Additively manufactured combustor body with resonating tube

Abstract

To provide an additively manufactured combustor body with a resonating tube in a turbomachine combustor.SOLUTION: A combustor 200 includes an additively manufactured (AM) combustor body 204 including an integrated member 206 that includes: a combustion liner 208 defining a combustion chamber 184 and including cylindrical and tapered transition portions 209, 212; and a rear frame 218 provided at a rear end 214 of the tapered transition portion 212. A resonating tube is part of the AM combustor body 204 and is configured to dampen acoustic pressure oscillations of combustion gases 152 in the combustor 200. The resonating tube includes a body defining a resonating chamber 190 and a resonating tube neck 192 having a first end in fluid communication with the resonating chamber 190.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates generally to turbomachine combustors, and more particularly to additively manufactured combustor bodies with resonator tubes. [Background technology]

[0002] Gas turbine systems include a combustion section containing multiple combustors in which fuel is burned to generate a flow of combustion gases that is converted to kinetic energy in a downstream turbine (e.g., an expansion turbine). In the combustors of such gas turbine systems, disruptive acoustic pressure oscillations (pressure pulses) can occur as a result of normal operating conditions depending on the fuel-air ratio, total mass flow, and other operating conditions. Combustion instabilities associated with operation using low-emission fuels tend to generate unacceptably high dynamic pressure oscillations within the combustor, potentially posing challenges to operability and / or durability. In particular, advanced gas turbine combustors increase the likelihood of high-frequency acoustics due to increased energy release density and rapid mixing of reactants to minimize nitrous oxide (NOx) emissions. Undesirable acoustic resonant frequency shifts can also result from pressure oscillations. Both low- and high-frequency acoustic modes can be challenging.

[0003] Additive manufacturing, such as direct metal laser melting (DMLM) or selective laser melting (SLM), is emerging as a reliable manufacturing method for producing combustor components that can mitigate undesirable acoustic frequencies and / or acoustic modes. Summary of the Invention

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

[0005] One aspect of the present disclosure includes a combustor for a gas turbine system, the combustor including an additively manufactured (AM) combustor body including a one-piece member, the one-piece member including a combustion liner defining a combustion chamber and including a cylindrical portion and a tapered transition portion, and a resonating tube configured to dampen acoustic pressure oscillations of combustion gases in the combustor, the resonating tube including a body defining a resonating chamber and a resonating tube neck having a first end in fluid communication with the resonating chamber, the AM combustor body including a plurality of parallel sintered metal layers. body includes a plurality of parallel, sintered metal layers).

[0006] Another aspect of the present disclosure includes any of the preceding aspects, and further includes an annulus surrounding at least part of the combustion liner, the annulus defined by one of a flow sleeve surrounding at least part of the combustion liner or an annular passage in the at least part of the combustion liner.

[0007] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is on an outside of the annulus, and the resonating tube neck includes a second end in fluid communication with the annulus.

[0008] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is on an outside of the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber defined by the combustion liner.

[0009] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is positioned in the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber defined by the combustion liner.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is spaced from an outside of the annulus by the resonating tube neck, and the resonating tube neck includes a second end in fluid communication with the annulus.

[0011] Another aspect of the present disclosure includes any of the preceding aspects, wherein the AM combustor body includes an aft frame at an aft end of the tapered transition portion and an impingement flow sleeve surrounding the tapered transition portion, the resonating chamber is on an outside of one of the tapered transition portions adjacent the aft frame and the impingement flow sleeve, an impingement annulus is defined between the impingement flow sleeve and the tapered transition portion of the combustion liner, and the resonating tube neck includes a second end in fluid communication with the combustion chamber in the combustion liner. in fluid communication with the combustion chamber in the combustion liner).

[0012] Another aspect of the present disclosure includes any of the preceding aspects, wherein a portion of the resonating chamber is within the aft frame.

[0013] Another aspect of the present disclosure includes any of the preceding aspects, and further includes an impingement annulus defined in one of the tapered transition portions of the combustion liner and between an impingement flow sleeve and the tapered transition portion of the combustion liner, the resonating chamber being on an outside of the impingement annulus, and the resonating tube neck includes a second end in fluid communication with the impingement annulus.

[0014] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating tube is one of at least two resonating tubes, and at least one of the two resonating tubes includes: (a) a resonating chamber disposed on an outside of an annulus surrounding at least part of the combustion liner, the annulus defined by one of a flow sleeve surrounding the combustion liner or an annular passage in at least part of the combustion liner, and wherein the resonating tube neck includes a second end in fluid communication with the annulus; (b) a resonating chamber disposed on an outside of the annulus, the resonating tube neck including a second end in fluid communication with a combustion chamber defined by a combustion liner;(c) a resonating chamber disposed within the annulus, and wherein the resonating tube neck includes a second end in fluid communication with the combustion chamber; (d) a resonating chamber spaced outside of the annulus by the resonating tube neck,and wherein the resonating tube neck includes a second end in fluid communication with the annulus; (e) a resonating chamber disposed on an outside of one of the tapered transition portion and an impingement flow sleeve surrounding the tapered transition portion, the tapered transition portion including an aft frame at an aft end of the tapered transition portion, the resonating chamber being adjacent to the aft frame, the impingement annulus being defined between the tapered transition portion and the impingement flow sleeve, the resonating chamber including a second end in fluid communication with the combustion chamber;and the resonating tube neck includes a second end in fluid communication with the combustion chamber), (f) a resonating chamber at least partially disposed within the aft frame, and the resonating tube neck includes a second end in fluid communication with the combustion chamber, or (g) a resonating chamber disposed on an outside of the impingement annulus, and the resonating tube neck has a second end in fluid communication with the impingement annulus.

[0015] Another aspect of the present disclosure includes any of the preceding aspects, wherein the at least two resonating tubes are configured to dampen different frequencies.

[0016] Another aspect of the present disclosure is a gas turbine (GT) system including: a compressor section; a combustion section operatively coupled to the compressor section; and a turbine section operatively coupled to the combustion section, wherein the combustion section includes at least one combustor including an additively manufactured (AM) combustor body including a one-piece member, the one-piece member including: a combustion liner defining a combustion chamber and including a cylindrical portion and a tapered transition portion; and a resonating tube configured to dampen acoustic pressure oscillations of combustion gases in the combustor, the resonating tube including a body defining a resonating chamber and a resonating tube neck having a first end in fluid communication with the resonating chamber. The AM combustor body includes a plurality of parallel, sintered metal layers.

[0017] Another aspect of the present disclosure includes any of the preceding aspects, and further includes an annulus surrounding at least part of the combustion liner, the annulus defined by one of a flow sleeve surrounding at least part of the combustion liner or an annular passage in the at least part of the combustion liner.

[0018] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is exterior to the annulus, and the resonating tube neck includes a second end in fluid communication with the annulus.

[0019] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is exterior to the annulus, and the resonating tube neck includes a second end in fluid communication with a combustion chamber defined by the combustion liner.

[0020] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is disposed within the annulus, and the resonating tube neck includes a second end in fluid communication with a combustion chamber within the combustion liner.

[0021] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating chamber is spaced from an exterior of the annular portion by the resonating tube neck, the resonating tube neck including a second end in fluid communication with the annular portion.

