Heat exchanger and related method for a combustor that heats an ammonia stream

Abstract

The present invention provides a heat exchanger and related methods for a combustor that heats an ammonia flow. [Solution] The combustor (100) includes a head end assembly (176) having a heat exchanger (210), and a cap assembly (198) having a primary burner (200) directed into a combustion liner to form a primary combustion zone (202) inside. The heat exchanger includes a body (220) having a first end (242) defining an ammonia inlet (240), a second end (224) extending from the cap assembly into the primary combustion zone, and an outlet end defined in front of the cap assembly. The body defines an ammonia heat exchange passage (214) extending toward the second end and returning from the second end of the heat exchanger to the outlet end. The heat exchanger heats an ammonia stream (212) transported through the ammonia heat exchange passage, converting the ammonia from a liquid state (216) to a gaseous state (218).

Description

Technical Field

[0001] The present invention generally relates to gas turbine system combustors, and more specifically to heat exchangers for combustors for heating a flow of ammonia, combustors including the heat exchangers, and related methods.

Background Art

[0002] A gas turbine system includes a combustion section that includes a plurality of combustors, and the combustors generate a flow of combustion gas in which fuel burns and is converted to kinetic energy in a downstream turbine section. Current combustors include a head end assembly that includes a plurality of burners for burning fuel in a (primary) combustion zone. Axial fuel stage (AFS) injectors can be used to burn fuel in another (secondary) combustion zone downstream of the primary combustion zone. For example, a portion of the air supply from the compressor discharge is sent to the head end assembly and the AFS injectors within various flow paths.

[0003] One problem with conventional combustors is that the combustion of hydrocarbons (e.g., natural gas) generally results in the formation of costly-to-mitigate carbon dioxide (CO2) and nitrogen oxides (NOx). To reduce the amount of CO2 produced, some manufacturers have attempted to use alternative fuel sources that include hydrogen and / or ammonia to remove carbon from the combustion products. However, heating ammonia to a gaseous state can have challenges associated with using ammonia as a fuel. In particular, ammonia has low flammability, a low heat of combustion, is not very stable, and can potentially extinguish at least a portion of the combustion reaction.

Summary of the Invention

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

[0005] One aspect of the present disclosure includes a heat exchanger for a combustor of a gas turbine system, the combustor comprising: a combustor body having a combustion liner; a head end assembly comprising: a cap assembly; a plurality of primary burners disposed within the cap assembly and led into the combustion liner, each primary burner configured to mix a first fuel with a first airflow and lead the first fuel / air mixture into a primary combustion zone in the combustion liner; and a heat exchanger comprising: a body having a first end defining an ammonia inlet; a second end extending from the cap assembly into a defined primary combustion zone in the combustion liner; and an outlet end in front of the cap assembly, wherein the heat exchanger defines an ammonia heat exchange passage extending toward the second end and returning from the second end of the heat exchanger to the outlet end, and the heat exchanger is configured to heat a flow of ammonia transported through the ammonia heat exchange passage and convert the ammonia from a liquid state to a gaseous state.

[0006] Another aspect of the present disclosure includes any of the preceding aspects, wherein the ammonia heat exchange passage includes an ammonia inlet at a first end of the body; a first sub-passage fluidly communicating with the ammonia inlet, through which ammonia flows in a first direction to a second end in the primary combustion zone; and a second return sub-passage fluidly communicating with the first sub-passage, through which ammonia flows from the second end out of the primary combustion zone in a second direction to a fuel plenum, and the fuel plenum directs the ammonia to a plurality of primary burners.

[0007] Another aspect of the present disclosure includes any of the preceding aspects, wherein a first sub-passage is defined by a first conduit that is in fluid communication with an ammonia inlet at a first end of a body, which is concentrically arranged in a second larger conduit having a closed end within a primary combustion zone; a second return sub-passage is defined by an open space between the first and second conduits; and the first conduit has an end having at least one opening that fluidly connects the first and second sub-passages.

[0008] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the second sub-passage includes an annular portion.

[0009] Another aspect of the present disclosure includes any of the preceding aspects, further comprising a secondary burner located within a central opening of the main body and thermally communicating with an ammonia heat exchange passage, thereby allowing a flow of ammonia transported through the ammonia heat exchange passage to cool the secondary burner.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, wherein the body includes an outer heat shield, an inner heat exchange member within the outer heat shield, a partition wall in the space between the outer heat shield and the inner heat exchange member, and an end wall connecting the outer heat shield and the inner heat exchange member, the partition wall defining spaces to a first and a second sub-passage.

[0011] Another aspect of the present disclosure includes any of the preceding aspects, wherein the secondary burner comprises a fuel-air mixture passage defined by the interior of an internal heat exchange member, and a swozle assembly disposed within the fuel-air mixture passage, the swozle assembly comprising a plurality of swirling vanes that give swirl to a second airflow flowing through the fuel-air mixture passage, each of which comprises an internal fuel passage in fluid communication with at least one fuel injector, and a fuel passage that introduces a second fuel into the internal fuel passage, the second fuel / air mixture being generated by the swozle assembly and directed to the primary combustion zone of a combustion liner.

[0012] Another aspect of the present disclosure includes any of the preceding aspects, wherein the outlet end of the fuel-air mixture passage of the secondary burner is located further within the combustion liner than the outlet ends of the multiple primary burners.

[0013] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the first and second auxiliary passages each include an annular portion.

[0014] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the first sub-passage and the second sub-passage each include a plurality of fluid-coupled passages.

[0015] Another aspect of the present disclosure includes a combustor for a gas turbine, the combustor comprising: a combustor body including a combustion liner; a head end assembly comprising: a plurality of primary burners disposed within the cap assembly and led into the combustion liner, each primary burner configured to mix a first fuel with a first airflow and lead the first fuel / air mixture into a primary combustion zone defined within the combustion liner; and a heat exchanger having a body having a first end defining an ammonia inlet, a second end extending beyond the cap assembly into a primary combustion zone defined within the combustion liner, and an outlet end forward of the cap assembly, wherein the body extends toward the second end and defines an ammonia heat exchange passage returning from the second end of the heat exchanger to the outlet end, and the body is configured to heat the flow of ammonia transported through the ammonia heat exchange passage and convert the ammonia from a liquid state to a gaseous state.

[0016] Another aspect of the present disclosure includes any of the preceding aspects, wherein the ammonia heat exchange passage includes an ammonia inlet at a first end of the body; a first sub-passage fluidly communicating with the ammonia inlet, through which ammonia flows to a second end in the primary combustion zone; and a second return sub-passage fluidly communicating with the first sub-passage, through which ammonia flows from the second end out of the primary combustion zone to a fuel plenum, the fuel plenum then directs the ammonia to a plurality of primary burners.

