BURNER FOR A COMBUSTION CHAMBER WITH HYDROGEN PRODUCTION FROM AMMONIA AND ASSOCIATED PROCESS

Abstract

A burner (200) for a combustion chamber (100) of a gas turbine system (90) is disclosed. The burner (200) includes an outer fuel / air premixer body (210) that mixes fuel (114A) and air (112A) for injection into a combustion chamber (172). A hydrogen-generating inner body (250) is located inside the outer fuel / air premixer body (210). The hydrogen-generating body (250) includes a hollow body (251) with a second air inlet (252) and an ammonia channel (254) within the hollow body (251). The ammonia channel (254) has an ammonia inlet (260), a heat exchanger section (262), a catalyst section (264), and an outlet (266) to the combustion chamber (172).An airflow (112C) from the second air inlet (252) in the hollow body (251) heats the heat exchanger section (262) and the catalyst section (264) to generate a hydrogen-containing stream (282) from an ammonia stream (270) therein. The hydrogen (282) exits the ammonia channel (254) and enters the combustion chamber reaction zone (201) to stabilize the combustion with ammonia and the fuel / air mixture from the outer fuel / air premixer body (210). A corresponding process is also disclosed.

Description

TECHNICAL AREA

[0001] The disclosure relates generally to turbomachine combustion chambers and in particular to a burner that produces hydrogen from ammonia, a combustion chamber enclosing 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. Current combustion chambers include a head-end fuel nozzle assembly, including a multitude of burners, for burning fuel in a (primary) combustion zone. Axial fuel stage injectors (AFS injectors) can be used to burn fuel in a separate (secondary) combustion zone downstream of the primary combustion zone. Portions of an air supply, for example from a compressor outlet, are delivered to the head-end fuel nozzle assembly and the AFS injectors via various flow channels.

[0003] One of the problems with conventional combustion chambers is that the combustion of hydrocarbons (e.g., natural gas) typically results in the formation of carbon dioxide (CO2) and nitrogen oxides (NOx), the control of which is costly. To reduce the amount of CO2 produced, some manufacturers have attempted to use alternative fuel sources, including hydrogen and ammonia, which remove carbon from the combustion products. 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 be well stabilized, 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 fuel / air premixer body with a first air inlet, a fuel inlet and a mixing channel, wherein the outer fuel / air premixer body mixes fuel and air for injection into a combustion chamber; and a hydrogen-generating inner body within the outer fuel / air premixer body, wherein the hydrogen-generating inner body comprises: a hollow body with a second air inlet;and an ammonia channel within the hollow body, wherein the ammonia channel has an ammonia inlet, a heat exchanger section downstream of the ammonia inlet, a catalyst section downstream of the heat exchanger section, and an outlet to the combustion chamber reaction zone downstream of the catalyst section, wherein an air stream from the second air inlet in the hollow body heats the heat exchanger section and the catalyst section to generate a hydrogen-containing stream from an ammonia stream contained therein, the hydrogen-containing stream exiting the combustion chamber from the outlet of the ammonia channel.

[0006] Another aspect of the disclosure includes one of the foregoing aspects, and the heat exchanger section includes one of a spiral channel or a sinusoidal channel.

[0007] Another aspect of the disclosure includes any of the foregoing aspects, and the first air inlet and the second air inlet are in fluid communication with an outlet of a compressor upstream of the burner, wherein the air entering the second air inlet has a higher temperature than the ammonia flow in the heat exchanger section.

[0008] Another aspect of the revelation includes any one of the foregoing aspects, and the ammonia stream is gaseous ammonia.

[0009] Another aspect of the disclosure includes any one of the foregoing aspects, and the outer fuel / air premixer body includes a first tube spaced concentrically from a second tube, and a swirl nozzle arrangement between the first tube and the second tube downstream of the first air inlet, the swirl nozzle arrangement including a plurality of deflecting vanes which impart a swirl to the air flowing between them, each of the deflecting vanes including an inner fuel flow channel in fluid communication with at least one fuel nozzle, the fuel inlet introducing fuel into the inner fuel flow channel.

[0010] Another aspect of the disclosure includes any one of the foregoing aspects and further comprises an end plate coupled to the hydrogen-generating inner body, the end plate being configured to allow the hydrogen-generating inner body to be removably positioned within the outer fuel / air premixer body.

[0011] Another aspect of the disclosure includes one of the foregoing aspects, and the second air inlet includes an opening in the end plate in fluid communication with a hot air source.

[0012] Another aspect of the disclosure includes one of the foregoing aspects, and the second air inlet includes an opening in the hollow body in fluid communication with the mixing channel.

[0013] Another aspect of the disclosure includes any of the foregoing aspects, and the catalyst section is replaceable.

[0014] Another aspect of the disclosure includes one of the foregoing aspects and further comprises a first channel support positioned upstream of the catalyst section to position the ammonia channel within the hollow body, and a second channel support positioned downstream of the catalyst section to position the ammonia channel within the hollow body, each channel support enclosing an open interior through which air can flow.

[0015] Another aspect of the disclosure includes a combustion chamber for a gas turbine system, the combustion chamber comprising: a combustion chamber body including a combustion tube; a head-end arrangement including a plurality of burners directed into the combustion tube, wherein at least one burner includes: an outer fuel / air premixer body with a first air inlet, a fuel inlet and a mixing channel, wherein the outer fuel / air premixer body mixes fuel and air for injection into a combustion chamber; and a hydrogen-generating inner body within the outer fuel / air premixer body, wherein the hydrogen-generating inner body comprises: a hollow body with a second air inlet;and an ammonia channel within the hollow body, wherein the ammonia channel has an ammonia inlet, a heat exchanger section downstream of the ammonia inlet, a catalyst section downstream of the heat exchanger section, and an outlet to the combustion chamber reaction zone downstream of the catalyst section, wherein an air stream from the second air inlet in the hollow body heats the heat exchanger section and the catalyst section to generate a hydrogen-containing stream from an ammonia stream contained therein, the hydrogen-containing stream exiting the combustion chamber from the outlet of the ammonia channel.