[0022] Another aspect of the present disclosure includes any of the preceding aspects, wherein the AM combustor body includes an aft frame at an aft end of the tapered transition portion and an impingement flow sleeve surrounding the tapered transition portion, the resonating chamber is on an outside of one of the tapered transition portions adjacent the aft frame and the impingement flow sleeve, an impingement annulus is defined between the impingement flow sleeve and the tapered transition portion of the combustion liner, and the resonating tube neck includes a second end in fluid communication with the combustion chamber in the combustion liner. in the combustion liner).

[0023] Another aspect of the present disclosure includes any of the preceding aspects, wherein a portion of the resonating chamber is within the aft frame.

[0024] Another aspect of the present disclosure includes any of the preceding aspects, and further includes an impingement annulus defined in one of the tapered transition portions of the combustion liner and between an impingement flow sleeve and the tapered transition portion of the combustion liner, the resonating chamber is on an outside of the impingement annulus, and the resonating tube neck includes a second end in fluid communication with the impingement annulus.

[0025] Another aspect of the present disclosure includes any of the preceding aspects, wherein the resonating tube is one of at least two resonating tubes, at least one of the two resonating tubes being: (a) a resonating chamber disposed on an outside of an annulus surrounding at least part of the combustion liner, the annulus defined by one of a flow sleeve surrounding the combustion liner or an annular passage in at least part of the combustion liner, and wherein the resonating tube neck includes a second end in fluid communication with the annulus; or (b) a resonating chamber disposed on an outside of the annulus, the resonating tube neck including a second end in fluid communication with the combustion chamber defined by the combustion liner. (c) a resonating chamber disposed within the annulus, wherein the resonating tube neck includes a second end in fluid communication with the combustion chamber defined by the combustion liner;and wherein the resonating tube neck includes a second end in fluid communication with the combustion chamber; (d) a resonating chamber spaced outside of the annulus by the resonating tube neck, and wherein the resonating tube neck includes a second end in fluid communication with the annulus; (e) a resonating chamber disposed on an outside of one of the tapered transition portion and an impingement flow sleeve surrounding the tapered transition portion, the tapered transition portion including an aft frame at an aft end of the tapered transition portion, the resonating chamber adjacent to the aft frame, the impingement annulus defined between the tapered transition portion and the impingement flow sleeve, and the resonating chamber includes a second end in fluid communication with the combustion chamber. impingement flow sleeve surrounding the tapered transition portion; therefore the tapered transition portion includes an aft frame at an aft end of the tapered transition portion,and the resonating chamber is adjacent to the aft frame; and wherein an impingement annulus is defined between the tapered transition portion and the impingement flow sleeve, and the resonating tube neck includes a second end in fluid communication with the combustion chamber; (f) a resonating chamber at least partially disposed within the aft frame, and the resonating tube neck includes a second end in fluid communication with the combustion chamber; or (g) a resonating chamber disposed on an outside of the impingement annulus, and the resonating tube neck has a second end in fluid communication with the impingement annulus.

[0026] Another aspect of the present disclosure includes any of the preceding aspects, wherein the at least two resonating tubes are configured to attenuate different frequencies.

[0027] Two or more aspects described in this disclosure, including those described in this Summary, may be combined to form embodiments not specifically described herein, i.e., all embodiments described herein may be combined with each other.

[0028] The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims. [Brief explanation of the drawings]

[0029] These and other features of the present disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings illustrating various embodiments of the present disclosure. [Figure 1] FIG. 1 is a cross-sectional side view of a portion of a combustor having an additively manufactured combustor body including a resonator tube according to an embodiment of the present disclosure. [Figure 2] FIG. 10 is a cross-sectional side view of a portion of a combustor having an additively manufactured single-wall combustor body including a resonator tube according to another embodiment of the present disclosure. [Figure 3] FIG. 2 is a cross-sectional view of multiple parallel sintered metal layers of a combustor body according to an embodiment of the present disclosure. [Figure 4] FIG. 1 is a cross-sectional view of a resonator tube according to an embodiment of the present disclosure. [Figure 5] FIG. 10 is a cross-sectional view of a resonator tube within a combustor body according to another embodiment of the present disclosure. [Figure 6] FIG. 10 is a cross-sectional view of a resonator tube within a combustor body according to another embodiment of the present disclosure. [Figure 7] FIG. 10 is a cross-sectional view of a resonator tube within a combustor body according to yet another embodiment of the present disclosure. [Figure 8] FIG. 10 is a cross-sectional view of a resonator tube within a combustor body according to an additional embodiment of the present disclosure. [Figure 9] FIG. 10 is a cross-sectional view of a resonator tube within a combustor body according to a further embodiment of the present disclosure. [Figure 10]FIG. 1 is a functional block diagram of an exemplary gas turbine system that may be used with a combustor and combustor body including a resonator tube according to various embodiments of the present disclosure. [Figure 11] FIG. 1 is a schematic block diagram of an exemplary additive manufacturing system for additively manufacturing a combustor body including a resonator tube, in accordance with various embodiments of the present disclosure.

[0030] It should be noted that the drawings of the present disclosure are not necessarily to scale. The drawings are intended to depict only typical aspects of the present disclosure and therefore should not be considered limiting of the scope of the present disclosure. In the drawings, like numbers represent like elements between the drawings. DETAILED DESCRIPTION OF THE INVENTION

[0031] As an initial issue, a clear explanation of the state of the art requires the selection of specific terminology when referring to and describing relevant machine components in an exemplary turbomachine application. In doing so, common industry terminology will be used, where possible, and employed in a manner consistent with its common meaning. Unless otherwise specified, such terms should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will recognize that particular components are often referred to using several different or overlapping terms. What is described herein as a single component may include and be referred to as being made up of multiple components in other contexts. Alternatively, what is described herein as including multiple components may be referred to elsewhere as a single component.

[0032] Additionally, several descriptive terms may be used periodically herein, and it may be helpful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise noted: As used herein, "downstream" and "upstream" are terms that indicate a direction relative to the flow of a fluid, such as a working fluid through a combustor of a turbomachine, or, for example, the flow of air through a combustor, or the flow of coolant through one of the component systems of a turbomachine. The term "downstream" corresponds to the direction of fluid flow, and the term "upstream" refers to the opposite direction of flow. The terms "forward" and "aft" refer to directions, without further specification, with "forward" referring to the forward or compressor end of a turbomachine and "aft" referring to the aft or turbine end of a turbomachine. The term "axial" refers to movement or position parallel to an axis, e.g., the axis of a combustor or turbomachine. The term "radial" refers to movement or position perpendicular to an axis, e.g., the axis of a combustor or turbomachine. In such cases, if a first component is closer to the axis than a second component, the first component is described herein as being "radially inward" or "inboard" of the second component. Conversely, if a first component is farther from the axis than a second component, the first component may be described herein as being "radially outward" or "outboard" of the second component. Finally, the term "circumferential" refers to movement or position about an axis, for example, the circumferential inner surface of a combustion liner or the circumferential inner surface of a casing extending about a combustor. As indicated above, and depending on the context, it will be understood that such terms may be applied in relation to the axis of a combustor or the axis of a turbomachine.

[0033] Furthermore, certain descriptive terms may be used regularly in this specification, as explained below: The terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to imply the position or importance of the individual components.

[0034] The terms used herein are for the purpose of describing particular embodiments only and are not intended to be limiting of the disclosure. As used herein, the singular forms "a," "an," and "the" are intended to include the plural forms unless the context clearly dictates otherwise. It will be further understood that as used herein, the terms "comprises" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. "Optional" or "optionally" means that the subsequently described event may or may not occur, or the subsequently described feature may or may not be present, and that the description includes instances in which the event occurs or the feature is present as well as instances in which the event does not occur or the feature is absent.

