BURNER FOR COMBUSTION CHAMBER WITH AMMONIA INJECTION DOWNFLOW OF A VULNERARY ARRAY AND ASSOCIATED METHOD

Abstract

A burner (200) includes an outer element (212) and a central element (210) within the outer element (212), defining a fuel-air mixing channel (214) between them. A vortex arrangement (220) located in the fuel-air mixing channel (214) includes a plurality of deflecting vanes (222) configured to swirl an airflow (234) passing through the mixing channel (214). An ammonia injector system (260) is located downstream of the vortex arrangement (220) to form an ammonia-air mixture for combustion in a combustion reaction zone (146) in a combustion tube (144) of the combustion chamber (118).The ammonia injector system (260) includes a first plurality of ammonia injectors (272) configured to inject a first ammonia stream (274) into the air stream (234), and optionally a second plurality of ammonia injectors (276) configured to inject a second ammonia stream (278) into the air stream (234). Each ammonia injector (276) has an injection axis (Ai) directed upstream from a radial position in the direction of the air stream (234) flowing through the mixing channel (214) downstream of the vortex arrangement (220).

Description

TECHNICAL AREA

[0001] The disclosure relates generally to combustion chambers of gas turbine systems and in particular to a burner for a combustion chamber with ammonia injection downstream of a vortex arrangement, a combustion chamber including the burner and an associated method. STATE OF THE ART

[0002] Gas turbine systems include a combustion section, which comprises a multitude of combustion chambers where fuel is burned to produce a combustion gas stream that is converted into kinetic energy in a downstream turbine section. Conventional combustion chambers include a head assembly with multiple burners for burning fuel in a combustion zone. These combustion chambers are typically fueled with hydrocarbon fuels (e.g., methane or diesel fuel), which contribute to various emissions that can adversely affect the environment.

[0003] One of the problems with conventional combustion chambers is that the combustion of these hydrocarbons generally leads to the formation of carbon dioxide (CO2) and nitrogen oxides (NOx), the control of which is costly. To reduce the amount of CO2, some manufacturers have tried using alternative fuel sources such as hydrogen and / or ammonia, which remove carbon from the combustion products. However, current combustion chambers present a challenge with regard to the use of ammonia as a fuel. In particular, ammonia is difficult to ignite, has a low calorific value, and may not stabilize well, resulting in at least part of the combustion reaction being inactivated. SHORT DESCRIPTION

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

[0005] One aspect of the disclosure includes a burner for a combustion chamber of a gas turbine system, the burner comprising: an outer element; a central element within the outer element defining a fuel-air mixing channel between them; a vortex arrangement positioned in the fuel-air mixing channel, the vortex arrangement comprising a plurality of deflecting vanes configured to swirl an airflow passing through the fuel-air mixing channel;and an ammonia injector system downstream of the vortex arrangement, wherein the ammonia injector system is configured to form an ammonia-air mixture for combustion in a combustion reaction zone in a combustion tube of the combustion chamber, the ammonia injector system comprising: a first plurality of ammonia injectors configured to inject a first stream of ammonia into the air stream, each of the first plurality of ammonia injectors having an injection axis directed upstream from a radial position in the direction of the air stream flowing through the fuel-air mixing channel downstream of the vortex arrangement.

[0006] Another aspect of the disclosure includes any one of the foregoing aspects, and the ammonia injector system includes a first ammonia supply line that directs the first ammonia stream to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia stream into the air stream; and a second ammonia supply line that directs the second ammonia stream to the second plurality of ammonia injectors; wherein each of the second plurality of ammonia injectors has an injection axis directed upstream from a radial position in the direction of the air stream.

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

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

[0009] Another aspect of the disclosure includes any of the foregoing aspects, and the ammonia injector system includes: a first body axially downstream of the vortex arrangement, in which a first ring distributor is defined, which is 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, wherein the second body has a second ring distributor defined therein, which is in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0010] Another aspect of the disclosure includes any one of the foregoing aspects, and the ammonia injector system includes a single body with a first ring distributor defined therein, which is in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring distributor defined therein, located next to the first ring distributor 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 one of the foregoing aspects, and each of the deflecting vanes includes an internal fuel flow channel in fluid communication with at least one fuel injector and further comprises a fuel supply which introduces a fuel other than ammonia into the internal fuel flow channel for injection into the airflow, wherein a fuel-air mixture generated by the vortex arrangement is directed into the combustion reaction zone in the combustion tube of the combustion chamber.

[0012] Another aspect of the disclosure includes any of the foregoing aspects and further comprises a central fuel supply line defined within the central element and a central fuel injector at a downstream end of the central fuel supply line, wherein the central fuel injector is configured to mix a fuel other than ammonia with a different air stream to produce a fuel-air mixture for combustion in the combustion reaction zone in the combustion tube of the combustion chamber.

[0013] Another aspect of the disclosure includes a combustion chamber for a gas turbine system, the combustion chamber comprising: a combustion chamber body with a combustion tube; a head-end arrangement with a cap arrangement and a plurality of burners positioned in the cap arrangement and directed into the combustion tube, wherein at least one burner of the plurality of burners includes: an outer element; a central element within the outer element defining a fuel-air mixing channel between them; a vortex arrangement positioned in the fuel-air mixing channel, the vortex arrangement including a plurality of deflector blades configured to swirl an airflow passing through the fuel-air mixing channel;and an ammonia injector system downstream of the vortex arrangement, wherein the ammonia injector system is configured to form an ammonia-air mixture for combustion in a combustion reaction zone in the combustion tube, the ammonia injector system comprising: a first plurality of ammonia injectors configured to inject a first stream of ammonia into the air stream; and a controller configured to selectively control the ammonia stream to the first plurality of ammonia injectors depending on a combustion chamber load, each of the first plurality of ammonia injectors having an injection axis directed upstream from a radial position in the direction of the air stream flowing through the fuel-air mixing channel downstream of the vortex arrangement.

[0014] Another aspect of the disclosure includes any one of the foregoing aspects, and the ammonia injector system includes a first ammonia supply line that directs the first ammonia stream to the first plurality of ammonia injectors; a second plurality of ammonia injectors configured to inject a second ammonia stream into the air stream; and a second ammonia supply line that directs the second ammonia stream to the second plurality of ammonia injectors, the control being configured to selectively control the flow to one or both of the first ammonia supply lines and the second ammonia supply lines depending on the combustion chamber load.

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

[0016] Another aspect of the disclosure includes any of the foregoing aspects, and the ammonia injector system includes: a first body axially downstream of the vortex arrangement, in which a first ring distributor is defined, which is 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, wherein the second body has a second ring distributor defined therein, which is in fluid communication with the second ammonia supply line and the second plurality of ammonia injectors.

