defining a fuel-air mixing passage therebetween;a swozzle assembly positioned in the fuel-air mixing passage, the swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage; andan ammonia injector system downstream of the swozzle assembly, the ammonia injector system configured to form an ammonia-air mixture for combustion in a combustion reaction zone in a combustion liner of the combustor, the ammonia injector system including:a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow,wherein each of the first plurality of ammonia injectors has an injection axis aimed upstream from a radial position toward the air flow flowing through the fuel-air mixing passage downstream of the swozzle assembly.

2. The burner of claim 1, wherein the ammonia injector system includes a first ammonia supply line conveying the first ammonia flow to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow; and a second ammonia supply line conveying the second ammonia flow to the second plurality of ammonia injectors; wherein each of the second plurality of injectors has an injection axis aimed upstream from the radial position toward the air flow.

3. The burner of claim 2, further comprising a controller configured to selectively control ammonia flow to one or both of the first plurality of ammonia injectors and the second plurality of ammonia injectors depending on a combustor load, wherein the controller is configured to selectively control flow to one or both of the first ammonia supply line and the second ammonia supply line depending on the combustor load.

4. The burner of claim 2, wherein the second plurality of ammonia injectors is axially downstream from the first plurality of ammonia injectors.

5. The burner of claim 4, wherein the ammonia injector system includes:a first body axially downstream of the swozzle assembly and having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors; anda second body axially downstream of the first body, the second body having a second ring manifold defined therein in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

6. The burner of claim 2, wherein the ammonia injector system includes a single body having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring manifold defined therein adjacent the first ring manifold and in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

7. The burner of claim 1, wherein each of the turning vanes includes an internal fuel flow passage in fluid communication with at least one fuel injector, and further comprising a fuel supply introducing a fuel other than ammonia into the internal fuel flow passage for injection into the air flow, wherein a fuel-air mixture generated by the swozzle assembly is directed into the combustion reaction zone in the combustion liner of the combustor.

8. The burner of claim 1, further comprising a central fuel supply line defined within the center member, and a central fuel injector at a downstream end of the central fuel supply line, the central fuel injector configured to mix a fuel other than ammonia with another air flow to generate a fuel-air mixture for combusting in the combustion reaction zone in the combustion liner of the combustor.

9. 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; anda plurality of burners positioned in the cap assembly and directed into the combustion liner, at least one burner of the plurality of burners including:an outer member;a center member inside the outer member and defining a fuel-air mixing passage therebetween;a swozzle assembly positioned in the fuel-air mixing passage, the swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage; andan ammonia injector system downstream of the swozzle assembly, the ammonia injector system configured to form an ammonia-air mixture for combustion in a combustion reaction zone in the combustion liner, the ammonia injector system including:a first plurality of ammonia injectors configured to inject a first ammonia flow into the air flow; anda controller configured to selectively control ammonia flow to the first plurality of ammonia injectors depending on a combustor load,wherein each of the first plurality of ammonia injectors has an injection axis aimed upstream from a radial position toward the air flow flowing through the fuel-air mixing passage downstream of the swozzle assembly.

10. The combustor of claim 9, wherein the ammonia injector system includes a first ammonia supply line conveying the first ammonia flow to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia flow into the air flow; and a second ammonia supply line conveying the second ammonia flow to the second plurality of ammonia injectors, wherein the controller is configured to selectively control flow to one or both of the first ammonia supply line and the second ammonia supply line depending on the combustor load.

11. The combustor of claim 10, wherein the second plurality of ammonia injectors is axially downstream from the first plurality of ammonia injectors.

12. The combustor of claim 11, wherein the ammonia injector system includes:a first body axially downstream of the swozzle assembly and having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors; anda second body axially downstream of the first body, the second body having a second ring manifold defined therein in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

13. The combustor of claim 10, wherein the ammonia injector system includes a single body having a first ring manifold defined therein in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring manifold defined therein adjacent the first ring manifold and in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

14. The combustor of claim 9, wherein each of the turning vanes includes an internal fuel flow passage in fluid communication with at least one fuel injector, and further comprising a fuel supply introducing a fuel other than ammonia into the internal fuel flow passage for injection into the air flow, wherein a fuel-air mixture generated by the swozzle assembly is directed into the combustion reaction zone in the combustion liner of the combustor.

15. The combustor of claim 9, further comprising a central fuel supply line defined within the center member, and a central fuel injector at a downstream end of the central fuel supply line, the central fuel injector configured to mix a fuel other than ammonia with another air flow to generate a fuel-air mixture for combusting in the combustion reaction zone in the combustion liner of the combustor.

16. A method of operating a combustor of a gas turbine system, the method comprising:in a combustor including a combustor body including a combustion liner; and a head end assembly including: a cap assembly, and a plurality of burners positioned in the cap assembly and directed into the combustion liner, at least one burner of the plurality of burners including a fuel-air mixing passage having a swozzle assembly including a plurality of turning vanes configured to impart a swirl to an air flow flowing through the fuel-air mixing passage, performing the following:injecting ammonia with a plurality of ammonia injectors aimed upstream into the air flow in the fuel-air mixing passage at one or more axial locations downstream of the swozzle assembly to generate an ammonia-air mixture; andcombusting the ammonia-air mixture formed by the plurality of burners in a combustion reaction zone in the combustion liner.

17. The method of claim 16, wherein the injecting ammonia into the air flow in the fuel-air mixing passage downstream of the swozzle assembly occurs at two different axial locations.

18. The method of claim 16, wherein the injecting ammonia into the air flow in the fuel-air mixing passage downstream of the swozzle 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.

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