[0035] When an element or layer is referred to as "resting," "engaged," "connected," "coupled," or "attached" to another element or layer, it may be directly resting, engaged, connected, coupled, or attached to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as "directly resting," "directly engaged," "directly coupled," "directly coupled," or "directly attached" to another element or layer, there are no intervening elements or layers present. 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 associated listed items. The verb forms of "coupled" and "mounted" may be used interchangeably herein.

[0036] An embodiment of the present disclosure provides a combustor for a gas turbine system. The combustor includes an additively manufactured (AM) combustor body including a one-piece member. The one-piece member includes a combustion liner including a cylindrical portion and a tapered transition section, and may optionally include an aft frame at the aft end of the tapered transition section. A resonator tube is part of the AM combustor body and is configured to damp acoustic pressure oscillations of combustion gases within the combustor. The AM combustor body includes multiple parallel sintered metal layers. The resonator tube includes a body defining a resonator chamber and a resonator tube neck having a first end in fluid communication with the resonator chamber. The second end of the resonator tube is in fluid communication with the annulus (airflow path) or combustion chamber. Additive manufacturing allows the AM combustor body to be formed as a single piece, reducing the cost of the combustor body by eliminating many of the multiple parts and required assembly steps. The AM combustor body also provides a low-cost resonator along the length of the combustion liner, which typically requires very expensive and complex installation. The AM process allows for easy modification and testing of various solutions.

[0037] 1 and 2 illustrate cross-sectional side views of portions of combustors 100, 200 that may employ a resonating tube 186 according to embodiments of the present disclosure. 1 and 2 are initially used to describe exemplary portions of combustors 100, 200. Operation of combustors 100, 200 as part of a gas turbine system 102 is described later herein in connection with FIG. 10.

[0038] FIG. 1 illustrates a cross-sectional side view of a portion of a combustor 100 (disposed within a gas turbine (GT) system 102) in which resonator tubes 186A-F (collectively referred to as resonator tubes 186) according to embodiments of the present disclosure may be used. As shown in FIG. 1 , the combustor 100 for the GT system 102 includes an additively manufactured combustor body 104 including a one-piece member 106 including a cylindrical portion 109 and a combustion liner 108 including a tapered transition section 112 that collectively define a combustion chamber 184. In some embodiments, an aft frame 118 at the aft end of the tapered transition section 112 of the combustion liner 108 may also be formed as part of the additively manufactured combustor body 104. The combustor 100 also includes one or more resonator tubes 186 configured to damp acoustic pressure oscillations of the combustion gases 152 flowing within the combustion chamber 184 of the combustor 100. The resonator tubes 186 may alternatively be known as Helmholtz dampers or resonators. The combustor body 104 may also include at least one axial fuel stage (AFS) injector 116 directed toward the combustion liner 108. Embodiments of the present disclosure may also include a flow sleeve 110 that surrounds at least a portion of the combustion liner 108 and may be integrally formed with the combustor body 104.

[0039] In certain embodiments, the AM combustor body 104 further includes at least one fuel passage 122 extending longitudinally along the flow sleeve 110 from its forward end to the AFS injector 116. The fuel passage 122 may be defined in an external fuel line attached to the combustor body 104 or may be integrally formed with the flow sleeve 110 and thus the combustor body 104, eliminating the need for a separate fuel line attached to the combustor body 104. The AM combustor body 104 may further include a plurality of flow passages 124, e.g., air cooling passages, extending longitudinally at least partially in the combustion liner 108, e.g., the cylindrical portion 109 thereof. In some embodiments, the flow passages 124 may be defined between the cylindrical portion 109 and the flow sleeve 110, or between the transition portion 112 and the aft flow sleeve 110. The flow passages 124 may be annular passages or discrete passages.

[0040] FIG. 2 illustrates a cross-sectional side view of a portion of a combustor 200 (disposed within a gas turbine (GT) system 102) in which a resonator tube 186 according to another embodiment of the present disclosure may be used. This embodiment is substantially similar to the embodiment of FIG. 1 , except that a combustion liner 208 is of unitary construction, omitting a separate flow sleeve. As shown in FIG. 2 , the combustor 200 for the GT system 102 includes an additively manufactured combustor body 204 including a unitary member 206 including a combustion liner 208 including a cylindrical portion 209 and a tapered transition section 212 at an aft end 214 of the cylindrical portion 209, which collectively define the combustion chamber 184. In some embodiments, an aft frame 218 at the aft end of the tapered transition section 212 may also be formed as part of the additively manufactured combustor body 204. The combustor body 204 may also include at least one axial fuel stage (AFS) injector 216 directed toward the combustion liner 208.

[0041] In certain embodiments, the AM combustor body 204 further includes at least one fuel passage 222, e.g., within the cylindrical portion 209, extending longitudinally of the AM combustor body 204 from its forward end to the at least one AFS injector 216. The fuel passage 222 is integrally formed in the unitary combustor body 204, i.e., in a portion radially outer than the cylindrical portion 209 of the combustion liner 108. The AM combustor body 204 may further include a plurality of flow passages 224, e.g., air cooling passages, extending at least partially longitudinally of the combustion liner 208 between the radially outer and inner portions that define the combustion chamber 184.

[0042] As a result of additive manufacturing, the combustor body 104 or 204 has no mechanical connections between the various referenced components (i.e., they are one-piece). Figure 3 shows a schematic cross-sectional view of any portion of the additively manufactured combustor body 104, 204 (hereinafter "AM combustor body 104, 204" or "combustor body 104, 204"). As shown in Figure 3, the AM combustor body 104, 204 includes, for example, multiple parallel sintered metal layers 120 resulting from its additive manufacturing.

[0043] 1 and 2 , the combustor 100, 200 may include a separate head-end fuel nozzle assembly 130 (hereinafter “head-end assembly 130”) coupled to the forward end 132 of the AM combustor body 104, 204. “Separate” indicates that the head-end assembly 130 is not additively manufactured with the combustor body 104, 204. The head-end assembly 130 may include any now known or later developed fuel nozzle assembly for delivering fuel 148 from axially extending fuel nozzles 170 to the primary combustion zone 174. The AFS injectors 116, 216 may include any now known or later developed axial-stage fuel injectors for delivering fuel 148 to the secondary combustion zone 176.

[0044] The combustor body 104, 204 may also include an annulus 175, 275 (which may also be the flow passage 124, 224) surrounding at least a portion of the combustion liner 108, 208. The annulus 175, 275 may be used to cool the combustion liner 108, 208 and / or to direct air 146 for combustion, for example, to the head end assembly 130 or the AFS injectors 116, 216. As shown in FIG. 1 , the annulus 175, 275 may be defined by or radially outwardly of the flow sleeve 110 ( FIG. 1 ) surrounding at least a portion of the combustion liner 108, or, as shown in FIG. 2 , an annular passage (annulus 275) may be defined in at least a portion (i.e., the radially outer portion) of the combustion liner 208.