[0016] Another aspect of the disclosure includes one of the foregoing aspects, and the heat exchanger section includes one of a spiral channel or a sinusoidal channel.

[0017] Another aspect of the disclosure includes any of the foregoing aspects, and the first air inlet and the second air inlet are in fluid communication with an outlet of a compressor upstream of the burner, wherein the air entering the second air inlet has a higher temperature than the ammonia flow in the heat exchanger section.

[0018] Another aspect of the disclosure includes any one of the foregoing aspects, and the outer fuel / air premixer body includes a first tube spaced concentrically from a second tube, and a swirl nozzle arrangement between the first tube and the second tube downstream of the first air inlet, the swirl nozzle arrangement including a plurality of deflecting vanes which impart a swirl to the air flowing between them, each of the deflecting vanes including an inner fuel flow channel in fluid communication with at least one fuel nozzle, the fuel inlet introducing fuel into the inner fuel flow channel.

[0019] Another aspect of the disclosure includes any one of the foregoing aspects and further comprises an end plate coupled to the hydrogen-generating inner body, the end plate being configured to allow the hydrogen-generating inner body to be removably positioned within the outer fuel / air premixer body.

[0020] Another aspect of the disclosure includes one of the foregoing aspects, and the second air inlet includes an opening in the end plate in fluid communication with a hot air source.

[0021] Another aspect of the disclosure includes one of the foregoing aspects, and the second air inlet includes an opening in the hollow body in fluid communication with the mixing channel.

[0022] Another aspect of the disclosure includes one of the foregoing aspects and further comprises a first channel support positioned upstream of the catalyst section to position the ammonia channel inside the hollow body, and a second channel support positioned downstream of the catalyst section to position the ammonia channel inside the hollow body, each channel support enclosing an open interior space through which air can flow.

[0023] Another aspect of the disclosure includes a process comprising: in a burner for a combustion chamber of a gas turbine system: mixing air and fuel for injection into a combustion chamber of the combustion chamber in an outer fuel / air premixer body having a first air inlet, a fuel inlet and a mixing channel; and generating hydrogen for injection into the combustion chamber reaction zone in a hydrogen-generating inner body within the mixing channel of the outer fuel / air premixer body, wherein the generation of hydrogen includes heating gaseous ammonia in an ammonia channel in the hydrogen-generating body to form a hydrogen-containing stream; and injecting the hydrogen-containing stream into the combustion chamber for combustion with a fuel / air mixture from the outer fuel / air premixer body.

[0024] Another aspect of the disclosure includes any one of the foregoing aspects, and a hydrogen-generating inner body includes: a hollow body with a second air inlet; and wherein the ammonia channel is located inside the hollow body and includes an ammonia inlet, a heat exchanger section downstream of the ammonia inlet, a catalyst section downstream of the heat exchanger section, and an outlet to the combustion zone downstream of the catalyst section, wherein the heating includes passing an air stream from the second air inlet in the hollow body through the heat exchanger section and the catalyst section to generate the hydrogen from a gaseous ammonia stream contained therein, the hydrogen-containing stream exiting from the outlet of the ammonia channel for injection into the combustion chamber.

[0025] 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.

[0026] 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

[0027] These and other features of this disclosure will be better understood from the following detailed description of the various aspects of the disclosure in conjunction with the accompanying drawings, which represent different embodiments of the disclosure, in which the following applies: Fig. Figure 1 shows a functional block diagram of an illustrative gas turbine system that can be used with a combustion chamber including a burner according to embodiments of the disclosure; Fig. Figure 2 shows a side cross-sectional view of a combustion chamber including a burner according to embodiments of the disclosure; Fig. Figure 3 shows a perspective cross-sectional partial view of a burner for a combustion chamber according to embodiments of the disclosure; Fig. Figure 4 shows a cross-sectional view of a burner for a combustion chamber according to embodiments of the disclosure; Fig. Figure 5 shows a cross-sectional view of a burner for a combustion chamber according to other embodiments of the disclosure; Fig. Figure 6 shows a cross-sectional view of a hydrogen-generating internal body removed from a burner for a combustion chamber, according to embodiments of the disclosure; and Fig. Figure 7 shows a perspective view of a channel support for an ammonia channel of a hydrogen-generating inner body for a burner according to embodiments of the disclosure.

[0028] It is noted that the drawings in the revelation are not necessarily to scale. The drawings are intended only to represent typical aspects of the revelation and should therefore not be considered as limiting the scope of protection afforded by the revelation. In the drawings, identical numbers correspond to identical elements between the drawings. DETAILED DESCRIPTION

[0029] To clearly describe the present disclosure, it will be necessary to select certain terminology when referring to and describing relevant machine components within the illustrative application of a turbomachine combustion chamber and an associated burner. Where possible, industry-standard terms will be 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 appended 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 several components and, in another context, be described as consisting of such components.Alternatively, what may be described herein as including several components may elsewhere be referred to as a single part.

[0030] 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. In the sense used herein, “downstream” and “upstream” are expressions 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 burner, or the coolant through one 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.

[0031] The term "axial" refers to a movement or position parallel to an axis, such as the axis of a combustion chamber, mixing chamber, AFS injector, or turbomachine. The term "radial" refers to a movement or position perpendicular to an axis, such as the axis of a 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 combustion chamber, burner, or turbine.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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 fuel / air premixer body that mixes fuel and air for injection into a combustion chamber reaction zone within a combustion chamber body. A hydrogen-generating inner body is arranged within the outer fuel / air premixer body. The hydrogen-generating body includes a hollow body with a second air inlet and an ammonia channel within the hollow body. The ammonia channel has an ammonia inlet, a heat exchanger section, a catalyst section downstream of the heat exchanger section, and an outlet to the combustion chamber reaction zone. An airflow from the second air inlet in the hollow body heats the heat exchanger section and the catalyst section to generate hydrogen from an ammonia stream, e.g.,gaseous ammonia is used to generate a hydrogen-containing stream. The hydrogen-containing stream exits the ammonia channel into the combustion chamber reaction zone.

