Turbine shroud and turbomachine with cooling circuit

Abstract

To provide a turbine shroud and a turbomachine with a cooling circuit.SOLUTION: The present disclosure provides: a turbine shroud (100) with a cooling circuit (106); and a turbomachine with the subject turbine shroud (100). The turbine shroud (100) includes a body (102) with a structural member thereon. The body (102) is coupled to a turbomachine casing (26, 36) or an intermediate component (50, 101) for coupling the body (102) to the turbomachine casing (26, 36). A cooling circuit (106) within the body (102) is in fluid communication with a cooling chamber (111) adjacent the body (102). The cooling circuit (106) includes: an inlet passage (107, 108) extending through the structural member of the body (102); and an outlet passage (109, 110) fluidly coupled to the inlet passage (107, 108) and extending through an external surface of the body (102).SELECTED DRAWING: Figure 11

Description

[Technical Field]

[0001] The present disclosure relates generally to turbomachines, and more particularly to turbine shrouds. [Background technology]

[0002] Conventional turbomachines, such as gas turbine systems, generate power for electric power utilities. Generally, gas turbine systems generate power by passing a fluid (e.g., hot gas) through turbine components of the gas turbine system. More specifically, inlet air may be drawn into a compressor, compressed, and subsequently mixed with fuel and ignited by a combustor to form the working fluid (e.g., hot gas) of the gas turbine system. The fluid then flows through a fluid flow path to rotate a plurality of rotating blades and a rotor or shaft of the turbine component to generate power. The fluid may be channeled through the turbine component via a plurality of rotating blades and a plurality of stationary nozzles or vanes positioned between the rotating blades. When the plurality of rotating blades rotates the rotor of the gas turbine system, an electric generator coupled to the rotor may generate power from the rotation of the rotor.

[0003] To improve operating efficiency, the rotating blades may include tip shrouds on their radially outer ends. The tip shrouds interact with the inner surface of the stationary casing to channel the working fluid (e.g., hot gases). During operation over the life of the turbomachine, the tip shrouds may weaken due to prolonged exposure to the stresses or temperatures of the rotational forces exerted on the rotating blades.

[0004] In a further embodiment, a turbine shroud may be attached to the stationary casing at a location radially outward of the tips of the rotating blades. The turbine shroud forms an annular ring around the rotating blades. Due to prolonged exposure to high temperatures from the combustion gases, the turbine shroud requires efficient cooling to achieve desired component life. Summary of the Invention

[0005] All aspects, examples, and features described below can be combined in any technically possible manner.

[0006] One aspect of the present disclosure provides a turbine shroud including: a body including a structural member at an upper portion, the body configured to couple to a turbomachine casing; and a cooling circuit within the body and in fluid communication with a cooling chamber defined radially outward of the body, the cooling circuit including an inlet passage extending through the structural member of the body, and an outlet passage fluidly coupled to the inlet passage and extending through an outer surface of the body.

[0007] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the structural member includes ribs on a radially outer surface of the body, and the cooling circuit includes a first plenum extending within the ribs of the body and in fluid communication with the inlet passage.

[0008] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the cooling circuit further includes a second plenum fluidly coupled to the first plenum and within a different structural member of the body, the second plenum fluidly coupling the first plenum to the outlet passage.

[0009] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the inlet passage is shaped to direct cooling air to an underside of the structural member within the first plenum.

[0010] Another aspect of the present disclosure provides any of the aforementioned aspects, further comprising an impingement panel positioned between the structural member of the body and the cooling chamber, the impingement panel including a plurality of impingement holes fluidly coupling the cooling chamber to an inlet passage of the cooling circuit.

[0011] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the impingement panel extends between first and second hooks extending outwardly from the body.

[0012] Another aspect of the present disclosure provides any of the aforementioned aspects, further including an intermediate component disposed between the body and the turbomachine casing, wherein the first hook and the second hook engage with respective recesses in the intermediate component.

[0013] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the first hook and the second hook are configured to engage respective recesses in the turbomachine casing.

[0014] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the body further includes a forward end positioned opposite the aft end, a first sidewall extending between the forward end and the aft end, a second sidewall extending between the forward end and the aft end and opposite the first sidewall, an outer surface extending between the first sidewall and the second sidewall, the outer surface oriented toward the cooling chamber and having a structural member thereon, and an inner surface oriented toward a blade structure and a hot gas path for the turbomachine.

[0015] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the structural members are a first rib and a second rib, each of the first rib and the second rib extending between a forward end and an aft end and including an inlet passage to a respective cooling circuit.

[0016] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the cooling circuit further includes a second plenum fluidly coupled to the first plenum and within a different structural member of the body, the second plenum fluidly coupling the first plenum to an outlet passage defined in one of the forward end or the aft end.

[0017] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the cooling circuit further includes at least two second plenums fluidly coupled to respective first plenums and within different structural members of the body, the at least two second plenums fluidly coupling respective first plenums to outlet passages defined at the forward end and the aft end.

[0018] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the structural member is a first rib extending between the first sidewall and the second sidewall, the first rib defining at least one first plenum in fluid communication with the inlet passage.

[0019] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the cooling circuit further includes a second plenum fluidly coupled to the at least one first plenum and within a different structural member of the body, the second plenum fluidly coupling the at least one first plenum to an outlet passage defined in at least one of the first sidewall or the second sidewall.

[0020] Another aspect of the present disclosure provides a turbomachine including: a blade structure configured to rotate about a rotational axis of a rotor; a turbine shroud oriented toward the blade structure and coupled to a turbomachine casing, the turbine shroud including a body including a structural member at an upper portion, the body coupled to one of the turbomachine casing or an intermediate component for coupling the body to the turbomachine casing; and a cooling circuit within the body and in fluid communication with a cooling chamber adjacent the body, the cooling circuit including an inlet passageway extending through the structural member of the body and an outlet passageway fluidly coupled to the inlet passageway and extending through an exterior surface of the body.

[0021] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the structural member includes ribs on a surface of the body, and the cooling circuit includes a first plenum extending within the ribs of the body and in fluid communication with the inlet passage.

[0022] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the cooling circuit further includes a second plenum fluidly coupled to the first plenum and within a different structural member of the body, the second plenum fluidly coupling the first plenum to the outlet passage.

[0023] Another aspect of the present disclosure provides any of the aforementioned aspects, further comprising an impingement panel positioned between the structural member of the body and the cooling chamber, the impingement panel including a plurality of impingement holes fluidly coupling the cooling chamber to an inlet passage of the cooling circuit.

[0024] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the impingement panel extends between first and second hooks extending outwardly from the body.

[0025] Another aspect of the present disclosure provides any of the aforementioned aspects, wherein the body further includes a forward end positioned opposite the aft end, a first sidewall extending between the forward end and the aft end, a second sidewall extending between the forward end and the aft end and opposite the first sidewall, an outer surface extending between the first sidewall and the second sidewall, the outer surface oriented toward the cooling chamber and having a structural member thereon, and an inner surface oriented toward a blade structure and a hot gas path for the turbomachine.

[0026] Two or more aspects described in this disclosure, including those described in this summary section, may be combined to form an embodiment not specifically described herein, i.e., all embodiments described herein can be combined with each other.

[0027] The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will become apparent from the description and drawings, and from the claims.