[0045] 1 , the combustor body 104 may also include an impingement flow sleeve 177 that surrounds the tapered transition portion 112 of the combustion liner 108 and defines an impingement annulus 179 between the impingement flow sleeve 177 and the tapered transition portion 112 of the combustion liner 108. Alternatively, as shown in FIG. 2 , the combustor body 204 may include an impingement annulus 279 defined in the tapered transition portion 212 of the combustion liner 208, i.e., integrally formed during additive manufacturing between a radially inner portion of the transition portion 212 and a radially outer portion of the transition portion 212. The impingement flow sleeve 177 or tapered transition portion 212 may include a plurality of holes 181, 281 to allow air 146 in the casing 166 supplied from the air supply 147, for example, the discharge port of the compressor 144, to enter the impingement annulus 179, 279 and cool the tapered transition portion 112, 212 (and provide air for combustion by the AFS injectors 116, 216).

[0046] 1 and 2 illustrate exemplary combustors 100, 200 that may use the resonator tube 186 according to an embodiment of the present disclosure, the resonator tube 186 may be used in any combustor requiring acoustic attenuation. Thus, the combustors 100, 200 are merely exemplary, and other combustor assemblies may benefit from the resonator tube 186 of the present invention.

[0047] Turning to the details of the resonator tubes 186, FIG. 4 shows a cross-sectional view of an exemplary resonator tube 186, such as the resonator tube 186A of FIGS. 1 and 2, for purposes of illustrating the general structure of each resonator tube 186. As shown in FIG. 4, the resonator tube 186 includes a body 188 defining a resonator chamber 190 and a resonator tube neck 192 having a first end 194 in fluid communication with the resonator chamber 190. The resonator tube neck 192 also includes a second end 196 that can be in fluid communication with different fluid chambers, such as the annulus 175, 275 or the combustion chamber 184, as will be described. The shape and / or size of the resonator chamber 190 and / or neck 192 can vary depending on the location of the tube 186 and the sound to be attenuated. For example, the internal attenuation volume of each resonator chamber 190 can be sized and / or shaped for a particular sound attenuation frequency. Generally, the resonator chamber 190 has a larger width and area than the neck 192.

[0048] While not required in all cases, any resonating chamber 190 described herein may have purge holes 191 providing fluid communication between the air supply 147 and the resonating chamber 190, as shown in FIGS. 4, 6, and 8 for exemplary embodiments. Notably, the purge holes 191 can increase cooling, although other embodiments, such as those shown in FIGS. 5, 7, and 9, may not include the purge holes 191 to eliminate fluid communication. When present, the purge holes 191 increase the cooling effect because cooling air 146 enters the resonating chamber 190 from the air supply 147 through the purge holes 191 and cools the damping volume within the resonating chamber 190. The cooled damping volume exits the resonating chamber 190 through the resonating tube neck 192 and into the annulus 175, 275 or combustion chamber 184. The purge holes 191 also aid in removing unsintered metal powder after additive manufacturing and before operation of the combustor 100, 200.

[0049] The resonator tubes 186 can be used in a variety of different configurations and locations on the combustion liner 108, 208, some examples of which are shown as resonator tubes 186A-F in Figures 1-2. Figures 4-9 show more detailed cross-sectional views of each resonator tube 186A-F.

[0050] 1, 2, and 4, the resonating chamber 190 of the resonating tube 186A is spaced from the exterior 198 of the annulus 175, 275 by the resonating tube neck 192, the second end 196 of which is in fluid communication with the annulus 175, 275. As previously mentioned, the annulus 175 may be formed by the flow sleeve 110 spaced from the combustion liner 108 (dashed line), or the annulus 275 may be formed in the combustion liner 208.

[0051] As shown in FIGS. 1, 2, and 5, the resonator tube 186B is disposed within the annulus 175, 275, i.e., the chamber 190 is within the annulus 175, 275. A first end 194 of the resonator tube neck 192 is in fluid communication with the resonator chamber 190, and a second end 196 of the resonator tube neck 192 is in fluid communication with the combustion chamber 184 within the combustion liner 108, 208. The body 188 of the resonator tube 186B may have angled sidewalls 290 such that the resonator chamber 190 is trapezoidal in cross section to reduce drag or interference with the flow of compressed air 146 within the annulus 175, 275. While shown in FIGS. 1, 2, and 5 as being mounted in the cylindrical portions 109, 209 of the combustion liners 108, 208, it should be understood that the resonator tube 186B may alternatively or additionally be mounted in the tapered transition portions 112, 212.

[0052] As shown in Figures 2 and 6, the impingement annulus 279 is defined in (additively fabricated in) the tapered transition portion 212 of the combustion liner 208, or as shown in Figures 1 and 6, the impingement annulus 179 is defined between the impingement flow sleeve 177 and the tapered transition portion 112 of the combustion liner 108. In the case of the resonator tube 186C, the resonator chamber 190 is on the outside 279 of the impingement annulus 179. That is, as shown in Figure 2, the resonator chamber 190 is on the outside of the tapered transition portion 212 having the impingement annulus 279 therein, or as shown in Figure 1, the resonator chamber 190 is on the outside of the flow sleeve 177 where the impingement annulus 179 is defined between the flow sleeve 177 and the tapered transition portion 112. In any event, the resonator tube neck 192 for the resonator tube 186C formed through the flow sleeve 177 or the radially outer portion of the tapered transition section 212 includes a first end 194 in fluid communication with the resonator chamber 190 and a second end 196 in fluid communication with the impingement annulus 179, 279.

[0053] 1, 2, and 7, the resonating chamber 190 of the resonating tube 186D is located outside the tapered transition portion 212 adjacent the aft frame 118 (FIGS. 2 and 7) or on the impingement flow sleeve 177 surrounding the tapered transition portion 112 of the combustion liner 108 (FIGS. 1 and 7). As described above, the impingement annulus 179 is defined between the tapered transition portion 112 of the combustion liner 108 and the impingement flow sleeve 177. Alternatively, as shown in FIG. 2, the impingement annulus 279 is defined within the tapered transition portion 212 (e.g., between the radially inner and radially outer portions). In either case, the resonator tube neck 192 of the resonator tube 186D includes a first end 194 in fluid communication with the resonator chamber 190 and a second end 196 in fluid communication with the combustion chamber 184 defined by the combustion liner 108, 208. That is, the resonator tube neck 192 extends circumferentially across or around a portion or all of the circumference of the impingement annulus 179, 279. In FIGS. 1 and 2, the resonator chamber 190 of the resonator tube 186D is adjacent to the aft frame 118, 218; that is, its body 188 may be upstream of or share an upstream wall with the aft frame 118, 218. In other embodiments, a portion 292 of the resonator chamber 190 is within the aft frame 118, 218, as shown in FIG. 7.

[0054] 1, 2, and 8, the resonating tube 186E includes a resonating chamber 190 outside the annulus 175, 275. The resonating tube neck 192 includes a first end in fluid communication with the resonating chamber 190 and a second end 196 in fluid communication with the combustion chamber 184 defined by the annulus 108, 208. The resonating tube neck 192 extends across the annulus 175, 275. In this embodiment, the resonating chamber 190 is defined in part by the flow sleeve 110 or the combustion liner 208, such that the flow sleeve 110 or the combustion liner 208 forms a radially inner wall 294 of the body 188 of the resonating tube 186E.

[0055] 1, 2, and 9, the resonating chamber 190 of the resonating tube 186F is outside of the annular portions 175, 275. The resonating tube neck 192 includes a first end in fluid communication with the resonating chamber 190 and a second end 196 in fluid communication with the annular portions 175, 275.