[0017] Another aspect of the present disclosure includes any of the preceding aspects, wherein a first sub-passage is defined by a first conduit that is in fluid communication with an ammonia inlet at a first end of a body, which is concentrically arranged in a second larger conduit having a closed end within a primary combustion zone; a second return sub-passage is defined by an open space between the first and second conduits; and the first conduit has an end having at least one opening that fluidly connects the first and second sub-passages.

[0018] Another aspect of the present disclosure includes any of the preceding aspects, further comprising a secondary burner located within a central opening of the main body and thermally communicating with an ammonia heat exchange passage, thereby allowing a flow of ammonia transported through the ammonia heat exchange passage to cool the secondary burner.

[0019] Another aspect of the present disclosure includes any of the preceding aspects, wherein the body includes an outer heat shield, an inner heat exchange member within the outer heat shield, a partition wall in the space between the outer heat shield and the inner heat exchange member, and an end wall connecting the outer heat shield and the inner heat exchange member, the partition wall defining the space into a first sub-passage and a second sub-passage.

[0020] Another aspect of the present disclosure includes any of the preceding aspects, wherein the secondary burner comprises a fuel-air mixture passage defined by the interior of an internal heat exchange member, and a swozle assembly disposed within the fuel-air mixture passage, the swozle assembly comprising a plurality of swirling vanes that give swirl to a second airflow flowing through the fuel-air mixture passage, each of which comprises an internal fuel passage in fluid communication with at least one fuel injector, and a fuel passage that introduces a second fuel into the internal fuel passage, the second fuel / air mixture being generated by the swozle assembly and directed to a primary combustion zone defined within a combustion liner.

[0021] Another aspect of the present disclosure includes any of the preceding aspects, wherein the outlet end of the fuel-air mixture passage of the secondary burner is located further within the combustion liner than the outlet ends of the multiple primary burners.

[0022] Another aspect of the present disclosure includes any of the preceding aspects and further comprises a fuel plenum that is in fluid communication with the outlet of an ammonia heat exchange passage and in fluid communication with the ammonia inlet of each of a plurality of primary burners, each primary burner being further configured to receive ammonia in a gaseous state as a first fuel, mix the ammonia in a gaseous state with a first airflow, and direct the ammonia / air mixture as a first fuel / air mixture into a primary combustion zone defined within a combustion liner.

[0023] Another aspect of the present disclosure includes a method for operating a combustor in a gas turbine system, the combustor comprising: a combustor body including a combustion liner; a head end assembly comprising: a cap assembly; a plurality of primary burners disposed within the cap assembly and led into the combustion liner, each primary burner configured to mix a first fuel with a first airflow and lead the first fuel / air mixture into a primary combustion zone defined within the combustion liner, wherein the method burns the fuel / air mixture formed by the plurality of primary burners within the primary combustion zone of the combustion liner. The invention involves transporting a flow of ammonia through an ammonia heat exchange passage defined within a heat exchanger to convert ammonia from a liquid state to a gaseous state, wherein the heat exchanger includes a body having a first end defining an ammonia inlet, a second end extending beyond a cap assembly into a primary combustion zone defined within a combustion liner, and an outlet end defined in front of the cap assembly, the ammonia heat exchange passage extending into the second end and returning from the second end of the heat exchanger to the outlet end, the outlet end being in fluid communication with a fuel plenum that leads gaseous ammonia to a plurality of primary burners.

[0024] Another aspect of the present disclosure includes any of the preceding aspects, further comprising a secondary burner located within a central opening of the body of a heat exchanger and thermally communicating with an ammonia heat exchange passage, and further comprising cooling the secondary burner using a flow of ammonia transported through the ammonia heat exchange passage.

[0025] Two or more embodiments described in this disclosure, including those described in this summary section, can be combined to form implementations not specifically described herein. That is, all embodiments described herein can be combined with one another.

[0026] Details of one or more implementations are described in the accompanying drawings and the following description. Other features, purposes, and advantages will become apparent from the description and drawings, as well as the claims.

[0027] These features of the present disclosure and other features will be more readily understood by considering the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings showing various embodiments of the present disclosure.

Brief Description of the Drawings

[0028] [Figure 1] FIG. 1 is a functional block diagram of an exemplary gas turbine system that can be used with a combustor including a heat exchanger according to an embodiment of the present disclosure. [Figure 2] FIG. 2 is a cross-sectional side view of a combustor including a heat exchanger according to an embodiment of the present disclosure. [Figure 3] FIG. 3 is a cross-sectional view of a heat exchanger for a combustor according to an embodiment of the present disclosure. [Figure 4] FIG. 4 is a partial cross-sectional perspective view of a heat exchanger for a combustor according to an embodiment of the present disclosure. [Figure 5] FIG. 5 is a cross-sectional end view of the heat exchanger along line A-A of FIG. 3. [Figure 6] FIG. 6 is an end view of a heat exchanger for a combustor according to another embodiment of the present disclosure. [Figure 7] FIG. 7 is an end view of a heat exchanger for a combustor according to an additional embodiment of the present disclosure. [Figure 8] FIG. 8 is a cross-sectional view of a heat exchanger having a burner for a combustor according to another embodiment of the present disclosure. [Figure 9] FIG. 9 is a partial cross-sectional perspective view of a heat exchanger having a burner for a combustor according to another embodiment of the present disclosure.

Modes for Carrying Out the Invention

[0029] Note that the drawings of the present disclosure are not necessarily drawn to scale. The drawings are intended to illustrate only typical aspects of the present disclosure and should not be considered as limiting the scope of the present disclosure. In the drawings, the same reference numerals represent similar elements among the drawings.

[0030] As a first issue, in order to clearly describe this disclosure, it is necessary to select specific terminology when referring to and describing relevant mechanical components within exemplary applications of turbomechanical combustors and associated heat exchangers therefor. Where this is done, common industrial terminology is used and adopted in a manner consistent with its accepted meaning, whenever possible. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that, in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single component may also be included in and referred to in another context as consisting of multiple components. Conversely, what may be described herein as consisting of multiple components may be referred to elsewhere as a single component.

[0031] Furthermore, this specification may use several descriptive terms, and it will be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise specified: As used herein, “downstream” and “upstream” are terms indicating direction relative to the flow of a working fluid through the combustor of a turbomachinery, or a fluid such as a flow of air or ammonia through the combustor or heat exchanger, or a coolant through one of the component systems of a turbomachinery. The term “downstream” corresponds to the direction of the fluid flow, and the term “upstream” refers to the direction opposite to the flow. The terms “forward” and “rear” refer to directions unless otherwise specified, with “forward” referring to the front of the turbomachinery or combustor or the compressor end, and “rear” referring to the rear of the turbomachinery or combustor or the turbine end.