[0028] 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 which illustrate various embodiments of the present disclosure. [Brief explanation of the drawings]

[0029] [Figure 1] 1 is a schematic diagram of a gas turbine system according to an embodiment of the present disclosure. [Figure 2A] 2 is a side view of a portion of a turbine of the gas turbine system of FIG. 1 according to a different exemplary configuration. [Figure 2B] 2 is a side view of a portion of a turbine of the gas turbine system of FIG. 1 according to a different exemplary configuration. [Figure 3A] FIG. 2 is an exploded cross-sectional side view of an outer shroud, an inner shroud, and an impingement panel of a turbine shroud according to an embodiment of the present disclosure. [Figure 3B] FIG. 2 is an assembled cross-sectional side view of an outer shroud, an inner shroud, and an impingement panel of a turbine shroud according to an embodiment of the present disclosure. [Figure 3C] FIG. 4 is a cross-sectional side view of an outer shroud, an inner shroud, and an impingement panel of a turbine shroud according to a further embodiment of the present disclosure. [Figure 4] FIG. 2 is a top view of an inner shroud according to some embodiments of the present disclosure. [Figure 5] 5A-5C are various cross-sectional top views of the inner shroud of FIG. 4 including various cooling circuit configurations according to embodiments of the present disclosure. [Figure 6] 5A-5C are various cross-sectional top views of the inner shroud of FIG. 4 including various cooling circuit configurations according to embodiments of the present disclosure. [Figure 7] 5A-5C are various cross-sectional top views of the inner shroud of FIG. 4 including various cooling circuit configurations according to embodiments of the present disclosure. [Figure 8] FIG. 2 is a top view of a turbine shroud according to an embodiment of the present disclosure. [Figure 9] FIG. 9 is a cross-sectional top view of the turbine shroud of FIG. 8 according to an embodiment of the present disclosure. [Figure 10] FIG. 2 is a top view of a turbine shroud according to an embodiment of the present disclosure. [Figure 11] FIG. 11 is a cross-sectional top view of the turbine shroud of FIG. 10 according to an embodiment of the present disclosure. [Figure 12] FIG. 2 is a top view of a turbine shroud according to an embodiment of the present disclosure. [Figure 13]13A-13C are various cross-sectional top views of the turbine shroud of FIG. 12 in various configurations according to embodiments of the present disclosure. [Figure 14] 13A-13C are various cross-sectional top views of the turbine shroud of FIG. 12 in various configurations according to embodiments of the present disclosure. [Figure 15] 13A-13C are various cross-sectional top views of the turbine shroud of FIG. 12 in various configurations according to embodiments of the present disclosure. [Figure 16] 13A-13C are various cross-sectional top views of the turbine shroud of FIG. 12 in various configurations according to embodiments of the present disclosure. [Figure 17] FIG. 4 is a top view of a turbine shroud according to another embodiment of the present disclosure. [Figure 18] 18A-18C are various cross-sectional top views of the turbine shroud of FIG. 17 including various configurations according to embodiments of the present disclosure. [Figure 19] 18A-18C are various cross-sectional top views of the turbine shroud of FIG. 17 including various configurations according to embodiments of the present disclosure. [Figure 20] 18A-18C are various cross-sectional top views of the turbine shroud of FIG. 17 including various configurations according to embodiments of the present disclosure. [Figure 21] FIG. 4 is a top view of a turbine shroud according to another embodiment of the present disclosure. [Figure 22] FIG. 4 is a top view of a turbine shroud according to another embodiment of the present disclosure. [Figure 23A] 1A-1C are cross-sectional side views of several non-limiting embodiments of collection plenums according to various embodiments of the present disclosure. [Figure 23B] 1A-1C are cross-sectional side views of several non-limiting embodiments of collection plenums according to various embodiments of the present disclosure. [Figure 23C] 1A-1C are cross-sectional side views of several non-limiting embodiments of collection plenums according to various embodiments of the present disclosure. [Figure 23D] 1A-1C are cross-sectional side views of several non-limiting embodiments of collection plenums according to various embodiments of the present disclosure. [Figure 23E] 1A-1C are cross-sectional side views of several non-limiting embodiments of collection plenums according to various embodiments of the present disclosure. [Figure 24] FIG. 1 is a schematic block diagram of an exemplary additive manufacturing system for additively manufactured components according to various embodiments of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[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 reference numerals represent like elements between the drawings.

[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 within an exemplary turbomachinery application. In doing so, common industry terminology is used where possible and consistent with its accepted meaning. Unless otherwise noted, such terminology should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that in many cases, a particular component may be referred to using several different or overlapping terms. What may be described herein as being a single component may include, and be referred to in other contexts as consisting of multiple components. Alternatively, what may be described herein as comprising multiple components may be referred to elsewhere as a single component.

[0032] Additionally, several descriptive terms may be used periodically herein, and it will prove useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise stated: As used herein, "downstream" and "upstream" are terms that indicate a direction relative to the flow of a working fluid through a combustor of a turbomachine, or a fluid, such as, for example, the flow of air through a combustor, or a 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 direction opposite to the flow. The terms "forward" and "aft" refer to directions, unless otherwise specified, with "forward" referring to the front or compressor end of the turbomachine and "aft" referring to the rear or turbine end of the turbomachine.

[0033] 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 located closer to the axis than a second component, the first component is referred to herein as being “radially inward” or “inward” of the second component. Conversely, if a first component is located farther from the axis than the second component, the first component may be referred to herein as being “radially outward” or “outward” of the second component. Finally, the term “circumferential” refers to movement or position around an axis, e.g., the circumferential inner surface of a combustion liner or the circumferential interior of a casing extending around a turbine section. As noted above, and depending on the context, it will be understood that such terms can be applied with respect to the axis of a combustor or the axis of a turbomachine.

[0034] Additionally, as described below, certain descriptive terms may be used periodically herein: the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to denote the location or importance of the individual components.

[0035] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit 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 the terms "comprise" and / or "comprising," as used herein, 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 sets thereof. "Optional" or "optionally" means that a subsequently stated event may or may not occur, or that a subsequently stated 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 not present.

[0036] When an element or layer is referred to as "on," "engaged," "connected," "coupled," or "mounted" to another element or layer, it may be directly on, engaged, connected, coupled, or mounted to the other element or layer, or there may be intervening elements or layers. Conversely, when an element is referred to as "directly on," "directly engaged," "directly connected," or "directly coupled" to another element or layer, there are no intervening elements or layers. 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 and all combinations of one or more of the associated listed items. The verb forms of "couple" and "mount" may be used interchangeably herein.

[0037] Embodiments of the present disclosure provide a turbine shroud for a turbine system, and more particularly, a turbine shroud including a plurality of conduits in fluid communication with a multi-stage plenum formed therein. These and other embodiments are described herein with reference to Figures 1-25. However, it will be readily understood by those skilled in the art that the detailed description provided herein is for purposes of illustration and not limitation.

[0038] FIG. 1 illustrates a schematic diagram of an exemplary gas turbine system 10. The gas turbine system 10 may include a compressor 12 that compresses an incoming flow of air 18 and delivers a flow of compressed air 20 to at least one combustor 22 of the gas turbine system 10. The combustor 22 mixes the flow of compressed air 20 with a flow of pressurized fuel 24 and ignites the mixture to generate a flow of combustion gases 26. The flow of combustion gases 26 is then delivered to a turbine 28 (e.g., an expansion turbine) that typically includes a plurality of turbine blades having one or more airfoils (see FIG. 2 ) that are driven by the flow of combustion gases 26 to generate mechanical work. This mechanical work drives the compressor 12 via a rotor 30 that extends through the turbine 28, which may be used to drive an external load 32, such as an electrical generator.