[0017] Another aspect of the disclosure includes any one of the foregoing aspects, and the ammonia injector system includes a single body with a first ring distributor defined therein, which is in fluid communication with the first ammonia supply line and the first plurality of ammonia injectors, and a second ring distributor defined therein, located next to the first ring distributor 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 one of the foregoing aspects, and each of the deflecting vanes includes an internal fuel flow channel in fluid communication with at least one fuel injector and further comprises a fuel supply which introduces a fuel other than ammonia into the internal fuel flow channel for injection into the airflow, wherein a fuel-air mixture generated by the vortex arrangement is directed into the combustion reaction zone in the combustion tube of the combustion chamber.

[0019] Another aspect of the disclosure includes any of the foregoing aspects and further comprises a central fuel supply line defined within the central element and a central fuel injector at a downstream end of the central fuel supply line, wherein the central fuel injector is configured to mix a fuel other than ammonia with a different air stream to produce a fuel-air mixture for combustion in the combustion reaction zone in the combustion tube of the combustion chamber.

[0020] Another aspect of the disclosure includes a method for operating a combustion chamber of a gas turbine system, the method comprising: in a combustion chamber comprising a combustion chamber body including a combustion tube and a head-end arrangement, including: a cap arrangement and a plurality of burners positioned in the cap arrangement and directed into the combustion tube, wherein at least one burner of the plurality of burners includes a fuel-air mixing channel with a vortex arrangement comprising a plurality of deflector blades configured to swirl an airflow passing through the fuel-air mixing channel, performing the following: injecting ammonia with a plurality of ammonia injectors directed upstream into the airflow in the fuel-air mixing channel, at one or more axial locations downstream of the vortex arrangement.to produce an ammonia-air mixture; and combustion of the ammonia-air mixture formed by the multitude of burners in a combustion reaction zone in the combustion tube.

[0021] Another aspect of the disclosure includes any one of the foregoing aspects, and the injection of ammonia into the airflow in the fuel-air mixing channel downstream of the vortex arrangement takes place at two different axial locations.

[0022] Another aspect of the disclosure includes any one of the foregoing aspects, and the injection of ammonia into the airflow in the fuel-air mixing channel downstream of the vortex arrangement includes the injection of a first volume of ammonia at a first combustion chamber load and a second, larger volume of ammonia at a second, larger combustion chamber load.

[0023] Two or more aspects described in this disclosure, including those described in this summary section, can be combined to form implementations not specifically described herein. That is to say, all embodiments described herein can be combined with one another.

[0024] The details of one or more implementations are set out in the attached drawings and the description below. Further features, functions, and advantages will become apparent from the description, the drawings, and the claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] These and other features of this revelation will be better understood from the following detailed description of the various aspects of the revelation in conjunction with the accompanying drawings, which depict different embodiments of the revelation, in which the following applies: Fig. Figure 1 shows a functional block diagram of an illustrative gas turbine system with a combustion chamber capable of enclosing a burner with an ammonia injector system, according to embodiments of the disclosure; Fig. Figure 2 shows a simplified cross-sectional side view of an illustrative combustion chamber which may include a burner with an ammonia injector system, according to embodiments of the disclosure; Fig. Figure 3 shows an upstream view of a section of the river in Fig. 2 combustion chamber shown according to embodiments of the disclosure; Fig. Figure 4 shows a cross-sectional side view of a burner incorporating an ammonia injector system, according to embodiments of the disclosure; Fig. Figure 5 shows an enlarged view of an ammonia injector system according to embodiments of the disclosure; Fig. Figure 6 shows a cross-sectional view of an ammonia injector according to embodiments of the disclosure; Fig. Figure 7 shows a schematic view of an ammonia injection jet from a conventional fuel injector; Fig. Figure 8 shows a schematic view of an ammonia injection jet from an ammonia injector according to embodiments of the disclosure; Fig. Figure 9 shows a perspective cross-sectional view of a single body with ring distributors for ammonia injectors according to embodiments of the disclosure; and Fig. Figure 10 shows a cross-sectional side view of a burner including an ammonia injector system comprising two bodies with ring distributors for ammonia injectors, according to other embodiments of the disclosure.

[0026] It is noted that the drawings in the Book of Revelation are not necessarily to scale. The drawings are intended only to represent typical aspects of the Book of Revelation and should therefore not be considered as limiting the scope of protection afforded by the Book of Revelation. In the drawings, identical numbers correspond to identical elements between the drawings. DETAILED DESCRIPTION

[0027] To clearly describe the present disclosure, it is first necessary to select a certain terminology when referring to and describing relevant machine components within the illustrative application of a turbomachine combustion chamber and an associated ammonia injector system. Where possible, industry-standard terms are used and employed in a manner consistent with their accepted meanings. Unless otherwise specified, such terminology should be interpreted broadly, in accordance with the context of the present application and the scope of the accompanying claims. Those skilled in the art will recognize that a particular component may often be referred to using several different or overlapping terms.What may be described herein as a single part may include multiple components and, in another context, be described as consisting of these. Alternatively, what may be described herein as including multiple components may elsewhere be described as a single part.

[0028] Furthermore, several descriptive terms may be used herein, and it should prove helpful to define these terms at the beginning of this section. These terms and their definitions are, unless otherwise stated, 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 combustion chamber of the turbomachine, or, for example, the flow of air or ammonia through the combustion chamber or heat exchanger, or coolant through any of the component systems of the turbomachine. The term "downstream" corresponds to the direction of flow of the fluid, and the term "upstream" denotes the direction opposite to the flow.The terms “front” and “rear” refer, without further specification, to directions, with “front” referring to the front or compressor end of the turbomachine or combustion chamber and “rear” referring to the rear or turbine end of the turbomachine or combustion chamber.

[0029] The term "axial" refers to a movement or position parallel to an axis, such as the axis of an ammonia injector, burner, combustion chamber, or turbomachine. The term "radial" refers to a movement or position perpendicular to an axis, such as the axis of an ammonia injector, burner, combustion chamber, or turbomachine. If a first component is closer to the axis than a second component, it is stated here that the first component is "radially inside" or "inside" to the second component. Conversely, if the first component is farther from the axis than the second component, it may be stated here that the first component is "radially outside" or "outside" to the second component. Finally, the term "circumferential" refers to a movement or position around an axis, such as...to a circumferential inner surface of a combustion chamber body or a circumferential inner surface of a housing extending around a combustion chamber. As stated above, and depending on the context, these terms are understood to refer to the axis of the ammonia injector, burner, combustion chamber, or turbomachine.