[0036] The hydrogen generating unit provides an efficient way to supply hydrogen (H2) for combustion using ammonia cracking. The unit can provide either a complete conversion of ammonia (NH3) to hydrogen (H2) and nitrogen (N2), or a partial conversion of ammonia to hydrogen (H2), nitrogen (N2), and ammonia (NH3). In either case, the hydrogen generating unit produces the minimum required amount of hydrogen in the hydrogen-containing stream, which comprises between 0.5% and 1% of the total fuel stream. The resulting hydrogen-containing stream is injected with air into the center of each burner, similar to pilot-ignition fuel injection.The hydrogen-containing stream improves the overall stabilization of combustion by enabling the combustion of ammonia with the fuel / air mixture from the external fuel / air premixer body and using the hydrogen to stabilize the combustion.

[0037] Fig. Figure 1 shows a functional block diagram of an illustrative gas turbine system (GT system) 90, which may include various embodiments of a combustion chamber 100 and a burner 200 of the present disclosure. As shown, the GT system 90 generally includes an inlet section 102, which may include an array of filters, cooling coils, moisture separators, and / or other devices for cleaning and otherwise conditioning air 106 entering the GT system 90. Air 106 flows to a compressor 108 in a compressor section 110, which progressively imparts kinetic energy to the air 106 to produce compressed high-pressure air (HP air) 112 (hereinafter referred to as "HP air 112" or "compressed air 112") in a high-energy state. HP air 112 is typically mixed with one or more fuels, e.g.,Fuels 114A and / or 114B from one or more fuel sources 116 are used to form a combustible mixture within at least one combustion chamber 100 in a combustion section 120, which is operationally coupled to the compressor section 110. The combustible mixture is burned to produce high-temperature, high-pressure combustion gases 122. The combustion gases 122 flow through a turbine 128 (e.g., an expansion turbine) of a turbine section 130, which is operationally coupled to the combustion section 120, to generate work. For example, the turbine 128 can be connected to a shaft 132, such that rotation of the turbine 128 drives the compressor 108 to generate high-pressure air 112. Alternatively or additionally, the shaft 132 can connect the turbine 128 to another load, such as a generator 134, to generate electricity.Exhaust gases 136 from the turbine 128 flow through an exhaust gas section 138, which connects the turbine 128 to an exhaust gas stack 140 downstream of the turbine 128. The exhaust gas section 138 can, for example, include a heat recovery steam generator (not shown) for cleaning and extracting additional heat from the exhaust gases 136 before they are released into the environment. If more than one combustion chamber 100 is used, these can be arranged circumferentially around a turbine inlet 142 of the turbine 128.

[0038] In one embodiment, the GT system 90 may include an existing propulsion machine model commercially available from GE Vernova in Cambridge, MA. The present disclosure is not limited to a particular GT system and may be implemented in conjunction with other propulsion machines, including, for example, any other HA, F, B, LM, GT, TM, and E-class propulsion machine model from GE Vernova and propulsion machine models from other companies. Furthermore, the present disclosure is not limited to a specific turbomachine and may, for example, be applicable to steam turbines, jet engines, compressors, turbofans, etc.

[0039] An illustrative combustion chamber 100, usable within the GT system 90, is now described. Fig. Figure 2 shows a cross-sectional side view of the combustion chamber 100 positioned within the GT system 90. As further described herein, the combustion chamber 100 can include a variety of burners 200 according to embodiments of the disclosure. Although an illustrative combustion chamber 100 is described herein, it is emphasized that the burner(s) 200 according to embodiments of the disclosure can be used in a wide variety of different types of combustion chambers 100. Therefore, the teachings of the disclosure are not limited to one particular combustion chamber.

[0040] As in Fig. As shown in Figure 2, the combustion chamber 100 can be at least partially surrounded by an outer casing 152, such as a compressor outlet casing and / or a turbine casing. An interior space of the outer casing 152 is in fluid communication with a compressor outlet 109 of the compressor 108 and generates a high-pressure air source 154. That is, the high-pressure air source 154 includes high-pressure air 112 from the compressor outlet 109 of the compressor 108. The high-pressure air source 154 is in direct fluid communication with a compressor outlet 109 of the GT system 90. However, the high-pressure air source 154 can be any supply of high-pressure air 112 capable of flowing into any type of opening or flow channel in the combustion chamber 100 to cool parts and / or for combustion, for example using burners 200 or axial fuel stage injectors (AFS injectors) 150.

[0041] As in Fig. As shown in Figure 2, the combustion chamber 100 for the GT system 90 includes a combustion chamber body 160. The combustion chamber body 160 can be manufactured using any currently known or subsequently developed techniques. For example, the combustion chamber body 160 can be additively manufactured. The combustion chamber body 160 can include a combustion tube 164, which may, for example, include a cylindrical section 166 and a conical transition section 168. The combustion tube 164 can have an axis A, the direction of which may vary slightly depending on its axial position within the curved combustion tube 164. The conical transition section 168 is located at a rear end (right side, as shown in Figure 2). Fig. 2 shown) of the cylindrical section 166. As is known in the field, the conical transition section 168 transfers the hot gas path (HGP) from the circular cross-section of the cylindrical section 166 of the tube to a more arcuate cross-section to match the turbine inlet 142 of the turbine 128. The combustion chamber 100 may also have a rear frame 170 at a rear end (right side in Fig. 2) include the conical transition section 168.