[0039] The gas turbine system 10 may further include an exhaust frame 34 positioned adjacent to (i.e., downstream of) the turbine 28 of the gas turbine system 10 and positioned to receive the flow of the combustion gases 26 after expansion of the combustion gases 26 in the turbine 28. As described herein, a portion of the exhaust frame 34 (e.g., an outer casing) may be directly coupled to an enclosure, shell, or casing 36 of the turbine 28.

[0040] After the combustion gases 26 flow to drive the turbine 28, the combustion gases 26 may be exhausted and / or discharged in a flow direction (D) through an exhaust frame 34. In the non-limiting example shown in Figure 1, the combustion gases 26 may flow in a flow direction (D) through the exhaust frame 34 and may be discharged from the gas turbine system 10 (e.g., to the atmosphere). In another non-limiting example in which the gas turbine system 10 is part of a combined cycle power plant (e.g., including a gas turbine system and a steam turbine system), the combustion gases 26 may be discharged from the exhaust frame 34 and flow in a flow direction (D) into a heat recovery steam generator of the combined cycle power plant.

[0041] 2A and 2B, a portion of the turbine 28 is shown in an alternative configuration. 2A and 2B each illustrate a side view of a portion of the turbine 28 including turbine blades 38 (one shown) coupled to the rotor 30 and stator vanes 40 (one shown) coupled to the casing 36 of the turbine 28. As described herein, the turbine blades 38 and stator vanes 40 may be arranged in multiple stages, e.g., a first stage, a second stage, and a third stage. Each stage may include multiple turbine blades 38 coupled to and positioned circumferentially around the rotor 30 and capable of being driven by the combustion gases 26 to rotate the rotor 30. Similarly, each stage may include multiple stator vanes 40, which may be coupled to and positioned circumferentially around the casing 36 of the turbine 28. In the non-limiting example herein, the stator vanes 40 may include an outer platform 42 positioned adjacent to and / or coupling the stator vanes 40 to the casing 36 of the turbine 28, an inner platform 44 positioned opposite the outer platform 42, and an airfoil 45 positioned between the outer platform 42 and the inner platform 44. The outer platform 42 and the inner platform 44 of the stator vane 40 may define a flowpath (FP) for the combustion gases 26 flowing over the stator vane 40.

[0042] Each turbine blade 38 of the turbine 28 may include an airfoil 46 extending radially from the rotor 30 and positioned in the flowpath (FP) of the combustion gases 26 flowing through the turbine 28. Each airfoil 46 may include a tip portion 48 positioned radially opposite the rotor 30. The turbine blades 38 and stator vanes 40 may also be positioned axially adjacent to one another within the casing 36. In the non-limiting example shown in FIG. 2 , the stator vanes 40 may be positioned axially adjacent to and downstream from the turbine blades 38. Some turbine blades 38, stator vanes 40, and / or portions of the rotor 30 of the turbine 28 are omitted for clarity of illustration. Additionally, although only a portion of the turbine blades 38 and stator vanes 40 of the turbine 28 are shown in FIG. 2 , the turbine 28 may include multiple stages of turbine blades and stator vanes positioned axially throughout the casing 36 of the turbine 28.

[0043] The turbine 28 (see FIG. 1 ) of the gas turbine system 10 may also include a plurality of turbine shrouds 100. For example, the turbine 28 may include a circumferential array (one shown) of turbine shrouds 100. The turbine shroud 100 may correspond to the turbine blades 38 and / or stator vanes 40. That is, as described herein, the turbine shroud 100 may be positioned within the turbine 28 adjacent to (i.e., radially outward of) the turbine blades 38 and / or stator vanes 40 and interact with and provide a seal with the flowpath (FP) of the combustion gases 26 flowing through the turbine 28. In the non-limiting example shown in FIG. 2 , the turbine shroud 100 may be positioned radially adjacent to and / or substantially surround or encircle the turbine blades 38. The turbine shroud 100 may be positioned radially adjacent to the tip portions 48 of the airfoils 46 for the turbine blades 38. Additionally, the turbine shroud 100 may also be positioned axially adjacent to and / or upstream of the stator vanes 40 of the turbine 28 (ie, between the turbine blades 38 and the stator vanes 40).

[0044] Similar to the stator vanes 40, the turbine shroud 100 may include multiple turbine shrouds 100, each of which may be coupled to and positioned circumferentially around the casing 36 of the turbine 28. In one example shown in FIG. 2A , the turbine shroud 100 may be coupled to the casing 36 of the turbine 28 via a coupling element 50 extending radially inward from the casing 36. The coupling element 50 may be configured to couple to and / or receive fasteners or hooks on the turbine shroud 100 to couple, position, and / or secure the turbine shroud 100 to the casing 36 of the turbine 28. In the example of FIG. 2A , the coupling element 50 may be coupled to and / or secured to the casing 36 of the turbine 28. In another example shown in FIG. 2B , the coupling element 50 ( FIG. 2A ) is omitted, and the turbine shroud 100 is directly coupled to the casing 36. Similar to the turbine blades 38 and / or stator vanes 40, although only a portion of the turbine shrouds 100 of the turbine 28 are shown in FIG. 2, the turbine 28 may include multiple stages of turbine shrouds 100 positioned axially throughout the casing 36 of the turbine 28.

[0045] Further details regarding turbine shrouds and gas turbine systems generally can be found in US Pat. No. 10,837,315 (Application Serial No. 16 / 170,331), which is incorporated herein by reference in its entirety.

[0046] 3A and 3B illustrate exploded and assembled cross-sectional views, respectively, of a turbine shroud 100 according to an embodiment of the present disclosure. As shown, the turbine shroud 100 includes a body 102 coupled to an intermediate component 101. The turbine shroud 100 may further include an impingement panel 200 coupled to the body 102, for example, such that the impingement panel 200 is between the body 102 and the intermediate component 101. The turbine shroud 100 may include various cooling circuits extending within the body 102, the intermediate component 101, and / or the impingement panel 200.

[0047] As shown, the intermediate component 101 includes a component body 103. The component body 103 may be configured to be coupled to the body 102 by one or more mechanical fasteners, hooks, or the like. The component body 103 may be coupled to the casing 36 ( FIG. 2A ). During operation, the component body 103 may be in fluid communication with a cooling fluid (e.g., air, coolant, etc.), thereby transmitting the cooling fluid to the body 102 of the turbine shroud 100. For example, as further shown in FIG. 3A , the component body 103 includes a component cooling circuit 105 extending therein. The component cooling circuit 105 includes an inlet passage 107 extending through one or more exterior surfaces of the intermediate component 101 (e.g., a feedhole). The inlet passage 107 may be oriented axially or substantially axially relative to the rotational axis of the turbomachine. The component cooling circuit 105 includes an outlet passage 109 in fluid communication with the inlet passage 107. The outlet passage 109 may be oriented in any direction, for example, radially inward relative to the axis of rotation. As further shown, the outlet passage 109 includes a portion adjacent the body 102 of the turbine shroud 100 that defines a cooling chamber 111 adjacent the body 102. During operation, a cooling fluid (e.g., compressed air 20 ( FIG. 1 ) from the compressor 12 ( FIG. 1 ) of the gas turbine system 10 ( FIG. 1 )) enters the cooling chamber 111 through the inlet passage 107 of the component cooling circuit 105. As described further herein, the cooling fluid may collect in the cooling chamber 111 and subsequently flow through the impingement panel 200 and through the cooling circuit 106 that extends into the body 102.