[0030] Furthermore, several descriptive terms can be used regularly here, as described below. The terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0031] The terminology used herein serves only to describe certain embodiments and is not intended to limit the disclosure. In the sense used herein, the singular forms "a," "an," and "the" are to include the plural forms unless the context clearly indicates otherwise. It is further understood that the terms "comprises" and / or "comprehensive," when used in this description, specify the presence of specified features, integers, steps, processes, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, processes, elements, components, and / or groups thereof.“Optional” or “chosen” means that the event described below may occur, but does not have to, or that the feature described below may be present, but does not have to, and that the description includes cases in which the event occurs or the feature is present, and cases in which the event does not occur or the feature is not present.

[0032] When an element or layer is described as "on," "interacting with," "connected with," "coupled with," or "mounted on" another element or layer, it may be directly on, interacting with, connected with, coupled with, or mounted on the other element or layer, or there may be intervening elements or layers. Conversely, when an element is described as "directly on," "directly interacting with," "directly connected with," or "directly coupled with" another element or layer, there are no intervening elements or layers. Other words used to describe the relationship between elements should be interpreted similarly (e.g., "between" versus "directly between," "adjacent" versus "directly adjacent," etc.).In the sense used here, the term "and / or" includes any and all combinations of one or more of the associated listed items. The verb forms of "couple" and "assemble" can be used interchangeably here.

[0033] Embodiments of the disclosure provide a burner for a combustion chamber of a gas turbine system, a combustion chamber, and an associated method. The burner includes an outer element and a central element within the outer element, the latter defining a fuel-air mixing channel. A vortex assembly is arranged in the fuel-air mixing channel. The vortex assembly includes a plurality of deflecting vanes configured, among other things, to swirl an airflow passing through the fuel-air mixing channel. An ammonia injector system is located downstream of the vortex assembly and is configured to form an ammonia-air mixture for combustion in a combustion reaction zone defined within a combustion tube of the combustion chamber.The ammonia injector system includes a first set of ammonia injectors configured to inject a first stream of ammonia into the airflow, and a second set of ammonia injectors configured to inject a second stream of ammonia into the airflow. Each ammonia injector has an injection axis directed upstream from a radial position in the direction of the airflow passing through the fuel-air mixing channel downstream of the vortex assembly.

[0034] The ammonia injector system provides an efficient method for injecting liquid ammonia. The ammonia injectors are inclined relative to and aligned with the airflow path to prevent film formation on the walls of the fuel-air mixing channel. The sets of ammonia injectors allow for the injection of varying ammonia volumes based on different combustion chamber loads to ensure the formation of fine ammonia droplets. At lower combustion chamber loads, one set of ammonia injectors is used for injecting liquid ammonia, while the other set can be operated with purging (air only). The burners described herein provide variable volume ammonia injection based on different combustion chamber loads, resulting in more precise and stable combustion.Furthermore, the angularity (alternatively “inclination”) of the ammonia injectors provides an improved dispersion of the ammonia, which is more efficient in avoiding film formation on the fuel-air mixing channel and does not destabilize the combustion reaction.

[0035] Referring to the drawings, the Fig. Figure 1 provides a schematic diagram of an illustrative gas turbine system 100 (GT system 100). The GT system 100 generally includes an inlet section 112, a compressor 114 located downstream of the inlet section 112, a combustion system 116 including at least one combustion chamber 118 located downstream of the compressor 114, a turbine 120 (i.e., an expansion turbine) located downstream of the combustion chamber 118, and an exhaust section 122 located downstream of the turbine 120. Furthermore, the GT system 100 may include one or more shafts 124 that couple the compressor 114 to the turbine 120. During operation, air 126 flows through inlet section 112 and into compressor section 114, where air 126 is progressively compressed, thereby providing compressed air 128 to the combustion chamber 118.One or more fuels 130 from one or more fuel feeds 132 are injected into combustion chamber 118, mixed with a portion of the compressed air 128, and combusted to produce combustion gases 134. The combustion gases 134 flow from combustion chamber 118 into turbine 120, transferring energy (kinetic and / or thermal) from the combustion gases 134 to rotor blades (not shown), causing shaft 124 to rotate. The mechanical rotational energy can then be used for various purposes, such as driving compressor 114 and / or generating electricity.

[0036] Combustion gases 134 exiting turbine 120 can then be expelled from GT system 100 via exhaust section 122.

[0037] In one embodiment, GT-System 100 can be applied to an existing drive machine model commercially available from GE Vernova in Cambridge, MA. The present disclosure is not limited to a particular GT-System and can be implemented in conjunction with other drive machines, including, for example, any other HA, F, B, LM, GT, TM, and E-class drive machine model from GE Vernova and drive machine models from other companies.

[0038] Fig. Figure 2 provides a schematic cross-sectional view of an exemplary combustion chamber 118, which may contain various embodiments of the present disclosure. As in Fig. As shown in Figure 2, burner 118 can be at least partially enclosed by an outer housing 136, such as a compressor outlet housing. The outer housing 136 can at least partially define a high-pressure distributor 138, which at least partially surrounds various components of the combustion chamber 118. The high-pressure distributor 138 can be connected to compressor 114 ( Fig. 1) are in fluid connection in order to receive at least part of the compressed air 128 from there. The high-pressure distributor 138 can supply compressed air 128 to various parts of the multi-fuel burner 200 described herein.

[0039] An end cover 140 can be coupled to an outer casing 136. The end cover 140 can include all necessary passages or openings to supply fuel such as natural gas, liquid fuel, ammonia, or compressed air 128 through it, as described herein. For example, the end cover 140 can include all necessary passages or openings to allow fuel supply lines 280, 282 ( Fig. 4 to 5) and 320 ( Fig. 10) thereby. The end cover 140 can be configured to detachably position multi-fuel burners 200, 202 (hereinafter referred to as "burner 200" or "middle burner 202" unless otherwise required for differentiation) in the head assembly 143 of the combustion chamber 118, which, for example, includes a cap assembly 150 with openings in which the rear ends of the burners 200 are positioned. In this way, burners 200 can be removed by removing part of the end cover 140 and / or the burner 200 from the connection to the head assembly 143 and sliding the burner(s) 200 out.

[0040] The end cover 140 can optionally be coupled to the head end assembly 143 in any currently known or subsequently developed manner, such as, but not limited to, threaded fastenings (not shown). The outer casing 136 and the end cover 140 can at least partially define a head end volume or chamber 142 within a head end assembly 143 of the combustion chamber 118. In particular embodiments, the head end volume 142 is in fluid communication with the high-pressure distributor 138 and / or compressor 114. One or more tubes or channels form the combustion tube 144, which can at least partially define a combustion reaction zone or chamber 146 for burning one or more fuel-air mixtures and can at least partially define a hot gas path 148 through the combustion chamber 118 to direct combustion gases 134 to an inlet in the turbine 120.