[0042] The combustion tube 164 can contain combustion gases 122 and lead to the turbine section 130 ( Fig. 1) transport. More precisely, the combustion tube 164 defines a combustion chamber 172, i.e., a hot gas path (HGP), within which combustion takes place. The combustion tube 164 may have a conical transition section 168 that is separate from the cylindrical section 166, as in many conventional combustion systems. Alternatively, the combustion tube 164 may have a unit body structure (or “unit body structure”) in which the cylindrical section 166 and the conical transition section 168 are integrated into one another, i.e., as part of an additively manufactured, one-piece element. Thus, any discussion of the combustion tube 164 herein is intended to include both conventional combustion systems that have separate cylindrical and conical transition sections and those combustion systems that have a unit body tube.

[0043] The combustion chamber body 160 also includes an airflow duct 174, which is defined at least partially by the cylindrical section 166 of the combustion tube 164. As described herein, the airflow duct 174 is configured to supply air (e.g., high-pressure air 112A from high-pressure air source 154) to a head-end arrangement 176 of the combustion chamber 100 at a front end (left end in Fig. 2) of the combustion tube 164. That is, it is dimensioned, shaped, and / or arranged to deliver air, such as high-pressure air 112A from high-pressure air source 154, to the head end assembly 176 of the combustion chamber 100, for example, a high-pressure distributor 220 of the head end assembly 176. The airflow channel 174 can be provided between the cylindrical section 166 and a flow sleeve 177 spaced along at least one section of an outer surface of the cylindrical section 166. The airflow channel 174 has an open end 178 or one or more airflow openings near the head end assembly 176 through which high-pressure air 112A from high-pressure air source 154 enters.

[0044] An annular partition 179, arranged between the cylindrical section 166 and the flow sleeve 177, separates a front section of the airflow channel 174 from a rear section of the airflow channel 174. The axial position of the annular partition 179 is approximately aligned with a cap arrangement 198, which is explained below, so that the front section of the airflow channel 174 is located radially outside the head end arrangement 176 (instead of the combustion chamber 172) and therefore requires less cooling. Downstream of the annular partition 179, the flow sleeve 177 can have a plurality of flame holes 192 (as shown in outer sleeve 190) that allow high-pressure air 112B to flow into the airflow channel 174. By flowing through flame holes 192, the high-pressure air 112B experiences a pressure drop and becomes low-pressure air 182, which flows through the airflow channel 174 to and / or into AFS injectors 150, as further discussed herein.

[0045] The head-end assembly 176 generally includes at least one axially extending fuel nozzle or burner 200 (hereinafter referred to as "burner 200"). As further described herein, the burner 200 directs fuel and air into a combustion chamber 172 of the combustion chamber 100. The combustion chamber 172 may include a primary combustion zone 202 in a forward section of the combustion tube 164. In certain embodiments, although not shown, axially extending burners 200 of the head-end assembly 176 may extend at least partially through the end cap assembly 198 to supply a combustible mixture of fuel 114A ( Fig. 3 to 5) and provide HD-Air 112A.

[0046] Combustion chamber body 160 optionally includes one or more axial fuel stage injectors (AFS injectors) 150 directed into the combustion tube 164 downstream of the head end assembly 176. Each AFS injector 150 receives, in addition to potentially other airflows, high-pressure air 112B from high-pressure air source 154 and fuel 114B from fuel source 116. AFS injectors 150, if provided, combust fuel 114B and high-pressure air 112B in a secondary combustion zone 204 of the combustion chamber 172 in the combustion tube 164. The fuel 114B can be supplied from fuel source 116 using any type of fuel tube(s) 188. As illustrated, combustion chamber 100 and combustion chamber body 160 can include a plurality of circumferentially spaced AFS injectors 150. Any number of AFS 150 injectors can be used.That is, AFS injector 150 can include a plurality of AFS injectors 150 spaced apart circumferentially around the combustion chamber body 160. Each AFS injector 150 extends radially through the combustion tube 164 downstream of the head-end assembly 176, which includes axially extending burners 200, as presented above and further discussed herein. While AFS injectors 150 are shown at one axial position of the combustion chamber body 160, sets of AFS injectors 150 can be provided at different axial positions of the combustion tube 164, e.g., downstream of the AFS injectors 150 (as in Figure 1). Fig. 2 shown) and upstream of the rear frame 170.

[0047] Fig. Figure 3 shows a perspective cross-sectional view, and Fig. Figure 4 shows a cross-sectional view of a burner 200 for combustion chamber 100 of the GT system 90 according to embodiments of the disclosure. Fig. Figure 5 shows a cross-sectional view of burner 200 for combustion chamber 100 of the GT system 90 according to embodiments of the disclosure.

[0048] As in Fig. 3 and Fig. As shown in Figure 4, burner 200 includes an outer fuel / air premixer body 210 (hereinafter referred to as "outer premixer body 210") with a first air inlet 212, a fuel inlet 214, and a mixing channel 216. The outer premixer body 210 mixes fuel 114A and air, e.g., high-pressure air 112A, for injection into the combustion chamber 172. Air 112A enters burner 200 from a high-pressure distributor 220 in a head-end arrangement 176 ( Fig. 2) a, which surrounds the burner 200 except for an outlet end 222 therein, which is directed into the combustion chamber 172 and may extend partially into it. Air 112A enters the high-pressure distributor 220 from the high-pressure air source 154 as described above. Air 112A for combustion enters the outer premixer body 210 via the first air inlet 212. The first air inlet 212 may include one or more openings that allow an airflow into the burner 200. For illustrative purposes, the first air inlet 212 is shown as an inlet flow conditioner (IFC) that includes an annular flow channel 224, which is bounded at the inner diameter by a solid cylindrical inner wall 226, at the outer diameter by a perforated cylindrical outer wall 228, and at the upstream end by a perforated end cap 230.Optionally, one or more annular deflector vanes 232 can be provided in the center of the flow channel 224. Air 112A for the outer premixer body 210 enters the IFC via the perforations in the end cap 230 and the cylindrical outer wall 228. As already mentioned, other air inlet shapes are also possible.