[0048] 3C illustrates a further example in which the body 102 and / or impingement panel 200 are directly coupled to a casing 36 having an inlet passageway 107, an outlet passageway 109, and / or a cooling chamber 111 at least partially defined therein. In this case, the intermediate component 101 may be omitted entirely, as the body 102 is directly coupled to the interior of the casing 36 via one or more fasteners, hooks, mechanical components, adhesives, etc. Regardless of whether the intermediate component 101 is present, the body 102 and portions thereof may be provided in accordance with any embodiment described herein.

[0049] 3A-3C together, the turbine shroud 100 may extend axially between a leading end 115 and an aft end 117 and may extend circumferentially between a first sidewall 126 and a second sidewall 128. The leading end 115 may be positioned upstream of the aft end 117 such that the combustion gases 26 flowing through a flowpath (FP) defined within the turbine 28 may flow past the adjacent leading end 115 before flowing past the adjacent aft end 117 of the turbine shroud 100.

[0050] During operation of the gas turbine system 10, a cooling fluid (e.g., air, coolant) flows through one or more cooling circuits to dissipate heat from the turbine shroud 100. As described herein, the cooling fluid may flow through the casing 36, the intermediate component 101, the impingement panel 200, the body 102, and / or an outer surface of the body 102 of the turbine shroud 100.

[0051] Optionally, the impingement panel 200 may be coupled to the body 102. In this case, the impingement panel 200 may channel cooling fluid (e.g., air) from the cooling chamber 111 in individual jets that impinge (or impact) on the body 102. As shown in FIG. 3A , the impingement panel 200 may be spaced radially outward from the radially outer surface 112 of the body 102 along the radial direction R. The impingement panel 200 may include a first surface 202 positioned opposite a second surface 204. The first surface 202 and the second surface 204 may be radially separated by a distance that defines a radial thickness therebetween. The first surface 202 may face the casing 36 and / or the intermediate component 101 and may be configured to partially define the cooling chamber 111. The second surface 204 may face the body 102 and be configured to partially define the air chamber 113 therebetween. The air chamber 113 may be positioned radially between the second surface 204 and the body 102. The impingement panel 200 may extend axially and / or circumferentially between two or more surfaces of the body 102 and / or the intermediate component 101. For example, the impingement panel 200 may extend between a pair of fasteners / hooks 116, 118 that extend radially outward from the body 102 relative to the axis of rotation of the turbomachine.

[0052] The impingement panel 200 may further include a plurality of impingement holes 206 extending radially through the first surface 202 and the second surface 204. Each impingement hole 206 may be sized and oriented to direct cooling fluid in an individual jet that impinges on one or more surfaces of the radially inner body 102 of the turbine shroud 100. The individual jets of air impinge (or impact) on the surfaces of the inner body 102 of the turbine shroud 100, forming a thin boundary layer of air over these surfaces and increasing heat transfer between the turbine shroud 100 and the air. Each impingement hole 206 may include an inlet formed in the first surface 202 and an outlet formed in the second surface 204 of the impingement panel 200. The one or more outlets for the plurality of impingement holes 206 may partially define the air chamber 113.

[0053] Further details regarding impingement panels for gas turbine systems generally can be found in US Pat. No. 11,371,702 (US Application Serial No. 17 / 007,068), which is incorporated herein by reference in its entirety.

[0054] During operation of the gas turbine system 10, cooling fluid flows from the cooling chamber 111 through the impingement panel 200 via the plurality of impingement holes 206 and then impinges on the body 102. After the cooling fluid impinges on the body 102, the cooling fluid collects in the air chamber 113 and then flows through the cooling circuits 106 of the body 102 that extend into the body 102.

[0055] As further shown in FIG. 4 , the body 102 extends axially between a forward end 115 and an aft end 117. The body 102 may include various ends, sides, and / or surfaces. For example, the body 102 may include a first sidewall 126 extending opposite a second sidewall 128. The first sidewall 126 and / or the second sidewall 128 may extend and / or be formed between the forward end 115 and the aft end 117. In some embodiments, the first sidewall 126 and / or the second sidewall 128 may be substantially closed and / or may include solid end walls or caps. Thus, during operation, the solid end walls of the first sidewall 126 and / or the second sidewall 128 may substantially prevent fluids within the turbine 28 (e.g., combustion gases 26, cooling fluid) from entering the turbine shroud 100 and / or the cooling fluid from exiting an interior portion (e.g., a passageway, a plenum) formed within the turbine shroud 100 via the first sidewall 126 and / or the second sidewall 128. In other embodiments, the first sidewall 126 and / or the second sidewall 128 include one or more outlet passageways (e.g., one or more exhaust holes) that extend through one or more exterior portions of the turbine shroud 100. Thus, during operation, the cooling fluid may be exhausted from the turbine shroud 100 via the one or more exhaust holes formed therein to cool one or more exterior portions of the body 102 and / or surrounding components of the gas turbine system 10.

[0056] 3A, 3B, 3C, and 4 together, the body 102 can further include one or more fasteners / hooks extending radially outward from one or more exterior portions thereof. For example, the body 102 may include a first hook 116 positioned at the forward end 115 and a second hook 118 positioned at the aft end 117. The first hook 116 and / or the second hook 118 may be configured to couple to and / or engage with the casing 36 or the intermediate component 101 to couple, position, and / or secure the body 102 to the casing 36 or the intermediate component 101. As shown, the first hook 116 and the second hook 118 extend radially outward from the outer surface 112 of the body 102. In an exemplary embodiment, the first hook 116 may be oriented axially forward, and the second hook 118 may be oriented axially aft. Other orientations are also possible.

[0057] The body 102 may further include various structural members on its outer surface. As used herein, the term "structural member" refers to any load-bearing component of the turbine shroud 100 and / or body 102 for structurally supporting and / or otherwise mechanically engaging other portions of the turbomachine structure. In various examples, the structural member may include one or more ribs on various surfaces of the body 102, sidewalls of the body 102 for structurally supporting adjacent components and / or other components coupled to the body 102, mechanical fastening elements (e.g., hooks 116, 118 described herein), and / or other mechanical members for coupling the body 102 to other components, such as the intermediate component 101 and / or the casing 36. While examples of ribs 124 are used herein to describe features and / or subcomponents formed within the structural members, as shown in FIGS. 4-23 , it is understood that any reference to ribs 124 may be substituted for any or all types of structural members in various further embodiments. Structural members, such as ribs 124, may form part of and / or be positioned on the outer surface 112. The ribs 124, as described above, may provide structural support to the body 102 against shroud deflection during operation of the turbine machine. However, the presence of the ribs 124 or other structural members also creates additional mass that may be subject to significant heat transfer during operation.

[0058] Embodiments of the present disclosure include features for cooling the body 102 and interconnected components via the ribs 124 (or other structural members) while maintaining the presence and structural benefits of the ribs 124 (or other structural members) within the body 102. The ribs 124, or any other structural members, may protrude radially outward from the outer surface 112. In some implementations, the ribs 124 may extend axially between the forward end 115 and the aft end 117, as shown in FIGS. 4-17. In other implementations, the ribs 124 may extend circumferentially between the first sidewall 126 and the second sidewall 128, as shown in FIGS. 18-23. In some implementations, the inner body 102 includes a plurality of ribs 124 positioned on the outer surface 112. The plurality of ribs 124 may extend circumferentially and / or axially along the outer surface 112. For example, in the top view of the body 102 of the turbine shroud 100 shown in FIG. 4, the body 102 includes a plurality of structural members in the form of a plurality of ribs 124 positioned on the outer surface 112, each extending axially between the first hook 116 and the second hook 118.