[0041] Fig. Figure 3 provides an upstream view of a section of combustion chamber 118, as shown in Fig. 2 shown. In various embodiments, as in Fig. 2 and Fig. As shown in Figure 3, combustion chamber 118 includes a plurality of burners or fuel nozzles (e.g., 200) whose upstream ends are coupled to end covers 140 and which extend towards the combustion reaction zone 146. The downstream ends of the burners 200 are aligned with corresponding openings (not shown) in cap arrangement 150, so that the burners 200 supply a fuel / air mixture to the combustion reaction zone 146, which is defined by combustion tube 144.

[0042] Different embodiments of the combustion chamber 118 can include different numbers and arrangements of burners 200, and the embodiments described herein are not limited to a particular number of burners unless otherwise specified in the claims. For example, in special configurations, such as the one described in Fig. In the configuration 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, burners 200 can be arranged in a ring around a center line of the end cover 140 without using the central burner 202. The central burner 202 can also be of the type of a premixed multi-fuel burner (liquid fuel and gas fuel burner). Other burner types can be used instead of the central burner 202, if desired. The central burner 202 can be the same as the burner 200 described herein. Each burner 200 can be of the type of a premixed multi-fuel burner. More precisely, each burner 200 can be used to burn a gaseous fuel, such as natural gas and / or ammonia, the latter being in liquid form.Each burner 200 is configured to burn a gaseous fuel and / or a liquid fuel with a stream of part of the compressed air 128 from head end volume 142 (. Fig. 2) to be injected and premixed in the head end arrangement 143 upstream of the combustion reaction zone 146.

[0043] Fig. Figure 4 provides a cross-sectional side view of an illustrative burner 200 (or 202) with premix and multi-fuel functions according to at least one embodiment of the present disclosure. In particular embodiments, such as the one in Fig. In the embodiment shown in Figure 4, burner 200 includes a central element 210 and an outer element 212, each element having a ring or tube shape. More precisely, burner 200 can include an outer element or burner tube 212 that extends circumferentially and concentrically around at least one section of the central element 210. As illustrated, the central element 210 is located within the outer element 212, and a fuel-air mixing channel 214 is defined between them. Burner 200 also includes a vortex assembly 220 positioned within the fuel-air mixing channel 214. The vortex assembly 220 includes a plurality of deflector blades 222 configured to swirl an airflow 234 that flows through gaps between circumferentially adjacent deflector blades 222 and into the fuel-air mixing channel 214.More precisely, a multitude of deflecting vanes 222 extend between the central element 210 and the outer element 212. Deflection vanes 222 are arranged in the fuel-air mixing channel 214, which can be annular, and can be defined radially between the central element 210 and the outer element 212, as mentioned.

[0044] Vortex arrangement 220 can, as described herein, be used simply to generate a swirling airflow 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 deflecting vanes 222 can enclose one or more fuel injectors 224 that are in fluid communication with a fuel distributor 226 defined within the central element 210 or another gas fuel source. Fuel distributor 226 is fluidically connected to a fuel supply 228 ( Fig. 4) coupled to obtain, for example, a gaseous fuel 230. More precisely, each deflector vane 222 can enclose an internal fuel flow channel 232, which is in fluid communication with at least one fuel injector 224. Fuel supply 228 introduces a fuel 230 other than ammonia (via fuel distributor 226) into the internal fuel flow channel 232 for injection into the airflow 234. Thus, a fuel-air mixture is generated by the vortex arrangement 220, which is directed into the combustion reaction zone 146 in the combustion tube 144 of the combustion chamber 118. In one example, the fuel 230 can be natural gas, which is mixed with the airflow 234 to generate a fuel-air mixture for combustion in the combustion reaction zone 146. In certain cases, fuel 230 can be shut off to the vortex arrangement 220, e.g. B. using a control valve 235, which is controlled by a controller 236 (e.g.The combustion chamber 118 or another system) is controlled so that only the (swirling) airflow 234 exits the vortex arrangement 220. Control 236 is described further herein. This arrangement can be used, for example, when ammonia is used as fuel for combustion instead of natural gas, as will be described herein.

[0045] As in Fig. As shown in Figure 4, the central element 210 can be formed from one or more sleeves or tubes 240, which are aligned coaxially with a common longitudinal axis or axial centerline 242 of the central element 210 and the burner 200. The axial centerline 242 of the central burner 202 also coincides with an axial centerline of the cap assembly 150. The burner 200 can be connected to an inner surface of the end cover 140 via mechanical fasteners or other connecting means (not shown). In special embodiments and as shown in Figure 4, the central element 210 can be formed from one or more sleeves or tubes 240, which are aligned coaxially with a common longitudinal axis or axial centerline 242 of the central element 210 and the burner 200. The axial centerline 242 of the central burner 202 also coincides with an axial centerline of the cap assembly 150. The burner 200 can be connected to an inner surface of the end cover 140 by means of mechanical fasteners or other connecting means (not shown). Fig. As shown in Figure 4, an upstream end section 244 of the outer element 212 can at least partially define an inlet 246 to the fuel-air mixing channel 214, and a downstream end section 248 of the outer element 212 can at least partially define an outlet 250 of the fuel-air mixing channel 214, i.e., to the 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 arrangement 143 of the combustion chamber 118, in order to obtain compressed air 128 therein.

[0046] Fig. Figure 5 provides an enlarged view of an ammonia injector system 260 of the burner 200, as shown in Fig. 4 shown. In various embodiments, examples of which are shown together in Fig. 4 and Fig. As shown in Figure 5, burner 200 includes an ammonia injector system 260 downstream of the vortex arrangement 220. The ammonia injector system 260 is configured to form an ammonia-air mixture 262 for combustion in combustion reaction zone 146 in the combustion tube 144 of the combustion chamber 118. In certain cases, the ammonia-air mixture 262 can be mixed with a mixture of fuel 230 ( Fig. 4) and an airflow 234 (i.e. a fuel-air mixture of natural gas and air) from vortex arrangement 220, but this is not required in all cases.

[0047] Ammonia injector system 260 includes a first plurality or set of ammonia injectors 272 configured to inject a first ammonia stream 274 into air stream 234 (from vortex arrangement 220), and a second plurality or set of ammonia injectors 276 configured to inject a second ammonia stream 278 into air stream 234. Fig. Figures 6 to 8 show different views of ammonia injectors 272, 276 according to embodiments of the disclosure and are further described herein. Continue with Fig. 4 and Fig. 5 Continuing, the ammonia injector system 260 includes a first ammonia supply line 280, which directs the first ammonia stream 274 to a first plurality of ammonia injectors 272, and a second ammonia supply line 282, which directs the second ammonia stream 278 to a second plurality of ammonia injectors 276. The ammonia supply lines 280 and 282 may include any suitable conduits or tubes suitable for supplying ammonia and capable of withstanding the high-temperature environment of the burner 200.