[0056] As shown in Figures 5 and 7-9, a portion of the (radial) inner wall 294 and / or resonator tube neck 192 of the body 188 of the resonator tubes 186B, D-F may be formed with or shared with the structure of the combustor body 104, 204 (Figures 1-2) to which the resonator tube 186 is adjacent. For example, Figure 5 shows the inner wall 294 integral with (and perhaps coplanar with) the cylindrical portion 109, 209 of the combustion liner 108, 208, Figure 7 shows the inner wall 294 integral with (and perhaps coplanar with) the flow sleeve 177 or tapered transition portion 212 of the combustion liner 108 or 208, respectively, and Figures 8 and 9 show the inner wall 294 integral with (and perhaps coplanar with) the flow sleeve 110 (Figure 1) or the outer portion of the combustion liner 208 (Figure 2). 6, the inner wall 294 may be a separate layer or layers of material, such as a sintered metal layer, that thickens the resonator tube 186 from any other structure in the combustor body 104, 204. In FIG. 6, the inner wall 294 is shown as a separate or thickened layer from a portion of the impingement sleeve 177 (FIG. 1) or tapered transition section 212 (FIG. 2).

[0057] It is emphasized that the resonating chamber 190 and / or the resonating tube neck 192 may have any cross-sectional shape and dimensions desired to damp acoustic pressure oscillations of the combustion gases 152 flowing through the combustor 100, 200. For example, while the resonating chamber 190 is shown as having a mostly rectangular cross-section, it may have any shape. For example, FIG. 5 illustrates a resonating chamber 190 having a trapezoidal cross-section, and FIG. 9 illustrates a resonating chamber 190 having rounded corners 296. Other shapes are possible for the resonating chamber 190 and / or the neck 192. The shape may also vary to extend circumferentially around the combustor body 104, 204, i.e., extending into or out of the page, as shown in the drawings. The resonating tube 186 may have any width in the circumferential direction up to and including a full annulus.

[0058] The resonating tube neck 192 may have any dimensions (e.g., length and diameter). As shown in FIG. 4, the resonating tube neck 192 may have a length sufficient to extend radially outward from the flow sleeve 110. Alternatively, as shown in FIGS. 5 and 9, the resonating tube neck 192 may have a length equal to the thickness of the flow sleeve 110 or the portion of the combustion liner 208 with which the resonating tube 186 is integrated. As yet another alternative, as shown in FIGS. 6, 7, and 8, the resonating tube neck 192 may have a length equal to or approximately equal to the distance between the combustion liner 108 and the flow sleeve 110, or the distance between the radially inner and radially outer portions of the combustion liner 208 (i.e., the length spanning the annulus 175, 275). While a single resonating tube neck 192 is shown, it should be understood that additional resonating tube necks 192 in fluid communication with the resonating chamber 190 may be used, particularly in embodiments where the resonating tube 186 has a significant circumferential width.

[0059] It should be noted that, for illustrative purposes only, Figures 1 and 2 show six different types of resonator tubes 186A-F and six different positions of the resonator tubes 186A-F together. In operation, any number of resonator tubes 186A-F may be used, e.g., one, two, three, four, five, six, or more than six. That is, it is not necessary to use all six types and positions of resonator tubes 186A-F shown in Figures 1-2 together. In fact, in most cases, only one style of resonator tube 186A-F will be used, e.g., in one axial position. The different types of resonator tubes 186A-F may be used alone or in any combination. In certain embodiments, at least two resonating tubes are used, and at least one of the two resonating tubes, as described herein, includes: (a) a resonating chamber disposed outside of an annulus surrounding at least a portion of a combustion liner, the annulus being defined by either a flow sleeve surrounding the combustion liner or an annular passage in at least a portion of the combustion liner, the resonating tube neck including a second end in fluid communication with the annulus; (b) a resonating chamber disposed outside of the annulus, the resonating tube neck including a second end in fluid communication with a combustion chamber defined by the combustion liner; (c) a resonating chamber disposed within the annulus, the resonating tube neck including a second end in fluid communication with the combustion chamber; (d) a resonating chamber spaced outside of the annulus by a resonating tube neck, the resonating tube neck including a second end in fluid communication with the annulus; or (e) a resonating chamber disposed outside of one of a tapered transition portion and an impingement flow sleeve surrounding the tapered transition portion.(f) a resonating chamber disposed at least partially within the aft frame, the resonating chamber having a second end in fluid communication with the combustion chamber; (g) a resonating chamber disposed outside the impingement annulus, the resonating tube neck having a second end in fluid communication with the impingement annulus. When at least two resonating tubes are provided, they can be configured to attenuate different frequencies. Furthermore, any number of resonating tubes 186 may be used circumferentially around the combustion liner 108, 208, i.e., in and out of the page of FIGS. 1 and 2, or in a circumferential array of discrete resonating tubes 186.

[0060] 1 and 2, the arrangement and operation of combustors 100, 200 within a GT system 102 will be described. FIG. 10 illustrates a functional block diagram of an exemplary GT system 102 that may incorporate various embodiments of the combustors 100, 200 of the present disclosure. As shown, the GT system 102 generally includes an inlet section 140 that may include a series of filters, cooling coils, water separators, and / or other devices to purify and otherwise condition a working fluid (e.g., air) 142 entering the GT system 102. The working fluid 142 flows to a compressor section 144 that progressively imparts kinetic energy to the working fluid 142 to produce highly energized compressed air 146. The compressed air 146 is mixed with fuel 148 from a fuel supply 150 to form a combustible mixture within one or more combustors 100, 200. The combustion liners 108, 208 of the combustors 100, 200 may contain and channel combustion gases 152 to the turbine section. The combustion liners 108, 208 define a combustion chamber 184 in which combustion occurs. As shown in FIGS. 1 and 2 , the combustion liners 108, 208 may extend between the head end assembly 130 and the aft frame 118, 218. The combustion liners 108, 208 may have a cylindrical portion 109, 209 and a tapered transition portion 112, 212 that is integral with the cylindrical portion 109, 209, i.e., forms an integrated body (or “unibody”) structure.

[0061] The combustible mixture combusts to produce high-temperature, high-pressure combustion gases 152. The combustion gases 152 flow through a turbine 154 (e.g., an expansion turbine) in a turbine section to produce work. For example, the turbine 154 may be connected to a shaft 156, such that rotation of the turbine 154 drives the compressor section 144 to produce compressed air 146. Alternatively, or in addition, the shaft 156 may connect the turbine 154 to a generator 158 to generate electricity. Exhaust gases 160 from the turbine 154 flow through an exhaust section 162 that connects the turbine 154 to an exhaust stack 164 downstream of the turbine 154. The exhaust 162 may include, for example, a heat recovery steam generator (not shown) to scrub the exhaust gases 160 and further extract heat therefrom before they are released to the environment.

[0062] In one embodiment, the GT system 102 may include a model commercially available from GE Vernova of Cambridge, Massachusetts. The present disclosure is not limited to any one particular GT system and may be adapted for use in connection with other engines, including, for example, GE Vernova's HA, F, B, LM, GT, TM, and E-class engine models, as well as engine models from other manufacturers. Furthermore, the present disclosure is not limited to a particular turbomachine and may be applied to, for example, steam turbines, jet engines, compressors, turbofans, etc.

[0063] 1 and 2 , the combustor 100, 200 is at least partially surrounded by an outer casing 166, such as a compressor discharge casing and / or a turbine casing. The outer casing 166 is in fluid communication with the compressor 144, whereby the compressed air 146 enters the combustor body 104, 204 at various locations. An end cover 168 of a head end assembly 130 is coupled to the casing 166 at one end of the combustor 100, 200. The head end assembly 130 generally includes at least one axially extending fuel nozzle 170 extending downstream from the end cover 168 and a cap assembly 172 extending radially and axially within the combustion liner 108, 208 downstream from the end cover 168 to define a forward boundary of the combustion chamber 184. In certain embodiments, axially extending fuel nozzles 170 extend at least partially through cap assembly 172 and deliver a combustible mixture of fuel and compressed air 146 to a primary combustion zone 174 downstream from fuel nozzles 170 to form combustion gases 152.