[0059] The outer surface 112 may be formed and / or positioned between the forward end 115 and the aft end 117 and between the first sidewall 126 and the second sidewall 128, respectively. During operation, the outer surface 112 may be positioned with, form, face, and / or be in fluid communication with a cooling chamber 111 formed between the body 102 and the casing 36 or intermediate component 101. As described herein, the cooling chamber 111 may receive and / or provide cooling fluid to the turbine shroud 100 during operation of the turbine 28. For example, the body 102 may include a cooling circuit 106 extending within the body 102 and in fluid communication with the cooling chamber 111.

[0060] As shown in FIGS. 3A-3C , the turbine shroud 100 includes a cooling circuit 106 that may include an inlet passage 108 extending through an outer surface 112 and fluidly connected to an outlet passage 110 extending through one or more outer surfaces of the body 102. The inlet passage 108 may extend in a predetermined direction (e.g., radially or substantially radially) through ribs 124 (or other structural members) of the body 102 (e.g., the same direction as the radial direction R, e.g., the axis of rotation of the turbomachine). The outlet passage 110 may extend in a predetermined direction (e.g., axially or substantially axially) through one or more outer surfaces of the body 102. During operation, cooling fluid flows through the inlet passage 108, through one or more plenums 120, 122 of the cooling circuit 106, and is exhausted through the outlet passage 110. While the inlet passage 108 and the outlet passage 110 are introduced above as a single item, it should be understood that multiple inlet passages 108 and multiple outlet passages 110 may be used. The plurality of inlet passages 108 may be different in number from the plurality of outlet passages 110 .

[0061] Referring now to Figure 4, a top view of the body 102 of the turbine shroud 100 is shown, according to some embodiments of the present disclosure. A portion of the body 102 extends between a forward end 115 and an aft end 117, as described above with reference to Figures 1, 2, 3A, 3B, and 3C, and redundant details of which have been omitted with reference to Figures 4-22 for the sake of brevity. The body 102 extends axially between the forward end 115 and the aft end 117 and includes a cooling circuit 106 (Figures 5-7) that includes an inlet passage 108 extending radially through the outer surface 112.

[0062] 5-7 illustrate various configurations of the cooling circuit 106 for the body 102 of FIG. 4, according to some embodiments of the present disclosure.

[0063] FIG. 5 shows a cross-sectional top view of the cooling circuit 106 according to a further embodiment. The inlet passages 108 are in fluid communication with first plenums 120 extending into the respective structural members. According to one example, the first plenums 120 may be “rib plenums” in which each plenum 120 extends into one rib 124. As shown, the cooling circuit 106 includes inlet passages 108 that extend through one of the first and second ribs 124 and into the respective first plenums 120. The inlet passages 108 may extend radially or substantially radially through the ribs 124 (or other structural members) into the body 102. During operation, cooling fluid flows from the cooling chamber 111 through the impingement panel 200, through the inlet passages 108, and into the plenums 120. The cooling fluid from the first plenums 120 flows into one or more second plenums 122 extending into the body 102. Each second plenum 122 may be defined within another structural element of the body 102 (i.e., within a structure other than the ribs 124). For example, the second plenums 122 are shown as being defined within the hooks 116, 118. In further embodiments, the second plenums 122 may be within various structural elements other than the ribs 124.

[0064] In some embodiments, the cooling circuit 106 includes one or more second plenums 122 in fluid communication with the first plenum 120. One or more inlets may be formed in fluid communication with the first plenum 120, and one or more outlets may be formed in fluid communication with the one or more second plenums 122. As shown, the second plenums 122 are fluidly coupled between the outlet passages 110 and the one or more first plenums 120 that extend into the ribs 124 (or other structural members). In some embodiments, for example, the second plenum 122 extends partially into at least one of the leading edge (i.e., the edge of the body 102 facing the incoming working fluid flow) or the trailing edge (i.e., the edge of the body 102 facing away from the incoming working fluid flow), the first sidewall 126, and the second sidewall 128 of the body 102. In some implementations, cooling circuit 106 includes one or more collection plenums that extend in a predetermined direction within body 102 (eg, circumferentially relative to the rotor axis).

[0065] In some embodiments, the cooling fluid may flow through and / or be exhausted from one or more exhaust holes in one or more outer surfaces of the turbine shroud 100. It should be understood that the formation and / or location of the exhaust holes in the turbine shroud 100 is exemplary and non-limiting. The exhaust holes, which may be formed in or through various portions of the turbine shroud 100, define the termination of the outlet passage 110. The cooling fluid may be discharged through the one or more exhaust holes and enter spaces formed between circumferentially adjacent turbine shrouds 100 and / or be used to cool circumferentially adjacent turbine shrouds 100 or other axially adjacent turbine components.

[0066] As further shown in Figure 5, the outlet passages 110 may be partially defined within, and thus extend through, the edges of the body 102. For example, as shown in Figure 5, the outlet passages 110 may include multiple outlet passages 110 partially defined within and / or extending through various edges of, the body 102. Arrows indicate the flow of cooling air exhausted from the body 102 through the outlet passages 110.

[0067] In some embodiments, the cooling circuit 106 includes an outlet passage 110 partially defined within the leading edge at the leading end 115 of the body 102, such that the outlet passage 110 extends through the leading edge surface of the body 102. The cooling circuit 106 further includes an outlet passage 110 partially defined within the trailing edge at the aft end 117 of the body 102, such that the outlet passage 110 extends through the trailing edge surface of the body 102. The cooling circuit 106 further includes an outlet passage 110 partially defined within the first sidewall 126 and the second sidewall 128 of the body 102, such that the outlet passage 110 extends through the respective sidewall surfaces of the body 102.

[0068] Figures 6 and 7 each show a cross-sectional view of a different embodiment of the body 102 of Figure 4. The body 102 shown in Figures 6 and 7 is substantially similar to the body 102, except for a different configuration of the cooling circuit 106 extending therethrough.

[0069] 6 shows the cooling circuit 106 including a second plenum 122 extending below the first hook 116 and proximate the forward end 115, and a second plenum 122 extending below the second hook 118 and proximate the aft end 117. In contrast to the body 102 of FIG. 5, the body 102 of FIG. 6 does not include a plenum 122 extending within or along the first sidewall 126 or the second sidewall 128.

[0070] 7 shows the cooling circuit 106 including a second plenum 122 extending below the second hook 118 and proximate the aft end 117. The cooling circuit 106 further includes an outlet passage 110 that fluidly couples the rib 124 (or other structural member) with the leading edge surface at the forward end 115. In contrast to the inner shroud 102 of FIGS. 5 and 6, the body 102 of FIG. 7 does not include the second plenum 122 extending within or along the first sidewall 126 or the second sidewall 128 or below the first hook 116.

[0071] 8 and 9 illustrate various views of another non-limiting example of the body 102 of the turbine shroud 100 according to an embodiment of the present disclosure. The non-limiting example of the body 102 illustrated in Figures 8 and 9 may include similar features as described herein with respect to Figures 4-7, oriented and / or positioned in a different manner.