[0049] In certain embodiments, the outer premixer body 210 can include a first (outer) tube 242 spaced concentrically from a second (inner) tube 244. The outer premixer body 210 can also include a swirl nozzle assembly 234 extending radially between the first tube 242 and the second tube 244 and positioned axially downstream of the first air inlet 212. The mixing channel 216 extends through the swirl nozzle assembly 234 (i.e., between the blades of the swirl nozzle assembly 234) and can be annular in shape between the first tube 242 and the second tube 244 outside the swirl nozzle assembly 234. The second tube 244 provides a solid cylindrical inner wall 226 at the inner diameter of the IFC.

[0050] The swirl nozzle assembly 234 includes a plurality of deflecting vanes 236 that impart a vortex to the air 112A flowing between them. Each of the deflecting vanes 236 can also include an internal fuel flow channel 238, which is in fluid communication with at least one fuel injector 240. Fuel inlet 214 introduces fuel 114A into the internal fuel flow channel 238. After air 112A leaves the IFC, it enters the swirl nozzle assembly 234. Each deflecting vane 236 includes various supply channels for fuel 114A (not shown) to distribute fuel 114A, e.g., natural gas, to one or more sets of fuel injectors 240 that penetrate the wall of the aerodynamically shaped deflecting vane 236. Fuel injectors 240 can be arranged on the pressure side, the suction side or on both sides of the deflecting vanes 236.Fuel 114A begins to mix with air 112A in the swirl nozzle assembly 234, and the fuel / air mixing is completed in the mixing channel 216, which, as mentioned, can be formed between an inner surface of the first outer tube 242 and an outer surface of the second inner tube 244. The second inner tube 244 can alternatively be referred to as the vortex center extension, and the first outer tube 242 can alternatively be referred to as the vortex sheath extension. After exiting the mixing channel 216, the fuel / air mixture 284 enters the combustion chamber 172 and ignites in the primary combustion zone 202, where combustion takes place. As is known in the art, the swirl nozzle assembly 234 injects fuel 114A through the surface of the aerodynamic deflecting vanes (blade) 236, thus minimizing disturbance of the airflow field.Although a particular external fuel / air premixer body 210 has been described herein, it is emphasized that various other structures can be used to provide the fuel / air mixture 284 and are considered to be within the scope of protection of the disclosure.

[0051] With further reference to Fig. 3 and Fig. 4. The burner 200 also includes a hydrogen-generating inner body 250 within the outer premixer body 210. The hydrogen-generating inner body 250 (hereinafter referred to as "inner body 250") includes a hollow body 251 with a second air inlet 252 and an ammonia channel 254 within the hollow body 251. In particular embodiments, the second air inlet 252 can include an opening 253 in the hollow body 251, which is in fluid communication with the mixing channel 216, e.g., directly with channel 216 or with channel 216 via a swirl nozzle arrangement 234. Alternatively or additionally, the second air inlet 252 can include an opening 255 in an end plate 257, which is in fluid communication with a hot air source 259. The hot air source 259 can be any air source 112C whose temperature is sufficient to split ammonia in the ammonia channel 254, e.g. cooling exhaust air from turbine 128 or compressor exhaust air 112C.Although both forms of the second air inlet 252 are shown, only one form can be used. In certain embodiments, the first air inlet 212 and the second air inlet 252 (regardless of the form) can be in fluid communication with compressor outlet 109 of the compressor 108 upstream of the burner 200, e.g., via high-pressure distributor 220 in head assembly 176 (. Fig. 2), HP air source 154 or another fluid connection. Ammonia channel 254 includes an ammonia inlet 260, a heat exchanger section 262 downstream of the ammonia inlet 260, a catalyst section 264 downstream of the heat exchanger section 262, and an outlet 266 to the combustion chamber 172 downstream of the catalyst section 264.

[0052] As in Fig. As shown in Figure 3, ammonia 270 (see arrow) can be directed from an ammonia source 272 to the ammonia inlet 260. Ammonia 270 can be a different form of fuel, e.g., fuel 114B, and ammonia source 272 can be a different form of fuel source 116, as previously described. In certain embodiments, ammonia 270 can be in liquid form; however, this is not preferred because the temperature must remain relatively low to maintain the liquid form, e.g., less than approximately -33 °C (-28 °F). In other embodiments, the ammonia stream 270 can be gaseous or predominantly gaseous. If necessary, ammonia source 272 can include a heater 274 to enhance the conversion of ammonia 270 to a gaseous form. Heating element 274 can assume any suitable form for heating ammonia 270 into a gaseous form.

[0053] Ammonia channel 254 can include any type of conduit, such as a pipe or tubular element, capable of conveying ammonia in liquid or gaseous form. Heat exchanger section 262 can include a variety of different shapes to increase its surface area and thus enhance heat exchange between air 112C and ammonia 270. Fig. 3 and Fig. Figure 4 shows heat exchanger section 262 with a spiral channel. In this case, heat exchanger section 262 can enclose any number of spiral windings with any overall diameter within the hollow body 251. In another embodiment, shown in Fig. As shown in Figure 5, heat exchanger section 262 includes a sinusoidal channel. In this case, heat exchanger section 262 can include any number of peaks / valleys and any overall diameter within the hollow body 251. Combinations of spiral, sinusoidal, or other paths that increase the surface area of ​​the ammonia channel 254 to create heat exchanger section 262 can also be used.