[0048] The ammonia injector system 260 can also include a controller 236 configured to selectively control the ammonia flow to one or both of the first set of ammonia injectors 272 and the second set of ammonia injectors 276 depending on a combustion chamber load. The controller 236 can be part of any currently known or subsequently developed combustion chamber control system or a control system of the GT system 100 ( Fig. 1) and can include any hardware and / or software configured to perform the functions described herein. For example, controller 236 is configured to selectively control the flow to one or both of the first ammonia supply line 280 and / or the second ammonia supply line 282, e.g., by controlling the valve(s) 283, from an ammonia supply 285 and thus the respective sets of ammonia injectors 272, 276 fluidically coupled thereto. Whether one or both sets of ammonia injectors 272, 276 are used depends on the combustion chamber load. The ‘combustion chamber load’ used herein refers to the amount of combustion that must be produced by the combustion chamber 118, based on the requirements of the turbine 120 ( Fig. 1) or other operating parameters such as, but not limited to, airflow 234, ambient conditions and flow rate, and can be calculated in any desired way based on the data provided to the controller 236.

[0049] Once again on Fig. 4 With reference to this, multiples of ammonia injectors 272, 276 can be provided in different ways according to embodiments of the disclosure. Fig. 4 Ammonia injector system 260 includes a single body or distributor body 300 with a first ring distributor 302 defined therein in fluid communication with the first ammonia supply line 280 and the first plurality of ammonia injectors 272. The first body 300 also includes a second ring distributor 304, defined therein adjacent to the first ring distributor 302 and in fluid communication with the second ammonia supply line 282 and the second plurality of ammonia injectors 276. It should be noted that, although, as used herein, the term ‘ring distributor’ is used, it is clear that distributors 302, 304 can extend to the required extent to provide a fuel distributor for all desired ammonia injectors 272, 276, and that they are located within a respective body 300 (310, 316 ( Fig. 10)) may not extend in a complete circle in which it is defined. Body 300 can be coupled to or integrated into the central element 210 in any known way.

[0050] Fig. Figure 9 shows a cross-sectional view of the single body 300 for an ammonia injector system 260 according to certain embodiments. The first plurality of ammonia injectors 272 and the second plurality of ammonia injectors 276 can be arranged circumferentially around the single body 300 in any configuration, but within a given plurality, they can be arranged at equal intervals to distribute ammonia more evenly. Each plurality of ammonia injectors 272, 276 can also be spaced equally apart circumferentially, with, for example, every second ammonia injector belonging to one of the pluralityes of ammonia injectors. Ring distributors 302, 304 are positioned side by side, meaning they are spaced apart so that they do not interfere with each other. In some embodiments, ring distributors 302, 304 can be axially spaced apart from each other within the single body 300, i.e. relative to the center line 242 of the burner 200.For example, the second ring distributor 304 can be located axially downstream of the first ring distributor 302 in the individual body 300. In contrast, in . Fig. 4 and Fig. Nine ring distributors 302 and 304 are radially spaced apart from each other with a partition 306 between them. Passages 308 fluidically couple the (inner) ring distributor 302 to the first plurality of ammonia injectors 272, e.g., one passage for each ammonia injector 272. Ring distributor 304 is located radially directly inside the ammonia injectors 276 (or the openings in which they are located), so that possibly no (or only very short) passages in the individual body 300 are required to fluidically couple ring distributor 304 to ammonia injectors 276.

[0051] In any case, as in Fig. 4 and Fig. Figure 9 shows that the first ammonia supply line 280 and the first plurality of ammonia injectors 272 are fluidically connected through the first ring distributor 302 (and passages 308), which is defined in the individual body 300, and the second ammonia supply line 282 and the second plurality of ammonia injectors 276 are fluidically connected through the second ring distributor 304, which is defined in the individual body 300. Controller 236 can thus control which ammonia injectors 272, 276 inject ammonia by controlling the valve(s) 283, which controls the ammonia flow to each ammonia supply line 280, 282. Control unit 236 can direct ammonia to a first plurality of ammonia injectors 272 and / or a second plurality of ammonia injectors 276. Control unit 236 can also control the opening / closing degree of the valve(s) 283 to control the volume of ammonia delivered to each of the plurality of ammonia injectors 272, 276.In this way, the volume of ammonia injected into the fuel-air mixing channel 214 can be controlled based on the combustion chamber load.

[0052] With reference to Fig. In another embodiment, the second plurality of ammonia injectors 276 can be located axially downstream of the first plurality of ammonia injectors 272 in a separate second body 316. Here, the ammonia injector system 260 includes a first body 310 axially downstream of the vortex arrangement 220. The first body 310 has a first ring distributor 314, which is defined therein in fluid communication with the first ammonia supply line 280 and the first plurality of ammonia injectors 272. Furthermore, the ammonia injector system 260 includes a second body 316 axially downstream of the first body 310. The second body 316 has a second ring distributor 318, which is defined therein in fluid communication with the 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 can be spaced circumferentially around the respective bodies 310, 316 in any way, but within a given plurality they are usually spaced uniformly to ensure a uniform ammonia distribution. Ammonia injectors in each of the plurality of ammonia injectors 272, 276 can also be circumferentially offset relative to each other in the respective bodies 310, 316, such that ammonia injectors 272 do not inject ammonia along the same axial line 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 can be spaced axially in any way, e.g. B. directly next to each other (in contact) or at any desired axial distance, i.e.within the central element 210, the different multitudes of ammonia injectors 272, 276 are arranged at different axial positions. Any axial spacing arrangement is possible to achieve the desired ammonia-air mixture 262.

[0053] As in Fig. As shown in Figure 10, the first ammonia supply line 280 and the first plurality of ammonia injectors 272 are fluidically coupled by the first ring distributor 314, which is defined in the first body 310, and the second ammonia supply line 282 and the second plurality of ammonia injectors 276 are fluidically coupled by the second ring distributor 318, which is defined in the second body 316. Controller 236 can control which ammonia injectors 272, 276 inject ammonia by controlling the valve(s) 283, which controls the ammonia flow to each ammonia supply line 280, 282. As mentioned, control unit 236 can direct ammonia to a first plurality of ammonia injectors 272 and / or a second plurality of ammonia injectors 276. Control unit 236 can also control the opening / closing degree of valve(s) 283 to control the volume of ammonia delivered to each of the plurality of ammonia injectors 272, 276.In this way, the volume of ammonia injected into the fuel-air mixing channel 214 can be controlled based on the combustion chamber load.