[0072] FIG. 8 illustrates a top view of a turbine shroud 100 including a body 102 extending axially between a forward end 115 and an aft end 117. The body 102 extends between a first sidewall 126 and a second sidewall 128 and includes an outer surface 112 positioned opposite an inner surface 114 configured to face a hot gas path (FP, FIGS. 2A and 2B ) of the gas turbine system 10 (see FIGS. 3A and 3B ). As shown, the body 102 includes a pair of ribs 124 (optionally along with other structural members) extending axially between the forward end 115 and the aft end 117. The inlet passages 108 of the cooling circuit 106 include a first set of inlet passages 108 axially separated from a second set of inlet passages 108 (i.e., the first set is adjacent the forward end 115 and the second set is adjacent the aft end 117).

[0073] FIG. 9 illustrates a cross-sectional top view of the body 102 of FIG. 8. As shown, the second circuit 106 includes four first plenums 120 extending within a pair of ribs 124 and fluidly communicating with the cooling chamber 111 by way of the inlet passages 108. Each of the four first plenums 120 illustrated in FIG. 9 is fluidly isolated from the other first plenums 120 extending within the body 102. In this embodiment, each first plenum 120 is fluidly connected to a corresponding second plenum 122 extending below the first hook 116 or the second hook 118, as applicable. The outlet passages 110 are partially defined within the body 102 proximate the forward end 115 or the aft end 117, as previously described herein with respect to FIGS. 4-7. During operation, cooling fluid flows from cooling chamber 111 through impingement panel 200, through inlet passage 108, through plenum 120, through plenum 122, and through outlet passage 110. It should be understood that alternative configurations for cooling circuit 106 are contemplated within the scope of this disclosure.

[0074] 10 and 11 illustrate various views of another non-limiting example of the body 102 of the turbine shroud 100 according to an embodiment of the present disclosure. The non-limiting example of the body 102 illustrated in Figures 10 and 11 may include similar features as described herein with respect to Figures 4-9, oriented and / or positioned in a different manner.

[0075] 10 illustrates a top view of a turbine shroud 100 including a body 102 extending between a forward end 115 and an aft end 117. The body 102 extends between a first sidewall 126 and a second sidewall 128 and includes an outer surface 112 positioned opposite an inner surface 114 configured to face a hot gas path for the turbomachine (see FIGS. 3A and 3B ). As shown, the body 102 includes a pair of ribs 124 extending axially between the forward end 115 and the aft end 117. An inlet passage 108 of a cooling circuit 106 extends axially along a portion of the ribs 124 and radially through a portion of the ribs 124.

[0076] FIG. 11 illustrates a cross-sectional top view of the body 102 of FIG. 10. As illustrated, each rib 124 includes one first plenum 120 extending internally between the outer surface 112 and the inner surface 114. Each first plenum 120 is coupled to one second plenum 122 extending circumferentially within the body 102 below the first hook 116 proximate the leading edge at the forward end 115. Each first plenum 120 is fluidly isolated from the other first plenums 120, and each second plenum 122 is fluidly isolated from the other second plenums 122. One or more outlet passages 110 are partially defined within the body 102 proximate the forward end 115, as previously described herein with respect to FIGS. 4-9. It should be understood that alternative configurations for the cooling circuit 106 are contemplated within the scope of the present disclosure.

[0077] 12-16 illustrate various views of other non-limiting examples of the body 102 of the turbine shroud 100 according to embodiments of the present disclosure. The non-limiting examples of the body 102 illustrated in Figures 12-16 can include similar features as described herein with respect to Figures 4-11 oriented and / or positioned in different ways.

[0078] 12 illustrates a top view of the body 102 extending axially between a forward end 115 and an aft end 117 and extending circumferentially between a first sidewall 126 and a second sidewall 128. The body 102 includes an outer surface 112 extending between the first sidewall 126 and the second sidewall 128 and positioned opposite an inner surface 114 facing a hot gas flow path for the turbomachine (see FIGS. 3A and 3B ). As shown, the body 102 includes a pair of ribs 124 (which may be replaced by or comprise other structural members) extending axially between the forward end 115 and the aft end 117. An inlet passage 108 of the cooling circuit 106 extends axially along a portion of the ribs 124 and radially through a portion of the ribs 124.

[0079] 13-16 show various configurations of the cooling circuit 106 for the body 102 of FIG.

[0080] FIG. 13 illustrates a cross-sectional top view of the body 102 of FIG. 12 , according to one embodiment. As shown, each rib 124 (or other structural member) includes one first plenum 120 extending internally between the outer surface 112 and the inner surface 114. Each first plenum 120 is coupled to one second plenum 122 extending circumferentially within the body 102. One or more outlet passages 110 are partially defined within the body 102, as previously described herein with respect to FIGS. 4-11 . In this embodiment, two cooling circuits 106 are provided, each including one first plenum 120 fluidly coupled to a respective second plenum 122, which extends below the second hook 118 at the trailing edge proximate the aft end 117.

[0081] FIG. 14 illustrates a cross-sectional top view of the body 102 of FIG. 12 according to another embodiment. As shown, each rib 124 includes one first plenum 120 extending internally between the outer surface 112 and the inner surface 114. Each first plenum 120 is coupled to a respective second plenum 122 extending circumferentially within the body 102. One or more outlet passages 110 are partially defined within the body 102, as previously described herein with respect to FIGS. 4-13. The outlet passages 110 may be fluidly coupled to the second plenums 122, or alternatively, may be fluidly coupled directly to the first plenums 120. In this embodiment, the cooling circuit 106 includes two second plenums 122 extending below the second hook 118 at the trailing edge proximate the aft end 115. The body 102 further includes an additional cooling circuit 130 extending through an exterior surface of the second hook 118 proximate the aft end 117. The additional cooling circuit 130 may include cooling passages extending through one or more of the first hook 116, the second hook 118, the first sidewall 126, and / or the second sidewall 128. For example, FIG. 15 shows a cross-sectional top view of the body 102 of FIG. 12 according to another embodiment. As shown, the additional cooling circuit 130 includes cooling passages extending through the first sidewall 126, the second sidewall 128, and the first hook 116.

[0082] Figure 16 illustrates a cross-sectional top view of another configuration of the cooling circuit 106 for the body 102 of Figure 12. As shown, the cooling circuit 106 further includes two additional first plenums 120 that are also coupled to the cooling chamber 111 but are fluidly isolated from the other first plenums 120. These additional first plenums 120 are in fluid communication with the outlet passages 110 that extend through the leading edge surface proximate the forward end 115.

[0083] It should be understood that alternative configurations for the cooling circuit 106 are contemplated within the scope of this disclosure.