[0064] The combustion liner 108, 208, also known as a hot gas path duct or unibody liner, extends downstream from the cap assembly 172. In certain embodiments, as shown in FIG. 1 , annular flow sleeve(s) 110 may at least partially surround at least a portion of the combustion liner 108, such as the cylindrical portion 109 and / or the tapered transition section 112. In another embodiment, as shown in FIG. 2 , the flow sleeve is omitted and a one-piece combustion liner 208 is used. In some embodiments, the AFS injectors 116, 216 extend through the liners 108, 208 downstream from the axially extending fuel nozzle(s) 170. In these embodiments, the AFS injectors 116, 216 deliver a combustible mixture of fuel 148 and compressed air 146 to a secondary combustion zone 176 downstream of the primary combustion zone 174 to form combustion gases 152.

[0065] 1 , the flow sleeve(s) 110 define an annulus 175, i.e., a flow passage, for routing the compressed air 146 across the outer surface of the combustion liner 108 (cylindrical portion 109 and / or tapered transition portion 112). Additionally, the flow sleeve(s) 110 may direct at least a portion of the compressed air 146 to one or more radially extending AFS injectors 116 for combining with fuel for combustion in a secondary combustion zone 176 downstream from the primary combustion zone 174. Further, as shown in FIG. 1 , fuel passages 122 within the flow sleeve 110 may supply fuel from a fuel supply 150 to the AFS injectors 116. 2, the combustion liner 208 (cylindrical portion 209 and / or tapered transition portion 212) may define an annulus 275 for channeling compressed air 146 within the combustion liner 208 (cylindrical portion 209 and / or tapered transition portion 212). Additionally, as shown in FIG. 2, a fuel passage 222 in the combustion liner 208 (at its forward end) may supply fuel from the fuel supply 150 to the AFS injector 116.

[0066] Regardless of the combustor embodiment, the combustor 100, 200 generally terminates adjacent a first stage 178 of a stationary nozzle 180 of the turbine 154. The first stage 178 of the stationary nozzle 180 at least partially defines a turbine inlet 182 of the turbine 154. As previously mentioned, the combustion liner 108, 208 at least partially defines a combustion chamber 184 for channeling combustion gases 152 from the primary combustion zone 174 and secondary combustion zone 176 to the turbine inlet 182 of the turbine 154 during operation of the GT system 102.

[0067] During operation, compressed air 146 flows from the compressor 144 and is channeled through the annulus 175, 275. A portion of the compressed air 146 is channeled to the head end assembly 130 of the combustor 100, 200, where it reverses direction and is channeled through the axially extending fuel nozzles 170. The compressed air 146 mixes with fuel to form a first combustible mixture that is injected into the primary combustion zone 174. The first combustible mixture combusts to produce combustion gases 152. A second portion of the compressed air 146 is channeled through the radially extending AFS injectors 116, 216, where it mixes with fuel 148 from the fuel passages 122 in the flow sleeve 110 (FIG. 1), or the fuel passages 222 in the combustion liner 208 (FIG. 2), or from fuel passages radially outward of such structures (not shown), to form a second combustible mixture. The second combustible mixture is injected through the liner 108, 208 into the combustion chamber 184. The second combustible mixture at least partially mixes with the combustion gases 152 and is combusted in the secondary combustion zone 176. The liner 108, 208 defines the combustion chamber 184 for channeling the combustion gases 152 from the primary combustion zone 174 and secondary combustion zone 176 to a turbine inlet 182 of the turbine 154 during operation of the GT system 102. During operation, one or more resonator tubes 186 damp acoustic pressure oscillations of the combustion gases within the combustor 100, 200.

[0068] The combustor body 104, 204, including the resonator tube 186, can be additively manufactured using any now known or later developed technique capable of forming a large, monolithic body. In certain embodiments, as shown in FIG. 3 , the combustor body 104, 204 includes multiple parallel sintered metal layers 120. The material of the combustor body 104, 204 can be, for example, a nickel-chromium-cobalt-molybdenum alloy (NiCrCoMo) (e.g., HA282 or HA233 from Haynes International), a nickel-chromium-molybdenum-niobium alloy (NiCrMoNb) (e.g., Inconel 625 or 718), a nickel-chromium-iron-molybdenum alloy (NiCrFeMo) (e.g., Hastelloy X available from Haynes International), or a nickel-chromium-cobalt-titanium (NiCrCoTi) alloy (e.g., GTD 262 developed by General Electric Company).

[0069] 11 is a schematic / block diagram of an exemplary computerized metal powder additive manufacturing system 310 (hereinafter “AM system 310”) for producing the combustor body 104, 204, of which only a single layer is shown. The combustor body 104, 204 and the resonator tube 186 may advantageously be manufactured as an integrated unit piece. It is emphasized, and will be readily appreciated, that while the teachings of the present disclosure are described in connection with constructing the combustor body 104, 204 using multiple melting beam sources 312, 314, 316, 318, it is equally applicable to constructing the combustor body 104, 204 using any number of melting beam sources.

[0070] In this example, the AM system 310 is configured for direct metal laser melting (DMLM). It is understood that the general teachings of the present disclosure are not limited to selective laser melting (SLM), but are similarly applicable to other forms of metal powder additive manufacturing, such as perhaps other forms of additive manufacturing (i.e., other than metal powder applications). While the layers of the combustor body 104, 204 in the build platform 320 are illustrated in FIG. 11 as circular elements, it is understood that the additive manufacturing process can be readily adapted to produce arbitrarily shaped portions of the combustor body 104, 204 on the build platform 320.

[0071] The AM system 310 generally includes an additive manufacturing control system 330 (“control system”) and an AM printer 332. As will be described, the control system 330 executes a set of computer-executable instructions or code 334 to produce the combustor body 104, 204 using multiple melt beam sources 312, 314, 316, 318. In the illustrated example, the four melt beam sources may include four lasers. However, the teachings of the present disclosure are applicable to any melt beam source, e.g., electron beam, laser, etc. The control system 330 is shown implemented on a computer 336 as computer program code. To this extent, the computer 336 is shown including a memory 338 and / or storage system 340, a processor unit (PU) 344, an input / output (I / O) interface 346, and a bus 348. Additionally, the computer 336 is shown in communication with an external I / O device / resource 350.

[0072] Generally, processor unit (PU) 344 executes computer program code 334 stored in memory 338 and / or storage system 340. While executing computer program code 334, processor unit (PU) 344 can read and / or write data from memory 338, storage system 340, I / O devices 350, and / or AM printer 332. Bus 348 provides a communication link between each component within computer 336, and I / O devices 350 can be any device (e.g., keyboard, pointing device, display, etc.) that allows a user to interact with computer 336.

[0073] Computer 336 is merely representative of various possible combinations of hardware and software. For example, processor unit (PU) 344 may consist of a single processing unit or may be distributed across one or more processing units at one or more locations, e.g., a client and a server. Similarly, memory 338 and / or storage system 340 may reside in one or more physical locations. Memory 338 and / or storage system 340 may be comprised of any combination of various types of non-transitory computer-readable storage media, including magnetic media, optical media, random access memory (RAM), read-only memory (ROM), etc. Computer 336 may consist of any type of computing device, such as an industrial controller, a network server, a desktop computer, a laptop, a handheld device, etc.