[0054] With further reference to Fig. 5 and Fig. 10. The burner 200 can optionally also include a central fuel supply line 320, which is defined in the central element 210, and a central fuel injector 322 at a downstream end 324 of the central fuel supply line 320. It should be noted that in the version of Fig. Figure 4 omits the central fuel passage and the injector, but these could also be included. As illustrated, the central fuel supply line 320 and the central fuel injector 322 can be positioned within the central element 210. The central fuel injector 322 is configured to mix a fuel 328 other than ammonia with a different airflow 128 (e.g., from passages in the central element 210 from the fuel-air mixing channel 214 or the vortex arrangement 220) to produce a fuel-air mixture 330 for combustion in the combustion reaction zone 146 in the combustion tube 144 of the combustion chamber 118. The fuel 328 can be, for example, a liquid fuel such as heating oil. The central fuel injector 322 is axially aligned with respect to the axial center line 242 and is in fluid communication with the fuel supply 332 via the central fuel supply line 320.During operation, the central fuel injector 322 injects atomized liquid fuel 328 into combustion zone 146 at a location downstream of vortex arrangement 220 and downstream of the plurality of ammonia injectors 272, 276. In particular embodiments, the central fuel injector 322 can be screwed, bolted, or otherwise detachably fastened into the central element 210 to facilitate maintenance (e.g., cleaning) and / or replacement as needed.

[0055] In various embodiments, such as in Fig. 5 and Fig. As shown in Figure 10, a section of the central fuel supply line 320, which is located inside the central element 210 and downstream of the body 300 ( Fig. 5) or the body 310, 316 ( Fig. 10) is arranged spirally around the axial centerline 242 of the burner 200. In operation, the spiral section of the central fuel supply line 320 acts as a spring, allowing the fuel passage to expand and contract due to temperature differences between different parts of the burner 200. The central fuel supply line 320 can be fluidically connected to a fuel supply 332 ( Fig. 10) be coupled to obtain, for example, liquid fuel 328 from it. Control unit 236 can control any number of valves 334 to control the flow of the liquid fuel 328. The central fuel supply line 320 can be routed with the ammonia supply lines 280, 282 in any way. For example, the single body 300 ( Fig. 4 to 5) or the first and second bodies 310, 316 ( Fig. 10) each have a central opening 338 to allow the passage of the central fuel supply line 320. Compressed air 128 can also flow through the central opening 338 to create a fuel-air mixture 330. The central fuel injector 322 can include any currently known or subsequently developed fuel injector structure for the fuel used.

[0056] With regard to the ammonia supply of the ammonia injector system 260, as in Fig. 4 and Fig. Figure 10 shows distributors 302, 304, 314, 318 fluidically coupled to an ammonia supply 228 via fuel supply lines 280, 282. At least one section of the ammonia supply lines 280, 282 can be at least partially spiraled within the central element 210 around the central fuel supply line 320 (if present) and around each other in front of the most upstream single body 300 ( Fig. 4) or the first body 310 ( Fig. 10) extend. Ammonia supply lines 280, 282 are also arranged radially within the gas fuel distributor 226. In Fig. 4 and Fig. 5 is a rear end of the first ammonia supply line 280 fluidically coupled to a single body 300 and the ring distributor 302 located therein, and in Fig. 10 is a rear end of the second ammonia supply line 280 fluidically coupled to the first body 310 and the ring distributor 314 located therein. In Fig. 4 and Fig. 5 is a rear end of the second ammonia supply line 282 fluidically coupled to a single body 300 and the ring distributor 302 located therein, and in Fig. 10 is a rear end of the second ammonia supply line 282 fluidically coupled to the second body 316 and the ring distributor 318 located therein. In Fig. 10 The second ammonia supply line 282 extends through the first body 310 in a manner that does not obstruct either the ring distributor 314 or the ammonia injectors 272 in the first body 310. Any extension of the second ammonia supply line 282 required to reach the second body 316 can be used between the first body 310 and the second body 316.

[0057] Body 300 or body 310, 316 are attached to the central element 210 in any desired manner. The central opening 338 in the individual body 300 ( Fig. 4 to 5) or in the first and second bodies 310, 316 ( Fig. 10) is separated from the central fuel supply line 320 and allows the passage of compressed air 128. Thus, in special embodiments, the central fuel supply line 320 running 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 one or more sections that are spirally or coiled to act as a spring. 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 equalizes temperature differences between the various parts of the burner 200 and transfers heat to the ammonia flow within it. The first and second supply lines 280 and 282 do not cross each other but run radially outside the axial centerline 242 of the burner 200.

[0059] With reference to Fig. Section 6 now describes details of the ammonia injectors 272 and 276. As mentioned, this shows Fig. 6 A cross-sectional view of an ammonia injector 272, 276 according to embodiments of the disclosure. Ammonia injectors 272, 276 can be circumferentially arranged around / within a respective body 300 ( Fig. 4 to 5) or the body 310, 316 ( Fig. 10) be spaced apart, and each is in fluid communication with a respective ring distributor 302, 304 ( Fig. 4 to 5) or 314, 318 ( Fig. 10) To prevent the formation of a film of ammonia (NH3) on the walls of the fuel-air mixing channel 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 that is directed upstream from a radial position R (with respect to the centerline 242 of the burner 200) in the direction of the airflow 234, which flows through the fuel-air mixing channel 214 downstream of the vortex arrangement 220. The injection axis Ai can be offset by an angle α relative to the radial position R. Angle α can be in a range of, for example, 15° to 65° from radius R. Angle α can be selected, for example, based on properties of the airflow 234 and / or the liquid ammonia and the desired atomization of the ammonia.Therefore, each ammonia injector 272, 276 is not radially oriented with respect to the axial centerline 242 in order to inject an atomized ammonia jet 274, 278 into the fuel-air mixing channel 214 at a location downstream of the vortex arrangement 220, deflector vanes 222, and / or gas fuel injectors 224. Although the first plurality of ammonia injectors 272 and the second plurality of ammonia injectors 276 are illustrated with injection axes Ai at the same angle α, it is understood that the first plurality of ammonia injectors 272 may have an injection axis Ai at a first angle that differs from the 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 the radius R.

[0060] Ammonia injectors 272, 276 can be inserted into a corresponding opening 340 of the individual body 300 ( Fig. 4 to 5) or the body 310, 316 ( Fig. 10) can be screwed, bolted, or otherwise detachably fastened therein to facilitate maintenance (e.g., cleaning) and / or replacement as needed. Openings 340 are also in Fig. Figure 9 shows that fuel injectors 272, 276 and / or openings 340 can be structured and / or arranged to generate the desired injection axis Ai, for example, 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 can otherwise take the form of any nozzle or atomizer capable of converting liquid ammonia into a mist of very fine droplets.