[0084] 17-20 illustrate various views of another non-limiting example of a body 102 for a turbine shroud 100. The non-limiting example of the body 102 illustrated in FIGS. 17-20 may include similar features as described herein with respect to FIGS. 4-16 , oriented and / or positioned in a different manner. FIG. 17 illustrates a top view of the turbine shroud 100 including ribs 124 extending circumferentially between a first sidewall 126 and a second sidewall 128. FIG. 18 illustrates a cross-sectional top view of the body 102 of FIG. 17 , according to one embodiment. As illustrated, the turbine shroud 100 includes a cooling circuit 106 extending within the body 102 between the forward end 115 and the aft end 117. The cooling circuit 106 includes a first plenum 120 extending circumferentially within the ribs 124 between the first sidewall 126 and the second sidewall 128. The first plenum 120 is fluidly coupled to a second plenum 122 that extends between the forward end 115 and the aft end 117. The cooling circuit 106 exhausts through outlet passages 110 in the first sidewall 126 and the second sidewall 128. FIG. 19 shows a cross-sectional top view of the body 102 of FIG. 17 according to another embodiment. The cooling circuit 106 includes a first plenum 120 that extends circumferentially within a rib 124 between the first sidewall 126 and the second sidewall 128. The first plenum 120 extends between the rib 124 and the aft end 117 and is fluidly coupled to a second plenum 122 that extends along a portion of the aft end 117. The cooling circuit 106 exhausts through outlet passages 110 in the aft portion of the first sidewall 126, the aft portion of the second sidewall 128, and at least a portion of the aft end 117. 20 shows a cross-sectional top view of the body 102 of FIG. 17 according to another embodiment. The cooling circuit 106 includes a first plenum 120 that extends circumferentially within a rib 124 between a first sidewall 126 and a second sidewall 128. The first plenum 120 extends between the rib 124 and the forward end 115 and is fluidly coupled to a second plenum 122 that extends along a portion of the forward end 115. The cooling circuit 106 exhausts through a forward portion of the first sidewall 126, a forward portion of the second sidewall 128, and outlet passages 110 in at least a portion of the forward end 115.

[0085] 21 and 22 illustrate various views of another non-limiting example of a body 102 according to some embodiments. The non-limiting example of a turbine shroud 100 illustrated in FIGS. 21 and 22 may include similar features as described herein with respect to FIGS. 4-20 , oriented and / or positioned in a different manner. FIG. 21 illustrates a top view of the body 102 including ribs 124 extending circumferentially between a first sidewall 126 and a second sidewall 128. FIG. 22 illustrates a cross-sectional top view of the body 102 of FIG. 21. As illustrated, the body 102 includes a cooling circuit 106 extending within the body 102 between a forward end 115 and an aft end 117. While similar to the embodiment illustrated in FIG. 18, the embodiment of FIG. 22 includes two first plenums 120 that are fluidly isolated from one another. Each first plenum 120 is fluidly coupled to a respective second plenum 122 that extends from the forward end 115 to the aft end 117. The cooling circuits 106 exhaust through outlet passages 110 along the first sidewall 126 and the second sidewall 128, although outlet passages at other locations may also be used.

[0086] 23A, 23B, 23C, 23D, and 23E show various cross-sectional views of several non-limiting embodiments of collection plenums of the cooling circuit 106, such as the first plenum 120 and / or the second plenum 122. As shown, in some embodiments, the first plenum 120 has a shape and dimensions such that the cross-section of the first plenum 120 is circular or substantially circular, as shown in FIG. 23A. In other embodiments, the first plenum 120 has a shape and dimensions such that the cross-section of the first plenum 120 is rectangular or substantially rectangular, as shown in FIG. 23B. In other embodiments, the first plenum 120 has a shape and dimensions such that the cross-section of the first plenum 120 is oval or elliptical, or substantially oval or elliptical, as shown in FIG. 23C. In other embodiments, the first plenum 120 has a shape and dimensions such that the cross-section of the first plenum 120 includes one or more rounded corners (e.g., fillets), as shown in Figure 23D. In other embodiments, the first plenum 120 has a shape and dimensions such that the cross-section of the plenum 120 is triangular or substantially triangular, as shown in Figure 23E. In another embodiment, the cooling circuit 106 includes two or more collection plenums, each having a distinct cross-sectional shape and dimensions. For example, the first plenum 120 may have a circular cross-section and the second plenum 120 may have a rectangular cross-section or a polygonal cross-section with rounded corners.

[0087] FIG. 24 illustrates a schematic / block diagram of an exemplary computerized metal powder additive manufacturing system 310 (hereinafter “AM system 310”) for generating turbine shroud 100, with only a single layer shown. Turbine shroud 100 can be fabricated separately or as a single, integrated piece. While the teachings of the present disclosure are described with respect to constructing turbine shroud 100 using multiple melting beam sources 312, 314, 316, 318, it is emphasized, and it will be readily appreciated, that the teachings of the present disclosure are equally applicable to constructing turbine shroud 100 using any number of melting beam sources. In this example, AM system 310 is configured for direct metal laser melting (DMLM). It is understood that the overall teachings of the present disclosure are equally applicable to other forms of metal powder additive manufacturing, such as, but not limited to, selective laser melting (SLM), and possibly other forms of additive manufacturing (i.e., other than metal powder applications). Although the layers of the turbine shroud 100 within the build platform 320 are shown as generally rectangular elements in FIG. 24, it is understood that the additive manufacturing process can be easily adapted to produce any shaped part of the shroud 100 on the build platform 320.

[0088] The AM system 310 generally includes an additive manufacturing control system 330 (“control system”) and an AM printer 332. As described below, the control system 330 executes a set of computer-executable instructions or code 334 for producing the turbine shroud 100 using multiple melt beam sources 312, 314, 316, and 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 as computer program code on a computer 336. In this sense, the computer 336 is shown to include 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 to be in communication with external I / O devices / resources 350. 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 write data from memory 338, storage system 340, I / O devices 350, and / or AM printer 332. Bus 348 provides a communications link between each of the components in computer 336, and I / O devices 350 can comprise any device (e.g., keyboard, pointing device, display, etc.) that enables a user to interact with computer 336.

[0089] Computer 336 is merely representative of various possible combinations of hardware and software. For example, processor unit (PU) 344 can comprise a single processing unit or can be distributed across one or more processing units at one or more locations, e.g., on 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 can comprise 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 can comprise any type of computing device, such as an industrial controller, a network server, a desktop computer, a laptop, a handheld device, etc.

[0090] As described above, the AM system 310, and in particular the control system 330, executes code 334 to produce the turbine shroud 100. 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 and a set of computer-executable instructions 334O (also referred to herein as “code 334O”) that define the turbine shroud 100 to be physically produced 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.

[0091] The set of computer-executable instructions 334O defining the turbine shroud 100 may include a precisely defined 3D model of the turbine shroud 100 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 turbine shroud 100 may be converted between different formats. For example, the code 334O may include a Standard Tessellation Language (STL) file generated for a 3D systems stereolithography CAD program, or an Additive Manufacturing File (AMF), an extensible markup language (XML)-based format standardized by the American Society of Mechanical Engineers (ASME) and designed to allow any CAD software to describe the shape and configuration of any three-dimensional object to be fabricated on any AM printer. The code 334O representing the turbine shroud 100 may also be converted to a set of data signals, transmitted, received as a set of data signals, converted to code, stored, etc., as needed. The code 334O may be configured according to embodiments of the present disclosure to enable the formation of boundaries and interior sections within overlapping field regions, as described below. In either case, the code 334O may be input to the AM system 310 and may come from a part designer, intellectual property (IP) provider, design firm, operator or owner of the AM system 310, or other source. In either case, the control system 330 executes the codes 334S and 334O to divide the turbine shroud 100 into a series of thin slices, which are assembled with successive layers of material using the AM printer 332.