[0054] Catalyst section 264 may include any currently known or subsequently developed structure that enables ammonia 270 to come into contact with a catalyst material contained therein, which is capable of splitting at least some of the ammonia 270, i.e., NH3, into its constituents hydrogen (H2) and nitrogen (N2). "Splitting," as used herein with respect to ammonia 270, means decomposing, breaking down, converting, and / or separating ammonia N3 into its constituents hydrogen (H2) and nitrogen (N2). Catalyst section 264 may include a material including, but not limited to: anodized aluminum (Al); carbon nanotube-based ruthenium (RuCNT); RuCNT with potassium hydroxide (KOH); ruthenium (Ru) and cesium (Cs); ruthenium (Ru) and aluminum oxide (Al2O3); nickel (Ni) and aluminum oxide (Al2O3); Nickel cerium oxide (Ni-CeO2) and aluminum oxide (Al2O3); nickel (Ni) and mesoporous silica; sodium (Na) and sodium amide (NaNH2).It is understood that a wide variety of other materials can also be used for cracking ammonia. The heat transfer from air 112C to ammonia 270 in the heat exchanger section 262 and catalyst section 264 is sufficient to achieve cracking by catalyst section 264. Catalyst section 264 does not need to crack all of the ammonia 270, as the required hydrogen content may only need to be between 0.5% and 1% of the total fuel stream to achieve the desired combustion stabilization, while ammonia 270 from the inner body 250, fuel / air mixture 284 from the outer premixer body 210, and any other fuel supply to the combustion chamber 172 are combusted.

[0055] In one example, a cracking process that converts more than 30% of ammonia 270 into hydrogen (H2) and nitrogen (N2) is sufficient to ensure 100% combustion, where the fuel 114A in the fuel / air mixture 284 from the outer premixer body 210 is methane (natural gas). Therefore, the hydrogen-containing stream 282 leaving the inner body 250 likely consists of less than 100% hydrogen (that is, it likely also includes ammonia in gaseous form and nitrogen). In any case, the hydrogen from the inner body 250 is sufficient to act as a pilot flame for the combustion chamber reaction zone 201 and to stabilize combustion in the primary combustion zone 202. More precisely, hydrogen from the inner body 250 reduces or prevents any exhaustion of combustion in the primary combustion zone 202 that usually occurs with ammonia injection alone.It should be noted that the amount of hydrogen can be varied according to the following factors, but not limited to them, to suit different situations: properties of ammonia 270 (e.g., pressure, volume, flow rate, etc.); properties of fuel 114A in the fuel / air mixture 284 (e.g., type, pressure, volume, flow rate, flammability, heat generation, etc.); properties of the combustion tube 164, in addition to other properties of the combustion chamber 100; properties of air 112A-C; and / or parameters of the AFS injector 150.

[0056] Outlet 266 of the ammonia channel 254 can be located at a variety of different points, depending on the desired flow and / or dispersion properties. Fig. 3 is located at outlet 266 upstream of an end 256 of the second inner tube 244, which is located upstream of an end 258 of the first outer tube 242, which adjoins the combustion chamber 172. In Fig. 4 and Fig. Outlet 266 is aligned with end 256 of the second inner tube 244 and is located axially upstream of the outlet end 222 of the burner 200, i.e., of the outer premixer body 210. The second tube 244 can have any currently known or subsequently developed shape of end 256, e.g., a constant inner diameter ( Fig. 3) or a tapered inner diameter ( Fig. 4) to generate the desired flow and / or distribution of hydrogen and ammonia from the inner body 250 into the primary combustion zone 202.

[0057] The burner 200 can also include an end plate 257 coupled to the hydrogen-generating inner body 250, for example, the hollow body 251. The end plate 257 is configured to detachably position the hydrogen-generating inner body 250 within the outer fuel / air premixer body 210. For example, the outer fuel / air premixer body 210 can include an end element 286 coupled to an end cover 196 of the combustion chamber 100 to position the burner 200 in the head end assembly 176 ( Fig. 2) to assemble. End plate 257 can be coupled to the inner body 250, which in turn can be coupled to end element 286, which, in addition to possibly other structures, with end cover 196 of the head end assembly 176 ( Fig. 2) is coupled. More precisely, end plate 257 can be coupled to at least hollow body 251. End plate 257 can include all necessary channels or openings to allow an upstream end of the ammonia channel 254 to pass through it, i.e., upstream of the heat exchanger section 262. End plate 257 can also include all necessary channels or openings to provide a second air inlet 252 and to allow air 112C to enter hollow body 251 when the second air inlet 252 is provided in end plate 257.

[0058] End plate 257 is configured to be detachably positioned (with inner body 250) in the end element 286, which secures the outer premixer body 210 in the end cover 196 of the head assembly 176 of the combustion chamber 100. The individual parts can be fastened to one another in any manner, e.g., with threaded fasteners (not shown). In this way, the burner 200 can be removed by moving end element 286 away from end cover 196 from the connection to the head assembly 176 and sliding the burner 200 out. End element 286 can optionally be coupled to end cover 196 in the head assembly 176 in any manner currently known or subsequently developed, such as, but not limited to, threaded fasteners (not shown). Furthermore, the inner body 250 can be removed from the rest of the burner 200, as shown in Fig. As shown in Figure 6, this can be achieved by removing the end plate 257 from the end element 286 and sliding the inner body 250 out. Since the service life of the catalyst section 264 is typically shorter than that of the rest of the burner 200, the catalyst section 264 is replaceable. That is, if either the inner body 250 or the burner 200 is removed from the combustion chamber 100, the catalyst section 264 can be selectively removed from the inner body 250 and, if necessary, replaced with a new version thereof. The catalyst section 264 can be detachably mounted in the inner body 250 in any currently known or subsequently developed manner, e.g., by threaded connection with one or more parts of the ammonia channel 254.

[0059] Fig. Figure 7 shows a perspective view of a channel support 285 for ammonia channel 254 of the hydrogen-generating inner body 250 for burner 200 according to embodiments of the disclosure. Any number of channel supports 285 can be used to position the ammonia channel 254 in the hollow body 251. Each channel support 285 can include any structure for holding the ammonia channel 254 in a position, e.g., a tube or another section thereof, in the hollow body 251 and an open interior 287 to allow air 112C to flow through it. The Fig. The example shown is only one possible structure capable of fulfilling this function. In the example shown, channel support 285 holds ammonia channel 254 centrally within the hollow body 251 (e.g., in the centrally located opening 288), but this is not necessary in all cases. For example, it may be advantageous to position ammonia channel 254 closer to the hollow body 251 to absorb more heat from it. Any number of channel supports 285 can be used. As shown in Fig. 6 and Fig. As shown in Figure 7, a first channel support 285A can be positioned upstream of the catalyst section 264 to position ammonia channel 254 within the hollow body 251, e.g., between catalyst section 264 and heat exchanger section 262. Furthermore, a second channel support 285B can be positioned downstream of the catalyst section 264 to position ammonia channel 254 within the hollow body 251, e.g., between catalyst section 264 and combustion reaction zone 201 and / or the end 256 of the second inner tube 244. Fig. 4).