[0061] Fig. Figure 7 shows a schematic representation of a conventional ammonia injection system with a radially extending (R) injection axis perpendicular to the airflow 234, and Fig. Figure 8 shows a schematic representation of an ammonia injection system with an injection axis Ai oriented at an angle α relative to a radial position R, according to embodiments of the disclosure. Fig. 7 The leeward or downstream side of the ammonia spray jet 344 is shielded by the upstream or windward side of the ammonia spray jet 346, creating a dense area 348 that hinders the atomization of the ammonia and can lead to the formation of a film 350 on the walls of the fuel-air mixing channel 214. Film 350 prevents efficient combustion of the ammonia-air mixture in the combustion reaction zone 146. In contrast, in Fig. 8 the leeward or downstream side 352 of the ammonia spray jet 274, 278 and the upstream or windward side 354 of the ammonia spray jet 274, 278 are directed more evenly into the airflow 234, whereby ammonia in the ammonia-air mixture 262 can be better atomized and only a small or no film 350 is formed ( Fig. 7) and the ammonia-air mixture 262 can be burned more efficiently in combustion reaction zone 146.

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

[0063] A method for operating the combustion chamber 118 of the GT system 100 according to embodiments of the disclosure is now described. In operation, embodiments of the method include the combustion of the ammonia-air mixture 262 formed by burners 200 in combustion reaction zone 146 in combustion tube 144. As mentioned, combustion chamber 118 includes a combustion chamber body 141, which in turn includes a combustion chamber tube 144 and a head-end arrangement 143 including a cap arrangement 150. Combustion chamber 118 also includes a plurality of burners 200, which are positioned in cap arrangement 150 and directed into combustion chamber tube 144. Each burner 200 includes a fuel-air mixing channel 214 with a vortex arrangement 220 including a plurality of deflecting vanes 222 configured to swirl the airflow 234 passing through the fuel-air mixing channel 214.The method involves injecting ammonia using a plurality of ammonia injectors 272, 276, which are directed upstream in the airflow 234 in the fuel-air mixing channel 214 at one or more axial locations downstream of the vortex assembly 220 to generate an ammonia-air mixture 262. During ammonia injection using the ammonia injector system 260, the injection of the gaseous fuel 230 using the vortex assembly 220 can be stopped, causing the vortex assembly 220 to provide only an airflow 234 to generate the ammonia-air mixture 262. Fig. Figures 4 to 5 show ammonia injectors 272, 276 in an axial position. As in Fig. As shown in Figure 10, the injection of ammonia into airflow 234 in the fuel-air mixing channel 214 downstream of the vortex arrangement 220 can take place 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 the combustion of an ammonia-air mixture 262, formed by a plurality of burners 200 in combustion reaction zone 146 in combustion tube 144. With reference to Fig. 4 and Fig. 10 In certain embodiments, the method can also include injecting ammonia into the airflow 234 in the fuel-air mixing channel 214 downstream of the vortex arrangement 220 in different volumes depending on the combustion chamber load. For example, the ammonia injection can include injecting a first volume of ammonia at a first combustion chamber load and a second, larger volume of ammonia at a second, larger combustion chamber load. Controls 236 can control the fuel flow of any fuel, including ammonia, using the valve(s) 235, 283, and / or 334. In certain embodiments, ammonia can be injected at an air-fuel ratio of 1.1 to 1.5. In some embodiments, as in Fig. 5 and Fig. As shown in Figure 10, the method can further include the injection of a liquid fuel from a central fuel injector 322 positioned downstream of the ammonia injector system 260, so that a liquid fuel-air mixture is introduced into combustion reaction zone 146 in the combustion tube 144.

[0064] The burner 200 and its components may be manufactured from any currently known or future developed combustion-tolerant and oxidation-resistant material. The material may be metal and may be a pure metal or an alloy. The burner 200 may include a metal commonly used in turbine components, such as turbine blades or nozzles, which exhibits higher temperature and oxidation tolerance than materials commonly used for combustion system components. In this case, the second material may include a non-reactive metal, such as one made from a non-explosive or non-conductive powder, such as, but not limited to: a cobalt-chromium-molybdenum alloy (CoCrMo alloy), stainless steel, an austenitic nickel-chromium-based alloy, such as a nickel-chromium-molybdenum-niobium alloy (NiCrMoNb alloy) (e.g.,Inconel 625 or Inconel 718), a nickel-chromium-iron-molybdenum alloy (NiCrFeMo alloy) (e.g., Hastelloy® X, available from Haynes International, Inc.), a nickel-chromium-cobalt-molybdenum alloy (NiCrCoMo alloy) (e.g., Haynes 232 or Haynes 282, available from Haynes International, Inc.), or a nickel-chromium-cobalt-titanium alloy (NiCrCoTi alloy) (e.g., GTD 262, developed by General Electric Company). Other options include René 108, CM 247, Mar M 247, and any heat-treatable (PH) nickel alloy.

[0065] In certain embodiments, the Brenner 200 can be additively manufactured using any currently known or future developed technology capable of forming a single-piece body. Consequently, the different parts can comprise a multitude of parallel, sintered metal layers. Other manufacturing methods are also possible.

[0066] As in Fig. As shown in Figure 2, embodiments of the disclosure may also include combustion chamber 118 for GT system 100. Combustion chamber 118 includes a combustion chamber body 141 including a combustion tube 144. Combustion chamber 118 also includes a head-end assembly 143 including burners 200, as described herein, possibly with a central burner 202 directed into combustion chamber tube 144. Burners 200 may be as described herein and are directed into combustion tube 144. Combustion chamber 118 generally terminates at a point adjacent to turbine 120. A first stage of fixed nozzles defines at least a portion of a turbine inlet to turbine 120. Combustion chamber body 141, i.e., combustion tube 144, defines at least a portion of a hot gas path (HGP) for directing combustion gases 134 from combustion reaction zone 146 to turbine 120 during operation of the GT system 100.

[0067] Furthermore, embodiments of the disclosure may, as in Fig. Figure 1 shows a GT system 100, which includes an inlet section 112, a compressor 114 located downstream of the inlet section 112, a combustion system 116, which includes at least one combustion chamber 118 located downstream of the compressor 114, and a turbine 120 located downstream of the combustion chamber 118. The combustion chamber(s) 118 is / are operationally coupled to the compressor 114, and the turbine 120 is operationally coupled to the combustion chamber(s) 118. As described herein, the combustion chambers 118 include the combustion chamber body 141, including the combustion tube 144 and the head-end fuel nozzle assembly 143 at a front end of the combustion chamber body 141. The combustion chamber(s) 118 may also include burners 200, as described herein. Head end arrangement 143 includes a plurality of burners 200 directed into combustion tube 144 as described herein.

[0068] The disclosure provides various technical and commercial advantages, examples of which are discussed herein. The burners described herein provide ammonia injection in varying volumes based on different combustion chamber loads, thereby ensuring more precise and stable combustion. Furthermore, the angled design of the ammonia injectors provides improved ammonia dispersion, which more effectively prevents film formation in the fuel-air mixing channel and avoids destabilizing the combustion reaction.