[0032] The term “axial” refers to movement or position parallel to an axis, for example, the axis of a heat exchanger, burner, combustor, or turbomachinery. The term “radial” refers to movement or position perpendicular to an axis, for example, the axis of a heat exchanger, burner, combustor, or turbomachinery. In such cases, if the first component is located closer to the axis than the second component, this specification states that the first component is “radially inward” or “inward” of the second component. On the other hand, if the first component is located further from the axis than the second component, this specification may state that the first component is “radially outward” or “outward” of the second component. Finally, the term “circumferential” refers to movement or position around an axis, for example, the circumferential inner surface of a combustor body, or the circumferential interior of a casing extending around a combustor. As described above, depending on the context, it will be understood that such terms may be applied to the axis of a heat exchanger, burner, combustor, or turbine.

[0033] In addition, several descriptive terms may be used repeatedly in this specification, as described below. The terms “first,” “second,” and “third” may be used interchangeably to distinguish any component from another component and are not intended to indicate the location or importance of any individual component.

[0034] The terms used herein are intended solely to describe specific embodiments and are not intended to limit the disclosure. Where used herein, the singular forms “a,” “an,” and “the” are intended to include the plural unless otherwise explicitly indicated by the context. Where used herein, the terms “comprise” and / or “comprising” express the existence of the described features, integers, steps, actions, elements, and / or components, but do not exclude the existence or addition of one or more other features, integers, steps, actions, elements, components, and / or sets thereof. “Optional” or “optionally” means that the events described later may or may not occur, or the features described later may or may not exist, and this statement includes both instances in which the events occur or the features exist, and instances in which the events do not occur or the features do not exist.

[0035] When any element or layer is referred to as “on top of,” “engaged with,” “connected to,” “joined,” or “attached” to another element or layer, it may be directly on top of, connected to, joined to, or attached to the other element or layer, and there may be an intervening element or layer. Conversely, when any element is referred to as “directly on top of,” “directly engaged to,” “directly connected to,” or “directly joined to” another element or layer, there is no intervening element or layer. Other words used to describe relationships between elements should be interpreted similarly (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any combination of one or more of the related enumerated items. The verb forms “join” and “attach” may be used interchangeably herein.

[0036] Embodiments of the present disclosure provide a heat exchanger for a combustor, a combustor including a heat exchanger, and related methods. The combustor includes a combustor body having a combustion liner, a cap assembly, and a head end assembly having a plurality of primary burners located within the cap assembly and directed into the combustion liner. Each primary burner is configured to mix a first fuel with a first airflow and direct the first fuel / air mixture into a primary combustion zone in the combustion liner. The heat exchanger includes a body having a first end located within the cap assembly and a second end extending from the cap assembly into the primary combustion zone in the combustion liner. The body defines an ammonia (NH3) heat exchange passage extending toward the second end and returning from the second end of the heat exchanger. The heat exchanger is configured to heat the flow of ammonia transported through the ammonia heat exchange passage, converting the ammonia from a liquid state to a gaseous state. The gaseous ammonia can be used elsewhere in the combustor, for example, in the primary burner as fuel for a combustion reaction. The heat exchanger does not require a separate ammonia evaporator outside the combustor. The heat exchanger can also act as a flame stabilizer through a recirculation zone within the primary combustion zone. In another embodiment, a secondary burner is located within the heat exchanger, and the ammonia flow also cools the secondary burner. Cooling the secondary burner extends the burner's lifespan.

[0037] Figure 1 shows a functional block diagram of an exemplary gas turbine (GT) system 90 that may incorporate various embodiments of the combustor 100 and heat exchanger 210 (Figure 2-9) of the present disclosure. As shown, the GT system 90 generally includes an inlet section 102 which may include a series of filters, cooling coils, moisture separators, and / or other devices for purifying and otherwise conditioning the air 106 entering the GT system 90. The air 106 flows to a compressor 108 in a compressor section 110, which gradually imparts kinetic energy to the air 106 to produce high-pressure (HP) air 112 (hereinafter, "HP air 112" or "compressed air 112") compressed in a high-energy state. HP air 112 is typically mixed with one or more fuels from a fuel source 116, e.g., gaseous ammonia 114A, fuel 114B, and / or fuel 114C, to form a combustible mixture in at least one combustor 100 within a combustion section 120 operably coupled to a compressor section 110. The combustible mixture ignites to produce high-temperature, high-pressure combustion gases 122. The combustion gases 122 flow through a turbine 128 (e.g., an expansion turbine) in a turbine section 130 operably coupled to the combustion section 120, and do work. For example, the turbine 128 may be connected to a shaft 132 so that the rotation of the turbine 128 drives a compressor 108 to produce HP air 112. Alternatively or additionally, the shaft 132 may connect the turbine 128 to another load, such as a generator 134 for generating electricity. Exhaust gases 136 from the turbine 128 flow through an exhaust section 138 that connects the turbine 128 to an exhaust stack 140 downstream of the turbine 128. The exhaust section 138 may include, for example, a heat recovery boiler ("HRSG", not shown) for purifying and extracting additional heat from the exhaust gases 136 before they are released into the environment. If multiple combustors 100 are used, they may be spaced circumferentially around the turbine inlet 142 of the turbine 128.

[0038] In one embodiment, the GT system 90 may be applicable to engine models commercially available from GE Vernova in Cambridge, Massachusetts. This disclosure is not limited to any one specific GT system, and may be adapted to any HA, F, B, LM, GT, TM, and E-class engine models from GE Vernova, as well as other engine-related systems, including engine models from other companies. Furthermore, this disclosure is not limited to specific turbomachinery, and is applicable to, for example, steam turbines, jet engines, compressors, turbofans, and the like.

[0039] Next, a combustor 100 that can be used within the GT system 90 will be described. Figure 2 shows a cross-sectional side view of a combustor 100 positioned within the GT system 90. As will be further described herein, the combustor 100 may include a heat exchanger 210 according to embodiments of the present disclosure. While an exemplary combustor 100 is described herein, it is important to emphasize that the heat exchanger 210 according to embodiments of the present disclosure can be used in a wide variety of different types of combustors 100. Therefore, the teachings of the present disclosure are not limited to any particular combustor.

[0040] As shown in Figure 2, the combustor 100 is at least partially enclosed by an outer casing 152, such as a compressor discharge casing and / or a turbine casing. The interior of the outer casing 152 is in fluid communication with the compressor discharge 109 of the compressor 108, forming an HP air source 154. That is, the HP air source 154 contains HP air 112 from the compressor discharge of the compressor 108. The HP air source 154 is in direct fluid communication with the compressor discharge 109 of the GT system 90. However, the HP air source 154 may be any source of HP air 112 that can flow into any various openings or passages of the combustor 100 for cooling and / or combustion of components, i.e., using a primary burner 200 or an axial fuel stage (AFS) injector 150.