[0060] In certain embodiments, burner 200 can include a bellows section (not shown) between hollow body 251 of the hydrogen-generating inner body 250 and the outer fuel / air premixer body 210 to compensate for different thermal expansions between hollow body 251 of the inner body 250 and the outer fuel / air premixer body 210.

[0061] A method according to embodiments of the disclosure is now described. The method is carried out in burner 200 for combustion chamber 100 of the GT system 90. The method can include mixing air 112A and fuel 114A (in fuel / air mixture 284) for injection into the combustion chamber reaction zone 201 of combustion chamber 100 in the outer fuel / air premixer body 210 with a first air inlet 212, fuel inlet 214, and mixing channel 216. After exiting the mixing channel 216, the fuel / air mixture 284 enters combustion chamber 172 for combustion in the primary combustion zone 202. The method also includes the generation of hydrogen for injection into the combustion chamber reaction zone 201 in the hydrogen-generating inner body 250 within the mixing channel 216 of the outer fuel / air premixer body 210.As described herein, hydrogen production involves heating gaseous ammonia 270 in ammonia channel 254 within the hydrogen-generating body 250 to produce a hydrogen-containing stream 282. More precisely, the heating involves passing an air stream 112C from the second air inlet 252 in the hollow body 251 over heat exchanger section 262 and catalyst section 264 to generate the hydrogen from the gaseous ammonia stream 270 contained therein. The air 112C transfers heat to the heat exchanger section 262 and catalyst section 264 as it flows over and within the hollow body 251. The air 112C entering the second air inlet 252 has a higher temperature than the ammonia stream 270 in the heat exchanger section 262. The heat transferred to ammonia 270 generates a hydrogen-containing stream 282 from ammonia 270, which flows in the ammonia channel 254.

[0062] In particular, the additional heat can cause ammonia 270 to reach temperatures in a range of, for example, 287 to 593 °C (550 to 1100 °F). The additional heat increases the efficiency of the catalyst section 264 to split at least some of the ammonia 270 into its components hydrogen (H2) and nitrogen (N2). The process also includes injecting a hydrogen-containing stream 282 into the combustion reaction zone 201 for combustion with at least one fuel / air mixture 284 from the outer premixer body 210. More precisely, the resulting hydrogen-containing stream 282 (including any undiluted ammonia) exits from outlet 266 of the ammonia channel 254 and enters the combustion chamber 172 for combustion in the primary combustion zone 202 with at least the fuel / air mixture 284 from the outer premixer body 210.The procedure can also include removing the inner body 250 and replacing the catalyst section 264.

[0063] The burner 200, including the outer premixer body 210 and inner body 250, can be made of any currently known or future developed combustion-tolerant and oxidation-resistant material. The material can be metal and can be a pure metal or an alloy. The burner 200, including the outer premixer body 210 and inner body 250, can incorporate a metal commonly used in turbine components, such as turbine blades or nozzles, which has a higher temperature and oxidation tolerance than materials commonly used for combustion system parts.In this case, the second material may include a non-reactive metal produced 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) (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.

[0064] In certain embodiments, burners 200 and / or parts thereof, e.g., outer premixer body 210, swirl nozzle assembly 234, inner body 250, etc., can be additively manufactured using any currently known or subsequently developed technique capable of forming an integral body. As a result, the various parts can comprise a multitude of parallel, sintered metal layers.

[0065] As in Fig. As shown in Figure 2, embodiments of the disclosure may also include combustion chamber 100 for GT system 90. The combustion chamber 100 includes a combustion chamber body 160 including a combustion tube 164. The combustion chamber 100 also includes a head-end arrangement 176 including a plurality of burners 200 directed into the combustion tube 164. The burners 200 may be arranged in any desired manner, such as in a circular pattern, but are not limited to this. Each burner 200 may be as described herein and is directed into the combustion tube 164. The combustion chamber 100 generally terminates at a point adjacent to a first stage 290 of stationary nozzles 292 of the turbine 128. The first stage 290 of the stationary nozzles 292 defines at least partially the turbine inlet 142 to the turbine 128. Combustion chamber body 160, i.e.,Combustion tube 164 defines at least partially a hot gas path (HGP) for directing combustion gases 122 from combustion chamber 172, i.e. the primary combustion zone 202 and the secondary combustion zone 204, to turbine inlet 142 of turbine 128 during operation of the GT system 90.

[0066] Furthermore, embodiments of the disclosure may, as in Fig.Figure 1 shows GT system 90, which includes compressor section 110, combustion section 120, which is operationally coupled to compressor section 110, and turbine section 130, which is operationally coupled to combustion section 120. As described herein, combustion section 120 includes at least one combustion chamber 100, which includes combustion chamber body 160 including combustion tube 164, and the head-end fuel nozzle assembly 176 at a front end of combustion chamber body 160. Head-end assembly 176 includes a plurality of burners 200 directed into combustion tube 164, as described herein.

[0067] The disclosure provides various technical and commercial advantages, examples of which are discussed herein. Embodiments of the disclosure provide an efficient way to combust ammonia without combustion exhaustion / blowout across all operating conditions, whereby a small portion of the ammonia is split for stable combustion. The hydrogen-generating body provides an efficient way to utilize the splitting of ammonia to provide hydrogen (H2) for combustion with ammonia. The hydrogen-generating body can provide a complete conversion of ammonia (NH3) to hydrogen (H2) and nitrogen (N2), or a partial conversion of ammonia to hydrogen (H2), nitrogen (N2), and ammonia (NH3). In either case, the hydrogen-generating body produces the minimum required hydrogen-containing stream, such that it is between 0.5% and 1% of the total fuel stream.The resulting hydrogen-containing stream is injected into the center of each burner along with air, similar to pilot injection. Therefore, the hydrogen-containing stream can be injected at any desired aerodynamic stabilization point to improve the overall stabilization of the gas turbine combustion, for example, with the fuel / air mixture from the external fuel / air premixer body.