[0074] As described above, the AM system 310, and particularly the control system 330, executes code 334 to generate the combustor body 104, 204 including the resonant tube(s) 186. The code 334 may include, among other things, a set of computer-executable instructions 334S (also referred to herein as “code 334S”) for operating the AM printer 332 as a system, and a set of computer-executable instructions 334O (also referred to herein as “code 334O”) for defining each object, such as the combustor body 104, 204 having the resonant tube(s) 186, that is physically generated by the AM printer 332. As described herein, the additive manufacturing process begins with a non-transitory computer-readable storage medium (e.g., memory 338, storage system 340, etc.) that stores the code 334. The set of computer-executable instructions 334S for operating the AM printer 332 may include any now known or later-developed software code capable of operating the AM printer 332.

[0075] The set of computer-executable instructions 334O defining the combustor body 104, 204 with the resonator tube 186 may include a precisely defined 3D model of the combustor body 104, 204 and the resonator tube 186 and may be generated from any of a wide variety of well-known computer-aided design (CAD) software systems, such as AutoCAD®, TurboCAD®, DesignCAD 3D Max, etc. In this regard, the code 334O may include any now known or later developed file format. Furthermore, the code 334O representing the combustor body 104, 204 may be converted between different formats. For example, the code 334O may include a Standard Tessellation Language (STL) file created for 3D Systems' stereolithography CAD program or an Additive Manufacturing File (AMF), an American Society of Mechanical Engineers (ASME) standard that is an Extensible Markup Language (XML)-based format designed to allow any CAD software to describe the shape and configuration of any three-dimensional object to be manufactured by any AM printer. The code 334O representing the combustor body 104, 204 may also be converted into a set of data signals and transmitted, or received as a set of data signals, converted into code, and stored, as needed. The code 334O may be configured to enable the formation of boundaries and interior sections in overlapping field regions as described, according to embodiments of the present disclosure. In either case, the code 334O may be input to the AM system 310 and may come from a part designer, an intellectual property (IP) provider, a design firm, the operator or owner of the AM system 310, or other source. In either case, the control system 330 executes the code 334S and 334O to divide the combustor body 104, 204 into a series of slices that are assembled using the AM printer 332 with successive layers of material.

[0076] The AM printer 332 can include a process chamber 360 sealed to provide a controlled atmosphere for printing the combustor body 104, 204. A build platform 320, upon which the combustor body 104, 204 is / will be built, is disposed within the process chamber 360. Multiple melt beam sources 312, 314, 316, 318 are configured to melt layers of metal powder on the build platform 320 to produce the combustor body 104, 204. While four melt beam sources 312, 314, 316, 318 are illustrated, it is emphasized that the teachings of the present disclosure are applicable to systems employing any number of sources, e.g., one, two, three, or five or more. As understood in the art, each melt beam source 312, 314, 316, 318 can each have a field that includes a non-overlapping field region where it can exclusively melt metal powder, and can include at least one overlapping field region where two or more sources can melt metal powder. In this regard, each melt beam source 312, 314, 316, 318 can generate a respective melt beam that melts the particles for each slice, as defined by reference numeral 334O.

[0077] 11 , melt beam source 312 is shown forming a layer of combustor body 104, 204 in one region using melt beam 362, while melt beam source 314 is shown forming a layer of combustor body 104, 204 in another region using melt beam 362′. Each melt beam source 312, 314, 316, 318 is calibrated by any now known or later developed method. That is, each melt beam source 312, 314, 316, 318 has the expected position of its laser or electron beam correlated with its actual position relative to build platform 320 to provide individual positional corrections (not shown) to ensure its individual accuracy. In one embodiment, each of multiple melt beam sources 312, 314, 316, 318 can generate melt beams, e.g., 362, 362′, having the same cross-sectional dimensions (e.g., shape and size during operation), power, and scan speed.

[0078] 11 , an applicator (or re-coater blade) 370 can create a thin layer of feedstock material 372 that is laid down as a blank canvas upon which each successive slice of the final combustor body 104, 204 is created. Various parts of the AM printer 332 can move to accommodate the addition of each new layer; for example, the build platform 320 can be lowered after each layer, and / or the chamber 360 and / or applicator 370 can be raised. The process can use different feedstock materials in the form of fine-grained metal powders, which can be held in a chamber or powder reservoir 368 accessible by the applicator 370.

[0079] The process chamber 360 is filled with an inert gas, such as argon or nitrogen, and is controlled to minimize or eliminate oxygen. The control system 330 is configured to control the flow of a gas mixture 374 into the process chamber 360 from an inert gas source 376. In this case, the control system 330 may control a pump 380 and / or an inert gas flow valve system 382 to control the content of the gas mixture 374. The flow valve system 382 may include one or more computer-controllable valves, flow sensors, temperature sensors, pressure sensors, etc., capable of precisely controlling the flow of specific gases. The pump 380 may be provided with or without the valve system 382. If the pump 380 is omitted, the inert gas can simply enter a conduit or manifold before being introduced into the process chamber 360. The source of the inert gas 376 can take the form of any conventional source for the material contained therein, such as a tank, reservoir, or other source. Any sensors (not shown) necessary to measure the gas mixture 374 may be provided. The gas mixture 374 may be filtered using a filter 386 in a conventional manner.

[0080] During operation, build platform 320 loaded with metal powder is provided within process chamber 360, and control system 330 controls the flow of gas mixture 374 within process chamber 360 from inert gas source 376. Control system 330 also controls AM printer 332, particularly applicator 370 and melt beam sources 312, 314, 316, 318, to sequentially melt layers of metal powder on build platform 320 to produce combustor body 104 in accordance with embodiments of the present disclosure. While a particular AM system 310 has been described herein, it is emphasized that the teachings of the present disclosure are not limited to any particular additive manufacturing system or method.

[0081] 2, once the combustor body 104, 204 is formed, it may be assembled to other components of the combustor 100 and / or the turbine inlet 254. For example, the head end assembly 130 may be coupled to the forward end of the combustor body 104, 204. The head end assembly 130 may be coupled by any now known or later developed method, such as welding or fasteners. Additionally, the turbine inlet 182 may be coupled to the aft frame 118, 218. The aft frame 118, 218 may be coupled to the turbine inlet 182 by any now known or later developed method, such as welding or fasteners.

[0082] The present disclosure provides various technical and commercial advantages, examples of which are discussed herein. Additive manufacturing allows the AM combustor body to be formed as a single body, reducing the cost of the combustor body by eliminating the multiple parts and many of the required assembly steps. The AM combustor body also provides a low-cost resonator along the length of the combustion liner, which typically requires very expensive and complex installation. The AM process allows for easy modification and testing of various solutions. Furthermore, the resonator tubes can be designed to mitigate different dynamic frequencies within the combustor 100, 200, and the AM process allows the resonator tubes (whether one or multiple frequencies of concern) to be easily incorporated into the combustor body without the need for separate fabrication and bonding, thereby reducing assembly time and inventory of individual resonator tubes.