[0041] As shown in Figure 2, the combustor 100 for the GT system 90 includes a combustor body 160. The combustor body 160 may be fabricated using any currently known or hereafter developed technique. For example, the combustor body 160 may be additively fabricated. The combustor body 160 may include a combustion liner 164, which may include, for example, a cylindrical portion 166 and a tapered transition portion 168. The combustion liner 164 may have an axis A, the direction of which may vary slightly depending on its axial position within the curved combustion liner 164. The tapered transition portion 168 is located at the rear end of the cylindrical portion 166 (on the right in Figure 2). As understood in the art, the tapered transition portion 168 transitions the high-temperature gas path (HGP) from the circular cross section of the cylindrical portion 166 of the liner to an arc-shaped cross section for mating with the turbine inlet 142 of the turbine 128. The combustor 100 may also include a rear frame 170 at the rear end of the tapered transition section 168 (right side in Figure 2).

[0042] The combustion liner 164 can contain the combustion gas 122 and transport it to the turbine section 130 (Figure 1). More specifically, the combustion liner 164 defines the combustion chamber 172, i.e., the high-temperature gas path (HGP) in which combustion occurs. The combustion liner 164 may have a separate tapered transition section 168 from the cylindrical section 166, as in many conventional combustion systems. Alternatively, the combustion liner 164 may have a unibody structure in which the cylindrical section 166 and the tapered transition section 168 are integrated with each other, i.e., as part of an additively manufactured, integrated component. Therefore, any description of the combustion liner 164 in this specification is intended to encompass both conventional combustion systems having separate cylindrical and tapered transition sections and combustion systems having a unibody liner.

[0043] The combustor body 160 also includes an air passage 174, at least partially defined by the cylindrical portion 166 of the combustion liner 164. As described herein, the air passage 174 is configured at the front end (left end in Figure 2) of the combustion liner 164 to deliver air (e.g., HP air 112A from the HP air source 154) to the head end assembly 176 of the combustor 100. That is, it is sized, shaped, and / or arranged to deliver air, such as HP air 112A from the HP air source 154, to the head end assembly 176 of the combustor 100, i.e., to the high-pressure plenum 222 of the head end assembly 176. The air passage 174 may be defined between the cylindrical portion 166 and a flow sleeve 177 spaced apart along at least a portion of the outer surface of the cylindrical portion 166. The air passage 174 has an open end 178 or an air flow opening upstream (upstream of the combustor 100) of any AFS injector 150 into which HP air 112A from the HP air source 154 enters.

[0044] An annular partition 179 positioned between the cylindrical section 166 and the flow sleeve 177 separates the front portion of the air passage 174 from the rear portion. The axial position of the annular partition 179 is substantially aligned with the cap assembly 198, described later, so that the front portion of the air passage 174 is radially outward of the head end assembly 176 (rather than the combustion chamber 172) and therefore requires less cooling. Behind the annular partition 179, the flow sleeve 177 may include a number of impingement holes 192 (shown in the outer sleeve 190) through which HP air 112B can flow into the air passage 174. As a result of passing through the impingement holes 192, the HP air 112B undergoes a pressure drop and becomes LP air 182, which flows through the air passage 174 toward and / or into one or more axial fuel stage (AFS) injectors 150, as described further herein.

[0045] The combustor body 160 also optionally includes one or more AFS injectors 150 directed into the combustion liner 164 downstream of the head end assembly 176. Each AFS injector 150 receives HP air 112B from the HP air source 154 and fuel 114B from the fuel source 116, possibly in other airflows as well. The AFS injectors 150 burn the fuel 114B and HP air 112B in the secondary combustion zone 204 of the combustion chamber 172 within the combustion liner 164, if provided. The fuel 114B may be delivered from the fuel source 116 using any form of fuel line 188. As shown, the combustor 100 and combustor body 160 may include a plurality of circumferentially spaced AFS injectors 150. Any number of AFS injectors 150 can be used. In other words, the AFS injector 150 may include a plurality of AFS injectors 150 spaced circumferentially around the combustor body 160. Each AFS injector 150 extends radially through the combustion liner 164 downstream of the head end assembly 176, which includes an axially extending primary burner 200, as will be further described below. Although the AFS injectors 150 are shown in axial positions on the combustor body 160, sets of AFS injectors 150 may be located in different axial positions on the combustion liner 164, for example, downstream of the AFS injectors 150 and upstream of the rear frame 170 (as shown in Figure 2).

[0046] The combustor 100 also includes a plurality of primary burners 200 arranged within the cap assembly 198 and directed into the combustion liner 164. More specifically, the head end assembly 176 includes a plurality of axially extending fuel nozzles or burners 200 (hereinafter, "primary burners 200"). The primary burners 200 may include any currently known or future-developed combustor burners. The primary burners 200 may include mounting flanges 197 for attaching the burners 200 to the end cover 196 in the head end assembly 176 (as shown in Figure 2). Alternatively, although not shown, the primary burners 200 can be attached to the cap assembly 198. The primary burners 200 can be arranged in any manner within the head end assembly 176, for example, in a spaced circular pattern. Each primary burner 200 is configured to mix gaseous ammonia 114A (fuel 114A), or its components hydrogen and nitrogen, into a flow of first air 112A, and to direct the fuel / air mixture 206 to the primary combustion zone 202 of the combustion liner 164. The combustion chamber 172 may include the primary combustion zone 202 within the combustion liner 164. In certain embodiments, although not shown, a primary burner 200 extending axially from the head end assembly 176 may extend at least partially through the cap assembly 198 and supply a combustible mixture of gaseous ammonia 114A (and / or its components hydrogen and nitrogen) and HP air 112A to the primary combustion zone 202 of the combustion chamber 172 of the combustion liner 164. The primary burner 200 may also burn other fuels, such as liquid and / or gaseous fuels. In this regard, each primary burner 200 may include any currently known or hereafter developed burner structure to provide dual-fuel capability beyond the structures described herein. Since dual-fuel fuel burners 200 are known in the art, no further details are provided, and the reader can therefore focus on the prominent parts of this disclosure.