[0068] 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 used to measure the value. Here, and throughout this patent specification 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”, referring to a particular 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.

[0069] 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 (100) of a gas turbine system (90), wherein the burner comprises: an external fuel / air premixer body (210) with a first air inlet (212), a fuel inlet (214) and a mixing channel (216), wherein the outer fuel / air premixer body (210) mixes fuel (114A) and air (112A) for injection into a combustion chamber (172) with a combustion chamber reaction zone (201); and a hydrogen-generating inner body (250) within the outer fuel / air premixer body (210), wherein the hydrogen-generating inner body (250) includes: a hollow body (251) with a second air inlet (252); and an ammonia channel (254) within the hollow body (251), wherein the ammonia channel (254) has an ammonia inlet (260), a heat exchanger section (262) downstream of the ammonia inlet (260), has a catalyst section (264) downstream of the heat exchanger section (262) and an outlet (266) to the combustion chamber reaction zone (201) downstream of the catalyst section (264), wherein an airflow (112C) from the second air inlet (252) in the hollow body (261) heats the heat exchanger section (262) and the catalyst section (264) to generate a hydrogen-containing stream (282) from an ammonia stream (270) therein, the hydrogen-containing stream (282) exiting the ammonia channel (265) from the outlet (266) into the combustion chamber (172). [2] Burner (200) according to claim 1, wherein the heat exchanger section (262) includes a spiral or sinusoidal channel. [3] Burner (200) according to claim 1, wherein the first air inlet (212) and the second air inlet (252) are in fluid communication with an outlet (109) of a compressor (108) upstream of the burner (200), wherein the air (112C) entering the second air inlet (252) has a higher temperature than the ammonia flow (270) in the heat exchanger section (262). [4] Burner (200) according to claim 1, wherein the ammonia stream (270) is gaseous ammonia. [5] Burner (200) according to claim 1, wherein the outer fuel / air premixer body (210) includes a first tube (242) spaced concentrically from a second tube (244) and a swirl nozzle arrangement (234) between the first tube (242) and the second tube (244) downstream of the first air inlet (212), wherein the swirl nozzle arrangement (234) includes a plurality of deflecting vanes (236) which impart a swirl to the air (112A) flowing between them, wherein each of the deflecting vanes (236) includes an inner fuel flow channel (238) in fluid communication with at least one fuel injector, wherein the fuel inlet (214) introduces fuel into the inner fuel flow channel (238). [6] Burner (200) according to claim 1, further comprising an end plate (257) coupled to the hydrogen-generating inner body (250), wherein the end plate (257) is configured so that the hydrogen-generating inner body (250) can be removably positioned within the outer fuel / air premixer body (210). [7] Burner (200) according to claim 6, wherein the second air inlet (252) includes an opening (255) in the end plate (257) which is in fluid communication with a hot air source (259). [8] Burner (200) according to claim 1, wherein the second air inlet (252) includes an opening (253) in the hollow body (251) which is in fluid communication with the mixing channel (216). [9] Burner (200) according to claim 1, wherein the catalyst section (264) is replaceable. [10] Burner (200) according to claim 1, further comprising a first channel support (285A) positioned upstream of the catalyst section (264) to position the ammonia channel (254) inside the hollow body (251), and a second channel support (285B) positioned downstream of the catalyst section (264) to position the ammonia channel (254) inside the hollow body (251), each channel support (285A, 285B) enclosing an open interior (287) to allow air (112C) to flow through it. [11] Combustion chamber (100) for a gas turbine system (90), the combustion chamber (100) comprising: a combustion chamber body (160) enclosing a combustion tube (164); a head end arrangement (176) including a plurality of burners (200) directed into the combustion tube (164), wherein at least one burner (200) is defined according to any one of claims 1 to 10. [12] Procedures, including: in a burner (200) for a combustion chamber (100) of a gas turbine system (90), wherein the burner (200) is defined according to any one of claims 1 to 10: Mixing air (112A) and fuel (114A) for injection into a combustion chamber (172) of the combustion chamber (100) in an external fuel / air premixer body (210) with a first air inlet (212), a fuel inlet (214) and a mixing channel (216); and Generating hydrogen for injection into a combustion chamber reaction zone (201) in a hydrogen-generating inner body (250) within the mixing channel (216) of the outer fuel / air premixer body (210), wherein the hydrogen generation step includes heating gaseous ammonia (270) in an ammonia channel (254) in the hydrogen-generating body (260) to form a hydrogen-containing stream (282); and Injection of the hydrogen-containing stream (282) into the combustion chamber reaction zone (201) for combustion with a fuel / air mixture (284) from the outer fuel / air premixer body (210). [13] Method according to claim 12, wherein a hydrogen-generating inner body (250) includes: a hollow body (251) with a second air inlet (252); and wherein the ammonia channel (254) is located inside the hollow body (251) and includes an ammonia inlet (260), a heat exchanger section (262) downstream of the ammonia inlet (260), a catalyst section (264) downstream of the heat exchanger section (262) and an outlet (266) to the combustion chamber reaction zone (201) downstream of the catalyst section (264), wherein the heating step includes directing an airflow (259) from the second air inlet (252) in the hollow body (251) via the heat exchanger section (262) and the catalyst section (264) to generate the hydrogen-containing stream (282) from the gaseous ammonia stream (270) contained therein, wherein the hydrogen-containing stream (282) exits from the outlet of the ammonia channel (254) to be injected into the combustion chamber reaction zone (201).

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