[0083] Approximate terms used throughout this specification and claims may be applied to modify any quantitative expression that can be permissibly varied without resulting in a change in the basic function to which it relates. Thus, values modified by terms such as "about," "approximately," and "substantially" are not limited to the exact value specified. In at least some instances, approximate terms may correspond to the precision of the instrument used to measure the value. Throughout this specification and claims, range limitations may be combined and / or interchanged. Such ranges are specified and include all subranges contained therein, unless the context or language indicates otherwise. "About" or "approximately," as applied to a particular value in a range, applies to both endpoints and may indicate ±10% of the stated value, unless dependent on the precision of the instrument used to measure the value.

[0084] Corresponding structure, materials, acts, and equivalents of all means- or step-plus-function elements in the following claims are intended to include any structure, material, or acts for performing the function in combination with other claimed elements as specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description, but is not intended to be exhaustive or limiting to the disclosure in the form disclosed. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the present disclosure. The embodiments were chosen and described to best explain the principles of the disclosure and practical application of the technology, and to enable those skilled in the art to understand the disclosure and to contemplate various modifications to the embodiments that may be suited to the particular uses contemplated. [Explanation of symbols]

[0085] 100, 200: Combustor 102: Gas Turbine System / GT System 104, 204: Additively Manufactured Combustor Body / AM Combustor Body 106, 206: Monolithic Component 108, 208: Combustion Liner 109, 209: Cylindrical Section 110: Flow Sleeve 112, 212: Tapered Transition Section 116, 216: Axial Fuel Stage Injector / AFS Injector 118, 218: Aft Frame 120: Multiple Parallel Sintered Metal Layers 122, 222: Fuel Passage 124, 224: Flow Passage 130: Head End Fuel Nozzle Assembly 132: Forward End 140: Inlet Section 142: Working Fluid 144: Compressor Section 146: Compressed Air 147: Air Supply 148: Fuel 150: Fuel Supply 152: Combustion Gas 154: Turbine 156: Shaft 158: Generator 160: Exhaust Gas 162: Exhaust Section 164: Exhaust Stack 166: Casing 168: End Cover 170: Fuel Nozzle 172: Cap Assembly 174: Primary Combustion Zone 175, 275: Annulus 176: Secondary Combustion Zone 177: Impingement Flow Sleeve 178: First Stage 179, 279: Impingement Annulus 180: Stationary Nozzle 181, 281: Holes 182: Turbine Inlet 184: Combustion Chamber 186, 186A, 186B, 186C, 186D, 186E, 186F: Resonator Tube 188: Body 190: Resonator Chamber 191: Purge Holes 192: Resonator Tube Neck 194: First End 196: Second End 198: Outer 214: Rear end 290: Angled sidewall 294: Inner wall 296: Rounded corners 310: Metal powder additive manufacturing system / AM system 312, 314, 316, 318: Melt beam source 320: Build platform 330: Additive manufacturing control system 332: AM printer 334, 334O, 334S: Computer executable instructions or code / Computer program code 336: Computer 338: Memory 340: Storage system 344: Processor unit (PU) 346: Input / output (I / O) interface 348: Bus 350: I / O device 360: Processing chamber 362, 362': Melt beam 368: Accessible chamber 370: Applicator / recoat blade 372: Raw material 374: Gas mixture376: Inert gas 380: Pump 382: Flow valve system 386: Filter

Claims

1. A combustor (100, 200) for a gas turbine system (102), comprising: an additively manufactured (AM) combustor body (104, 204) including a one-piece member (106, 206); The integral member (106, 206) a combustion liner (108, 208) defining a combustion chamber (184) and including a cylindrical portion (109, 209) and a tapered transition portion (112, 212); an aft frame (118, 218) at the aft end (214) of the tapered transition (112, 212) of the combustion liner (108, 208); a resonator tube (186) configured to damp acoustic pressure oscillations of the combustion gases (152) within the combustor (100, 200); Including, The resonating tube (186) includes a body (188) defining a resonating chamber (190) and a resonating tube neck (192) having a first end (194) in fluid communication with the resonating chamber (190); A combustor (100, 200) in which the AM combustor body (104, 204) includes a plurality of parallel sintered metal layers (120).

2. 2. The combustor of claim 1, further comprising an annular portion surrounding at least a portion of the combustion liner, wherein the annular portion is defined by one of a flow sleeve surrounding at least a portion of the combustion liner or an annular passage in at least a portion of the combustion liner.

3. 3. The combustor of claim 2, wherein the resonating chamber is on an exterior side of the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber within the combustion liner.

4. 3. The combustor of claim 2, wherein the resonating chamber is exterior to the annulus, and the resonating tube neck includes a second end in fluid communication with the annulus.

5. 3. The combustor of claim 2, wherein the resonating chamber is disposed within the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber within the combustion liner.

6. 3. The combustor of claim 2, wherein the resonating chamber is spaced from an exterior of the annulus by a resonating tube neck, the resonating tube neck including a second end in fluid communication with the annulus.

7. 2. The combustor of claim 1, wherein the resonating chamber is located outside either of a tapered transition portion adjacent the aft frame and the impingement flow sleeve that surrounds the tapered transition portion of the combustion liner and defines an impingement annulus between the impingement flow sleeve and the tapered transition portion of the combustion liner, and the resonating tube neck includes a second end that is in fluid communication with the combustion chamber within the combustion liner.

8. The combustor (100, 200) of claim 7, wherein a portion (292) of the resonating chamber (190) is within the aft frame (118, 218).

9. further comprising an impingement annulus (179, 279) formed at one of a tapered transition portion (112, 212) of the combustion liner (108, 208) and between the tapered transition portion (112, 212) of the combustion liner (108, 208) and the impingement flow sleeve (177); The resonating chamber (190) is located outside the impingement annulus (179, 279); The combustor of claim 1 , wherein the resonator tube neck comprises a second end in fluid communication with the impingement annulus.

10. The combustor (100, 200) of any of the preceding claims, further comprising a separate head-end fuel nozzle assembly (130) coupled to a forward end (132) of the AM combustor body (104, 204).

11. A gas turbine (GT) system (102), comprising: a compressor section (144); a combustion section operably coupled to the compressor section (144); a turbine section operably coupled to the combustion section; Including, the combustion section includes at least one combustor (100, 200) including an additively manufactured (AM) combustor body (104, 204) including a monolithic member (106, 206); The integral member (106, 206) a combustion liner (108, 208) defining a combustion chamber (184) and including a cylindrical portion (109, 209) and a tapered transition portion (112, 212); an aft frame (118, 218) provided at the aft end (214) of the tapered transition section (112, 212) of the combustion liner (108, 208); a resonator tube (186) configured to damp acoustic pressure oscillations of the combustion gases (152) within the combustor (100, 200); Including, The resonating tube (186) includes a body (188) defining a resonating chamber (190) and a resonating tube neck (192) having a first end (194) in fluid communication with the resonating chamber (190); A GT system (102) in which an AM combustor body (104, 204) includes a plurality of parallel sintered metal layers (120).

12. 12. The GT system of claim 11, further comprising an annulus surrounding at least a portion of the combustion liner, the annulus being defined by one of a flow sleeve surrounding at least a portion of the combustion liner or an annular passage in at least a portion of the combustion liner.

13. 13. The GT system of claim 12, wherein the resonating chamber is exterior to the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber within the combustion liner.

14. 13. The GT system of claim 12, wherein the resonating chamber is exterior to the annulus, and the resonating tube neck includes a second end in fluid communication with the annulus.

15. 13. The GT system of claim 12, wherein the resonating chamber is disposed within the annulus, and the resonating tube neck includes a second end in fluid communication with the combustion chamber within the combustion liner.

Images