[0047] Figure 3 shows a cross-sectional view of a heat exchanger 210 for a combustor 100 of a GT system 90 according to an embodiment of the present disclosure, and Figure 4 shows a partial cross-sectional perspective view thereof. As described above, the combustor body 160 has a combustion liner 164, and the head end assembly 176 has a cap assembly 198. The combustor 100 also includes primary burners 200 located within the cap assembly 198 and directed into the combustion liner 164. As described above, each primary burner 200 is configured to mix gaseous ammonia 114A into a first flow of air 112A and direct the ammonia / air mixture 206 into a primary combustion zone 202 in the combustion liner 164. As described later, the heat exchanger 210 heats the flow of ammonia 212 (hereinafter referred to as "ammonia 212," "ammonia flow 212," or "ammonia stream 212") transported through the ammonia heat exchange passage 214, converting the ammonia 212 from a liquid state 216 to a gaseous state 218, i.e., gaseous ammonia 114A, and causing the gaseous ammonia to be at least partially thermally dissociated ("decomposed") into its constituent hydrogen and nitrogen. The reference labeling of the location of the liquid state 216 versus the gaseous state 218 is not necessarily accurate in terms of where evaporation occurs, and it should be emphasized that evaporation and / or decomposition can occur anywhere along the heat exchanger 210 where enough heat is absorbed by the ammonia stream 212 to convert from liquid to gas. More specifically, the heat of the air 112A in the high-pressure plenum 222 is made high enough to thermally dissociate the ammonia into nitrogen and hydrogen, and references to "gas state 218" herein should be understood to mean "gasic and / or thermally dissociated state."

[0048] Next, the heat exchanger 210 will be described in detail. As shown in Figures 3 and 4, the heat exchanger 210 includes a body 220, which has a first end 242 located within or near the end cover 196 and defining an ammonia inlet 240, a second end 224 extending into a primary combustion zone 202 defined from the cap assembly 198 within the combustion liner 164 (Figure 2), and an outlet end 223 located in front of the cap assembly 198, i.e., upstream of the cap assembly 198. The second end 224 is enclosed by the combustion liner 164 and extends into the primary combustion zone 202, thereby allowing heat from the primary combustion zone 202 to be transferred through the body 220 to the ammonia fuel moving through the body 220. Specifically, the heat exchanger 210 defines an ammonia heat exchange passage 214 (hereinafter referred to as "HE passage 214" for brevity) that extends toward the second end 224 and returns from the second end 224 of the heat exchanger 210.

[0049] More specifically, the HE passage 214 may include an ammonia inlet 240 located at the first end 242 of the main body 220, a first sub-passage 244 fluidly communicating with the ammonia inlet 240, through which ammonia 212 flows in a first direction to the second end 224 in the primary combustion zone 202, and a second return sub-passage 246 fluidly communicating with the first sub-passage 244, through which ammonia 212 flows out of the second end 224 in the primary combustion zone 202 in a second direction. Thus, the HE passage 214 directs the flow of ammonia 212 away from the head end assembly 176 to the primary combustion zone 202, and then returns the ammonia to the fuel plenum 320 which leads to the head end assembly 176 via the outlet end 223 and to the primary burner 200. As the ammonia 212 flows along the heat exchanger 210, it is exposed to heat from the primary combustion zone 202, possibly from other sources, which heats the ammonia 212 transported through the HE passage 214, converting it from a liquid state 216 to a gaseous state 218, i.e., gaseous ammonia 114A, and / or thermally dissociating the ammonia into nitrogen and hydrogen. The outlet end 223 is fluidly coupled to the fuel plenum 320 (described further below), which supplies the primary burner 200. The HE passage 214 may include a single passage or multiple passages through the main body 220.

[0050] In certain embodiments, as shown in Figures 3 and 4, the first sub-passage 244 is defined by a first conduit 250 that fluidly communicates with the ammonia inlet 240 at a first end 242 of the main body 220, and is located within the primary combustion zone 202 and concentrically within a second larger conduit 252 having a closed end 254 exposed to the primary combustion zone. The second conduit 252 having the closed end 254 may have a cup or bucket shape. Thus, the second return sub-passage 246 is defined by an open space (e.g., an annular portion 260) between the first conduit 250 and the second conduit 252. The first conduit 250 may have at least a partially closed end 256 and at least one opening 258 that fluidly connects the first sub-passage 244 and the second sub-passage 246 and provides impingement cooling to the closed end 254 of the second conduit 252. The opening 258 allows the flow of ammonia 212 to return to the head end assembly 176 in a gaseous state 218, i.e., gaseous ammonia 114A, for use elsewhere in the combustor 100.

[0051] Figure 5 shows a cross-sectional end view of line AA in Figure 3. In Figures 3 to 5, the second conduit 252 is separated from the first conduit 250 such that the second sub-passage 246 includes an annular portion 260. In this way, the ammonia 212 exiting the opening 258 from the first sub-passage 244 (first conduit 250) enters the manifold 262 at the closed end 254 and then enters the second sub-passage 246 in the form of the annular portion 260. However, the first and second sub-passages 244, 246 can have other configurations. Figures 6 and 7 show end views of alternative arrangements (similar to line AA in Figure 3). In Figure 6, the first sub-passage 244 includes a conduit supplying the manifold (as in the manifold 262 in Figures 3 and 4), while the second sub-passage 246 includes multiple individual passages 264 within the main body 220 (rather than a concentric annular portion 260). In Figure 7, the conduit is replaced, and the first sub-passage 244 and the second sub-passage 246 can each contain multiple fluid-coupled passages. More specifically, multiple first sub-passages 244 can supply a manifold (not shown) (such as the manifold 262 in Figures 3-4) to supply multiple second sub-passages 246, or multiple first sub-passages 244 (as shown by dashed lines in Figure 7) can each supply their respective second sub-passages 246. Other arrangements of sub-passages for allowing the ammonia flow 212 to enter and exit the primary combustion zone 202 within the body 220 of the heat exchanger 210 are also possible. Although the sub-passages 244, 246 are shown as linear, they may include any form of curvature and / or undulation, such as peaks and valleys, protrusions / depressions, or other heat exchange elements, to increase heat exchange from the primary combustion zone 202 to the ammonia flow 212.

[0052] Figure 8 shows a cross-sectional view of a heat exchanger 210 having a secondary burner 270 inside for a combustor 100 according to another embodiment of the present disclosure, and Figure 9 shows a partial cross-sectional perspective view. In the embodiments of Figures 8 and 9, the heat exchanger 210 may have any of the above-described configurations, but also includes a secondary burner 270 located within a central opening 272 of the body 220 and thermally communicating with an HE passage 214, where an ammonia flow 212 delivered through the HE passage 214 also cools the secondary burner 270. In these embodiments, the body 220 of the heat exchanger 210 includes an outer heat shield 280, an inner heat exchange member 282 within the outer heat shield 280, and a partition wall 284 in the space between the outer heat shield 280 and the inner heat exchange member 282. An end wall 286 connects the outer heat shield 280 and the inner heat exchange member 282 concentrically and spaced apart. The partition wall 284 divides most of the space (axial direction) between the outer shield 280 and the inner heat exchange member 282 into a first sub-passage 244 and a second sub-passage 246. Here, as shown in Figure 9, the first sub-passage 244 and the second sub-passage 246 each include an annular section; that is, both are annular passages.