[0069] An approximation language, such as that used throughout this description and the claims, may be applied to modify any quantitative representation that could permissibly vary without altering the fundamental function to which it relates. Accordingly, a value modified by a term or terms such as "approximately," "approximately," and "essentially" is not limited to the precisely specified value. At least in some cases, the approximation formulation may correspond to the accuracy of an instrument for measuring the value. Here, and throughout this patent and the claims, range limitations may be combined and / or interchanged; such ranges are identified and include all subranges contained therein unless context or formulation indicates otherwise.“Approximately” or “about” in relation to a specific value of a range applies to both end values ​​and, unless otherwise stated, may indicate + / - 10% of the stated value(s), depending on the accuracy of the instrument measuring the value.

[0070] The corresponding structures, materials, actions, and equivalents of all means or stages plus functional elements in the following claims are intended to include any structure, material, or action for performing the function in combination with other claimed elements, as specifically claimed. The description of the present disclosure has been provided for illustrative and descriptive purposes but is not intended to be exhaustive or limited to the disclosure as disclosed. To those skilled in the art, many modifications and variations are apparent without departing from the scope of protection and spirit of the disclosure.The embodiments were chosen and described to best illustrate the principles of the disclosure and their practical application of the technology, and to enable other persons skilled in the art to understand the present disclosure with consideration of various modifications to the present embodiments which may be suitable for the specific intended use.

Claims

[1] Burner (200) for a combustion chamber (118) of a gas turbine system (100), wherein the burner (200) comprises: an outer element (212); a central element (210) within the outer element (212) which defines a fuel-air mixing channel (214) in between; a vortex arrangement (220) positioned in the fuel-air mixing channel (214), wherein the vortex arrangement (220) includes a plurality of deflecting vanes (222) configured to swirl an airflow (234) flowing through the fuel-air mixing channel (214); and an ammonia injector system (260) downstream of the vortex arrangement (220), wherein the ammonia injector system (260) is configured to form an ammonia-air mixture (262) for combustion in a combustion reaction zone (146) in a combustion tube (144) of the combustion chamber (118), the ammonia injector system (260) comprising: a first plurality of ammonia injectors (272) configured to inject an initial stream of ammonia (274) into the air stream (234), wherein each of the first plurality of ammonia injectors (272) has an injection axis (Ai) directed from a radial position upstream in the direction of the airflow (234) flowing through the fuel-air mixing channel (214) downstream of the vortex arrangement (220). [2] Burner (200) according to claim 1, wherein the ammonia injector system (260) includes a first ammonia supply line (280) that directs the first ammonia stream (274) to the first plurality of ammonia injectors (272); a second plurality of ammonia injectors (276) configured to inject a second ammonia stream (278) into the air stream (234); and a second ammonia supply line (282) that directs the second ammonia stream (278) to the second plurality of ammonia injectors (276); wherein each of the second plurality of injectors (276) has an injection axis (Ai) directed upstream from the radial position in the direction of the air stream (234). [3] Burner (200) according to claim 2, further comprising a control (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) depending on a combustion chamber load, wherein the control (236) is configured to selectively control the flow to one or both of the first ammonia supply line (280) and the second ammonia supply line (282) depending on the combustion chamber load. [4] Burner (200) according to claim 2, wherein the second plurality of ammonia injectors (276) is located axially downstream of the first plurality of ammonia injectors (272). [5] Burner (200) according to claim 4, comprising the ammonia injector system (260): a first body (300) axially downstream of the vortex arrangement (220), which has a first ring distributor (302) defined therein, which is in fluid communication with the first ammonia supply line (280) and the first plurality of ammonia injectors (272); and a second body (316) axially downstream of the first body (300), wherein the second body (316) has a second ring distributor (318) defined therein, which is in fluid communication with the second ammonia supply line (282) and the second plurality of ammonia injectors (276). [6] Burner (200) according to claim 2, wherein the ammonia injector system (260) includes a single body (300) with a first ring distributor (302) defined therein in fluid communication with the first ammonia supply line (280) and the first plurality of ammonia injectors (272) and a second ring distributor (304) defined therein adjacent to the first ring distributor (302) and in fluid communication with the second ammonia supply line (282) and the second plurality of ammonia injectors (276). [7] Burner (200) according to claim 1, wherein each of the deflecting vanes (222) includes an inner fuel flow channel (232) in fluid communication with at least one fuel injector (224), and further comprising a fuel supply (228) which introduces a fuel (230) other than ammonia into the inner fuel flow channel (232) for injection into the airflow (234), wherein a fuel-air mixture generated by the vortex arrangement (220) is directed into the combustion reaction zone (146) in the combustion tube (144) of the combustion chamber (118). [8] Burner (200) according to claim 1, further comprising a central fuel supply line (320) defined within the central element (210) and a central fuel injector (322) at a downstream end (324) of the central fuel supply line (320), wherein the central fuel injector (322) is configured to mix a fuel (230) other than ammonia with a different air stream to produce a fuel-air mixture for combustion in the combustion reaction zone (146) in the combustion tube (144) of the combustion chamber (118). [9] Combustion chamber (118) for a gas turbine system (100), wherein the combustion chamber (118) comprises: a combustion chamber body (141) with a combustion tube (144); a head end arrangement (143) with a cap arrangement (150) and a plurality of burners (200) positioned in the cap arrangement (150) and directed into the combustion tube (144), wherein at least one burner of the plurality of burners (200) is defined according to any one of claims 1 to 8. [10] Method for operating a combustion chamber (118) of a gas turbine system (100), the method comprising: in a combustion chamber 118, which includes a combustion chamber body 141 including a combustion tube 144 and a head end arrangement (143), including: a cap arrangement (150) and a plurality of burners (200) which are positioned in the cap arrangement (150) and directed into the combustion tube (144), wherein at least one burner of the plurality of burners (150) is defined according to any one of claims 1 to 8, performing the following: Injecting ammonia with a plurality of ammonia injectors (272, 276) directed upstream into the airflow (234) in the fuel-air mixing channel (214) at one or more axial locations downstream of the vortex arrangement (220) to generate an ammonia-air mixture (262); and Combustion of the ammonia-air mixture (262) formed by the multitude of burners (200) in a combustion reaction zone (146) in the combustion tube (144). [11] Method according to claim 10, wherein the injection of ammonia into the air stream (234) in the fuel-air mixing channel (214) downstream of the vortex arrangement (220) takes place at two different axial locations. [12] Method according to claim 10, wherein the injection of ammonia into the airflow (234) in the fuel-air mixing channel (214) downstream of the vortex arrangement (220) includes the injection of a first volume of ammonia at a first combustion chamber load and a second, larger volume of ammonia at a second, larger combustion chamber load.

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