[0053] The secondary burner 270 can take on a wide variety of forms, similar to the primary burner 200 or other burners. In the example shown in Figure 9, the secondary burner 270 includes a fuel-air mixed passage 290 defined by an interior 292 of the internal heat exchange member 282 (the interior 292 may also be defined by a central opening 272). The secondary burner 270 also includes a swozle assembly 294 located within the fuel-air mixed passage 290. The swozle assembly 294 may include a plurality of swirling vanes 296 that give swirling to the airflow 112C flowing through the fuel-air mixed passage 290. Each swirling vane 296 may include an internal fuel passage 298 that is in fluid communication with at least one fuel injector 300. The secondary burner 270 may also include a fuel passage 302, such as a central fuel passage 302, that introduces a second fuel 114C into the internal fuel passage 298. Fuel 114C may be delivered in any way from the fuel source 116 (Figure 1) to the fuel passage 302 in the head end assembly 176. A second fuel / air mixture 310 is generated by the swozle assembly 294 and led to the primary combustion zone 202 in the combustion liner 164. A specific swozle assembly 294 is shown, but it should be noted that it may include any currently known or future-developed structures for mixing air and fuel using swirling vanes. Furthermore, with respect to the secondary burner 270, the outlet end 312 of the fuel-air mixture passage 290 of the secondary burner 270 is located further into the primary combustion zone 202 than the outlet ends 314 of the multiple primary burners 200.

[0054] The combustor 100 may include an optional gas transport passage for guiding gaseous ammonia 114A, i.e., the gaseous state 218, from the heat exchanger 210 to its final place of use. In some embodiments, the gaseous ammonia 114A is thermally dissociated into hydrogen and nitrogen gases, possibly with some residual (undecomposed) ammonia in the gaseous state 218. For example, the combustor 100 may include a fuel plenum 320 that is in fluid communication with the outlet of the ammonia HE passage 214 and with the ammonia inlets 322 of each of the multiple primary burners 200. In this case, each primary burner 200 may be further configured to mix the ammonia 212 in the gaseous state 218, i.e., gaseous ammonia 114A, and / or its constituent diatomic gases, into an airflow 112A, guiding the fuel / air mixture 206 into a primary combustion zone 202 defined within the combustion liner 164. The primary burner 200 may be one of a group of bundles of premixed tubes extending through a common fuel plenum 320 defined between a front plate 326 and a rear plate 328, as shown in Figures 3 and 8. The rear plate 328 may be in front of the cap assembly 198 (as shown in Figures 3 and 8), thereby allowing an air plenum to be defined between them, or the cap assembly 198 may function as the rear plate 328 of the fuel plenum 320 (as shown in Figures 4 and 9).

[0055] Next, a method for operating the combustor 100 of the GT system 90 according to embodiments of the present disclosure will be described. During operation, embodiments of the method include burning a fuel / air mixture 206 formed by a plurality of primary burners 200 in a primary combustion zone 202 defined within a combustion liner 164. Furthermore, embodiments of the method may include transporting a flow of ammonia 212 through an ammonia HE passage 214 defined in a heat exchanger 210 in order to convert the ammonia 212 from a liquid state 216 to a gaseous state 218, i.e., gaseous ammonia 114A, and / or to thermally dissociate the ammonia into hydrogen and nitrogen. As described above, the heat exchanger 210 includes a body 220 having an outlet end 223 located within or in front of the cap assembly 198 and a second end 224 extending beyond the cap assembly 198 into the primary combustion zone 202 defined within the combustion liner 164. The ammonia HE passage 214 extends into the second end 224 and returns from the second end 224 of the heat exchanger 210, so that ammonia 212 absorbs heat from the primary combustion zone 202 and evaporates into a gaseous state 218 (thermally dissociating into gas and / or hydrogen and nitrogen). The evaporated and / or thermally decomposed ammonia flows through the outlet end 223 of the heat exchanger 210 to the fuel plenum 320 and is used as fuel by the primary burner 200. In certain embodiments, the combustor 100 further includes a secondary burner 270 located within the central opening 272 of the body 220 of the heat exchanger 210, as shown in Figures 8-9, and is thermally in communication with the ammonia HE passage 214, for example, via an internal heat exchange member 282. In this setting, embodiments of the method may further include using the flow of ammonia 212 transported through the ammonia HE passage 214 to cool the secondary burner 270. To promote the thermal dissociation of ammonia, one or more surfaces of the ammonia HE passage 214 may be coated with a catalytic material which may include nickel, iron, ruthenium, and / or cobalt.

[0056] The mounting flange 197 and end cover 196 may include any necessary passages or openings for delivering ammonia 212, fuel 114B, 114C and / or air 112A-C. Furthermore, the end cover 196 and / or cap assembly 198 may include any necessary walls, passages and / or openings adjacent thereto, and may form a fuel plenum 320 to guide gaseous ammonia 114A to a desired location, for example, to an ammonia inlet 322 in the primary burner 200. The mounting flange 197 is also configured to allow the heat exchanger 210 (and / or secondary burner 270) to be removed within the head end assembly 176 of the combustor 100. In this way, removal of the heat exchanger 210 and / or secondary burner 270 can be achieved by removing the mounting flange 197 from the connection of the head end assembly 176 to the end cover 196 and sliding out the heat exchanger 210. The mounting flange 197 can be selectively coupled to the head end assembly 176 by any currently known or future-developed method, such as, but not limited to, threaded fasteners (not shown).

[0057] The heat exchanger 210 (and any burners 200, 270) may be made of any currently known or future-developed flame-resistant and oxidation-resistant material. The material may be a metal, a pure metal, or an alloy. The heat exchanger 210 (and any burners 200, 270) may include a metal that is typically used in turbine components such as turbine blades or nozzles and has higher temperatures and higher oxidation resistance than materials typically used in combustion hardware. In this case, the material may include, but is not limited to, cobalt-chromium-molybdenum (CoCrMo) alloys, stainless steel, austenitic nickel-chromium-based alloys, such as nickel-chromium-molybdenum-niobium alloy (NiCrMoNb) (e.g., Inconel 625 or Inconel 718), nickel-chromium-iron-molybdenum alloy (NiCrFeMo) (e.g., Hastelloy® X, available from Haynes International, Inc.), nickel-chromium-cobalt-molybdenum alloy (NiCrCoMo) (e.g., Haynes 232 or Haynes 282, available from Haynes International, Inc.), or nickel-chromium-cobalt-titanium alloy (NiCrCoTi) (e.g., GTD 262, developed by General Electric Company), and other non-reactive metals made from non-explosive or non-conductive powders. Other possibilities include, for example, Rene 108, CM 247, Mar M 247, and any precipitation-hardening (PH) nickel alloy.

[0058] In certain embodiments, the heat exchanger 210 (and optional burners 200, 270) may be additively manufactured using any currently known or future-developed techniques capable of forming a single body. Thus, various components may include multiple parallel sintered metal layers. Other manufacturing methods are also possible.

[0059] As shown in Figure 2, embodiments of the present disclosure may also include a combustor 100 for the GT system 90. The combustor 100 includes a combustor body 160 including a combustion liner 164. The combustor 100 also includes a head end assembly 176 including primary burners 200 directed into the combustion liner 164 and a heat exchanger 210 integrated with one or more of the primary burners 200. The heat exchanger 210 may be as described herein and extends into a combustion chamber 172 defined by the combustion liner 164. The combustor 100 generally terminates at a point adjacent to the first stage 340 of the stationary nozzle 342 of the turbine 128. The first stage 340 of the stationary nozzle 342 at least partially defines the turbine inlet 142 to the turbine 128. The combustor body 160, i.e., the combustion liner 164, at least partially defines a high-temperature gas path (HGP) for delivering combustion gases 122 from the combustion chamber 172, i.e., the primary combustion zone 202 and any secondary combustion zone 204, to the turbine inlet 142 of the turbine 128 during the operation of the GT system 90.

[0060] Embodiments of the present disclosure may also include a GT system 90, as shown in Figure 1, comprising a compressor section 110, a combustion section 120 operably coupled to the compressor section 110, and a turbine section 130 operably coupled to the combustion section 120. As described herein, the combustion section 120 includes at least one combustor 100, comprising a combustor body 160 including a combustion liner 164, and a head end assembly 176 located at the front end of the combustor body 160. The combustor 100 may also include a heat exchanger 210 as described herein. The head end assembly 176 includes a plurality of primary burners 200 directed toward the combustion liner 164, as described herein.

[0061] This disclosure provides various technical and commercial advantages, examples of which are described herein. Embodiments of a heat exchanger provide a mechanism for efficiently heating a flow of ammonia transported through an ammonia heat exchange passage and converting ammonia from a liquid state to a gaseous state. In some situations, ammonia can be thermally dissociated ("decomposed") into hydrogen and nitrogen. Gaseous ammonia (and / or hydrogen produced by ammonia decomposition) can be used as fuel for a combustion reaction elsewhere in the combustor, for example, in the primary burner. In this way, the heat exchanger eliminates the need for a separate ammonia evaporator. The heat exchanger can also act as a flame stabilizer through a recirculation zone within the primary combustion zone. If a secondary burner is located within the heat exchanger, the ammonia flow can cool the secondary burner and extend its lifespan.

[0062] Throughout this specification and the claims, the approximation language used herein may be applied to modify any quantitative expression that is permitted to vary without altering the fundamental function of the subject. Thus, values ​​modified by terms such as “approximately,” “about,” and “substantially” are not limited to the exact values ​​specified. In at least some examples, the approximation language may correspond to the precision of the instrument used to measure the value. Herein, and throughout this specification and the claims, range limitations are combinatorial and / or substituted, and unless the context or wording specifically indicates otherwise, such ranges are identified and include all subranges encompassed therein. “Approximately” or “about,” applied to specific values ​​within a range, may indicate + / - 10% of the stated value, unless applied to the values ​​at both ends and particularly dependent on the precision of the instrument used to measure the value.

[0063] All corresponding structures, materials, actions, and equivalents of all means-plus-function elements or step-plus-function elements in the following claims are intended to include any structures, materials, or actions for performing a function in combination with other claimed elements specifically claimed. The descriptions in this disclosure are presented for illustrative and explanatory purposes and are not intended to be exhaustive or to limit the disclosure to the forms disclosed herein. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. The embodiments have been selected and described to best illustrate the principles of this disclosure and the practical applications of the art, and to enable those skilled in the art to understand this disclosure in order to consider various modifications to these embodiments that may be suitable for the particular use under consideration. [Explanation of symbols]

[0064] 90 Gas Turbine (GT) System 100 Combustor 102 Entrance Section 106 Air 108 Compressor 109 Compressor discharge port 110 Compressor Section 112 High-pressure (HP) air 112A HP Air 112B HP Air 112C Airflow 114A Gaseous ammonia 114B Fuel 114C fuel 116 Fuel source 120 Combustion Sections 122 Combustion gases 128 Turbine 130 Turbine Section 132 shaft 134 Generators 136 Exhaust gas 138 Exhaust Section 140 exhaust stack 142 Turbine Inlet 150 Axial Fuel Stage (AFS) Injector 152 Outer casing 154 HP air source 160 Combustion Unit 164 Combustion Liner 166 Cylindrical section 168 Tapered transition section 170 Rear frame 172 Combustion Chamber 174 Airflow channel 176 Head end assembly 177 Flow Sleeve 178 Open end 179 Annular partition 182 LP air 188 Fuel Line 190 outer sleeve 192 Collision Hole 196 End cover 197 Mounting flange 198 Cap Assembly 200 Primary Burner, Dual Fuel Burner 202 Primary Combustion Zone 204 Secondary Combustion Zone 206 Fuel / Air Mixture 210 Heat exchanger 212 Ammonia, ammonia flow 214 Ammonia heat exchange passage 216 Liquid state 218 Gas state 220 Main Unit 222 High-pressure plenum 223 Outlet end 224 Second end 240 Ammonia inlet 242 First end 244 First side aisle 246 Second return side passage 250 First conduit 252 Second larger conduit, second conduit 254 Closed end 256 End 258 opening 260 Circular section 262 Manifold 264 Passage 270 Secondary Burner 272 Center opening 280 Outer heat shield 282 Internal heat exchange component 284 Partition wall 286 End wall 290 Fuel-air mixing passage 292 Interior 294 Swozle Assembly 296 Swivel vanes 298 Internal fuel passage 300 Fuel Injector 302 Fuel passage 310 Second fuel / air mixture 312 Outlet end 314 Outlet end 320 Fuel Plenum 322 Ammonia Inlet 326 Front Plate 328 Rear plate 340 Section 1 342 Stationary nozzle

Claims

1. A heat exchanger (210) for a combustor (100) of a gas turbine system (90), wherein the combustor (100) includes a combustor body (160) having a combustion liner (164), a head end assembly (176) having a cap assembly (198), and a plurality of primary burners (200) disposed within the cap assembly (198) and led into the combustion liner (164), each primary burner (200) configured to mix a first fuel (114A) into a first airflow (112A) and lead the first fuel / air mixture (206) into a primary combustion zone (202) defined within the combustion liner (164), and the heat exchanger (210) includes, A body (220) having a first end (242) defining an ammonia inlet (240), a second end (224) extending from the cap assembly (198) to the primary combustion zone (202) defined within the combustion liner (164), and an outlet end (223) in front of the cap assembly (198), wherein the heat exchanger (210) extends toward the second end (224) and defines an ammonia heat exchange passage (214) of the heat exchanger (210) returning from the second end (224) to the outlet end (223), the body (220) comprises The heat exchanger (210) is configured to heat the flow of ammonia (212) conveyed through the ammonia heat exchange passage (214) and convert the ammonia (212) from a liquid state (216) to a gaseous state (218). Heat exchanger (210).

2. The heat exchanger (210) according to claim 1, wherein the ammonia heat exchange passage (214) includes: an ammonia inlet (240) located at the first end (242) of the main body (220); a first sub-passage (244) fluidly communicating with the ammonia inlet (240), wherein the ammonia (212) flows in a first direction to the second end (224) in the primary combustion zone (202); and a second return sub-passage (246) fluidly communicating with the first sub-passage (244), wherein the ammonia (212) flows from the second end (224) out of the primary combustion zone (202) to the fuel plenum (320) in a second direction, and the fuel plenum (320) guides the ammonia (212) to the plurality of primary burners (200).

3. The first sub-passage (244) is defined by a first conduit (250) that is in fluid communication with the ammonia inlet (240) at the first end (242) of the main body (220), which is arranged concentrically within a second larger conduit (252) having a closed end (254) within the primary combustion zone (202). The second return sub-passage (246) is defined by the open space (260) between the first conduit (250) and the second conduit (252), The first conduit (250) has an end having at least one opening that fluidly connects the first sub-passage (244) and the second sub-passage (246), The heat exchanger (210) according to claim 2.

4. The heat exchanger (210) according to claim 3, wherein the second sub-passage (246) includes an annular portion (260).

5. The heat exchanger (210) according to claim 2, further comprising a secondary burner (270) disposed within the central opening (272) of the main body (220) and thermally communicating with the ammonia heat exchange passage (214), thereby cooling the secondary burner (270) with respect to the flow of ammonia conveyed through the ammonia heat exchange passage (214).

6. The heat exchanger (210) according to claim 5, wherein the main body (220) includes an outer heat shield (280), an inner heat exchange member (282) within the outer heat shield (280), a partition wall (284) in the space between the outer heat shield (280) and the inner heat exchange member (282), and an end wall (286) connecting the outer heat shield (280) and the inner heat exchange member (282), the partition wall (284) defining the space to the first sub-passage (244) and the second sub-passage (246).

7. The aforementioned secondary burner (270) The fuel-air mixing passage (290) is defined by the interior (292) of the inner heat exchange member (282), A swozle assembly (294) disposed within the fuel-air mixing passage (290), wherein the swozle assembly (294) includes a plurality of swirling vanes (296) that give swirling to a second airflow (112C) flowing through the fuel-air mixing passage (290), and each of the swirling vanes (296) includes an internal fuel passage (298) that is in fluid communication with at least one fuel injector (300), The system includes a fuel passage (302) for introducing a second fuel (114C) into the internal fuel passage (298), A second fuel / air mixture (310) is generated by the swozle assembly (294) and directed to the primary combustion zone (202) within the combustion liner (164). The heat exchanger (210) according to claim 6.

8. The heat exchanger (210) according to claim 7, wherein the outlet end (312) of the fuel-air mixing passage (290) of the secondary burner (270) is located further within the combustion liner (164) than the outlet ends (314) of the plurality of primary burners (200).

9. The heat exchanger (210) according to claim 2, wherein the first sub-passage (244) and the second sub-passage (246) each include an annular portion (260).

10. The heat exchanger (210) according to claim 2, wherein the first sub-passage (244) and the second sub-passage (246) each include a plurality of fluid-coupled passages (264).

11. A combustor (100) of a gas turbine system (90), wherein the combustor (100) is The combustion chamber body (160) includes a combustion liner (164), Head end assembly (176), Cap assembly (198) and, A plurality of primary burners (200) are arranged within the cap assembly (198) and led into the combustion liner (164), each primary burner (200) being configured to mix a first fuel (114A) with a first airflow (112A) and lead the first fuel / air mixture (206) into a primary combustion zone (202) defined within the combustion liner (164), A heat exchanger (210) according to any one of claims 1 to 10, The head end assembly (176) and A combustion device (100) equipped with the above.

12. The combustor (100) according to claim 11, further comprising a fuel plenum (320) that is in fluid communication with the outlet of the ammonia heat exchange passage (214) and in fluid communication with the ammonia inlet (322) of each of the plurality of primary burners (200), wherein each primary burner (200) is further configured to receive the ammonia (212) in a gaseous state (218) as a first fuel, mix the gaseous ammonia (114A) with the first airflow (112A), and direct the ammonia / air mixture as the first fuel / air mixture (206) to the primary combustion zone (202) defined within the combustion liner (164).

13. A method for operating a combustor (100) of a gas turbine system (90), the combustor (100) comprising: a combustor body (160) including a combustion liner (164); a head end assembly (176) comprising: a head end assembly (176) comprising: a plurality of primary burners (200) disposed within the cap assembly (198) and led into the combustion liner (164), each primary burner (200) configured to mix a first fuel (114A) into a first airflow (112A) and lead the first fuel / air mixture (206) into a primary combustion zone (202) in the combustion liner (164); and a heat exchanger (210) according to any one of claims 1 to 10, wherein the method is The steps include burning the fuel / air mixture (206) formed by the plurality of primary burners (200) in the primary combustion zone (202) of the combustion liner (164), A step of transporting a flow of ammonia (212) through an ammonia heat exchange passage (214) defined within the heat exchanger (210) to convert ammonia (212) from a liquid state (216) to a gaseous state (218), wherein the heat exchanger (210) has a first end (242) defining an ammonia inlet (240) and a second end extending beyond the cap assembly (198) into the primary combustion zone (202) defined within the combustion liner (164) The device includes a body having two ends (224) and an outlet end (223) defined in front of the cap assembly (198), wherein the ammonia heat exchange passage (214) extends into the second end (224) and returns from the second end (224) of the heat exchanger (210) to the outlet end (223), and the outlet end (223) is in fluid communication with a fuel plenum (320) that leads the gaseous ammonia (114A) to the plurality of primary burners (200), and Methods that include...

14. The method according to claim 13, further comprising the step of cooling the secondary burner (270) using the flow of ammonia conveyed through the ammonia heat exchange passage (214), wherein the combustor (100) further comprises a secondary burner (270) disposed within the central opening of the body (220) of the heat exchanger (210) and thermally communicating with the ammonia heat exchange passage (214).

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