[0092] The AM printer 332 may include a sealed processing chamber 360 to provide a controlled atmosphere for printing the turbine shroud 100. A build platform 320, on which the turbine shroud 100 is built, is positioned within the processing chamber 360. Several melting beam sources 312, 314, 316, 318 are configured to melt layers of metal powder on the build platform 320 to produce the turbine shroud 100. While four melting beam sources 312, 314, 316, 318 are shown, it is emphasized that the teachings of the present disclosure are applicable to systems using any number of sources, for example, one, two, three, or five or more sources. As understood in the art, each melting beam source 312, 314, 316, 318 may have fields that each include non-overlapping field regions capable of melting only metal powder, and two or more sources may include at least one overlapping field region capable of melting metal powder. In this regard, each melt beam source 312, 314, 316, 318 can generate a respective melt beam that melts particles for each slice, as defined by code 334O. For example, in FIG. 25 , melt beam source 312 is shown generating a layer of turbine shroud 100 using melt beam 362 in one region, and melt beam source 314 is shown generating a layer of turbine shroud 100 using melt beam 362′ in another region. Each melt beam source 312, 314, 316, 318 is calibrated in any now known or later developed manner. That is, each melt beam source 312, 314, 316, 318 correlates the expected position of its laser or electron beam 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 the multiple melt beam sources 312, 314, 316, 318 can generate a melt beam, eg, 362, 362', having the same cross-sectional dimensions (eg, shape and size during operation), power, and scanning speed.

[0093] 24 , an applicator (or recoater blade) 370 produces a thin layer of feedstock material 372, which is laid out as a blank canvas from which each successive slice of the final turbine shroud 100 will be produced. Various parts of the AM printer 332 may move to accommodate the addition of each new layer; for example, after each layer, the build platform 320 may lower and / or the chamber 360 and / or the applicator 370 may raise. The process may use a different feedstock material in the form of a fine-grained metal powder, a stock of which may be held in a powder reservoir 368 accessible by the applicator 370.

[0094] The processing chamber 360 is filled with an inert gas, such as argon or nitrogen, and controlled to minimize or eliminate oxygen. The control system 330 is configured to control the flow of a gas mixture 374 within the processing chamber 360 from an inert gas source 376. In this case, the control system 330 can 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 can 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 or may not include the valve system 382. If the pump 380 is omitted, the inert gas can enter a conduit or manifold before being introduced into the processing chamber 360. The inert gas source 376 can take the form of any conventional source for the materials 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.

[0095] During operation, a build platform 320 having metal powder thereon is provided within a processing chamber 360, and a control system 330 controls the flow of a gas mixture 374 within the processing chamber 360 from an inert gas source 376. The control system 330 also controls the AM printer 332, and in particular the applicator 370 and melt beam sources 312, 314, 316, 318, to sequentially melt layers of metal powder on the build platform 320 to produce a turbine shroud 100 according to an embodiment of the present disclosure. While a particular AM system 310 is described herein, it is emphasized that the teachings of the present disclosure are not limited to any particular additive manufacturing system or method.

[0096] The present disclosure provides various technical and commercial advantages, examples of which are described herein. The turbine shroud 100 may provide a series of impingement cooling passages that cool large ribs via impingement cooling. The turbine shroud 100 may provide a cascading cooling circuit that directs air through a series of collection plenums within the turbine shroud 100. The turbine shroud 100 may recycle the cooling air by directing the cooling air exiting the series of impingement cooling passages to one or more regions along the circumference of the turbine shroud 100.

[0097] As used herein throughout this specification and claims, approximation language can be applied to modify any quantitative expression that can reasonably vary without resulting in a change in the relevant basic function. Thus, values ​​modified by terms such as "approximately," "about," and "substantially" are not limited to the exact value specified. In at least some instances, approximation language can correspond to the precision of the instrument used to measure the value. Here, and throughout this specification and claims, range limitations are combinable and / or interchangeable, and unless the context or language dictates otherwise, such ranges are identified and include all subranges encompassed therein. "About" or "approximately," as applied to a particular value in a range, applies to both endpoints and can indicate + / - 10% of the stated value, unless specifically dependent on the precision of the instrument used to measure the value.

[0098] The corresponding structure, material, 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 that are specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the disclosure to 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 present embodiment was chosen and described in order to best explain the principles of the disclosure and its practical application, and to enable others skilled in the art to understand the present disclosure to envision various embodiments with modifications as suitable for particular given uses. [Explanation of symbols]

[0099] 10 Gas Turbine System 12 Compressor 18 Air 20 Compressed air 22 Combustor 24 Fuel 26 Combustion gases, turbomachinery casings 28 Turbine 30 rotors 32 External Load 34 Exhaust frame 36 Casing, turbomachinery casing 38 Turbine Blade 40 stator vane 42 Outer Platform 44 Inner Platform 45 Airfoil 46 Airfoil 48 Tip part 50 Connecting components, intermediate components 100 Turbine shroud 101 Intermediate Components 102 Inner body 103 Component Body 105 Component Cooling Circuit 106 Cooling circuit 107 Entrance Passage 108 Entrance Passage 109 Exit passage 110 Exit passage 111 Cooling chamber 112 Radial outer surface 113 Air Chamber 114 Inner surface 115 Front end 116 First Hook 117 Rear end 118 Second Hook 120 First Plenum 122 Second Plenum 124 Pair of Ribs / First Rib / Second Rib 126 First Side Wall 128 Second Side Wall 130 additional cooling circuits 200 Impingement Panel 202 First Surface 204 Second Surface 206 Impingement holes 310 Computerized Metal Powder Additive Manufacturing System / AM System 312 Melting Beam Source 314 Melting Beam Source 316 Melting Beam Source 318 Melting Beam Source 320 Building Platform 330 Additive Manufacturing Control System 332 AM Printer 334 Computer Program Code 334S Computer Executable Instructions / Code 334O Computer executable instructions / code 336 Computer 338 memory 340 Memory System 344 Processor Unit / PU 346 Input / Output (I / O) Interface 348 Bus 350 External I / O Devices / Resources 360 Processing Chamber 362 Melting Beam 362' molten beam 370 Applicator 372 raw materials 374 Gas Mixtures 376 Inert Gas Source 380 Pump 382 Flow Valve System 386 filters D Flow direction R Radial direction FP hot gas flow path

Claims

1. A turbine shroud (100), comprising: a body (102) including a structural member thereon, the body (102) configured to couple to a turbomachine casing (26, 36); a cooling circuit (106) within the body (102) and in fluid communication with a cooling chamber (111) defined radially outwardly of the body (102), the cooling circuit (106) comprising: an inlet passage (107, 108) extending through the structural member of the body (102); and outlet passages (109, 110) fluidly coupled to the inlet passages (107, 108) and extending through an outer surface of the body (102); a cooling circuit (106) including A turbine shroud (100) comprising:

2. 2. The turbine shroud of claim 1, wherein the structural member includes ribs on a radially outer surface of the body, and the cooling circuit includes a first plenum extending within the ribs of the body and in fluid communication with the inlet passage.

3. 3. The turbine shroud of claim 2, wherein the cooling circuit further includes a second plenum fluidly coupled to the first plenum and within a different structural member of the body, the second plenum fluidly coupling the first plenum to the outlet passage.

4. The turbine shroud (100) of claim 2, wherein the inlet passages (107, 108) are shaped to direct cooling air (18) into the first plenum (120) and beneath the structural member.

5. 2. The turbine shroud of claim 1, further comprising an impingement panel positioned between the structural member of the body and a cooling chamber, the impingement panel including a plurality of impingement holes fluidly coupling the cooling chamber to the inlet passage of the cooling circuit.

6. The turbine shroud of claim 5, wherein the impingement panel extends between first and second hooks that extend outwardly from the body.

7. 7. The turbine shroud of claim 6, further comprising an intermediate component disposed between the body and the turbomachine casing, wherein the first hook and the second hook engage respective recesses in the intermediate component.

8. The turbine shroud (100) of claim 6, wherein the first hook (116) and the second hook (118) are configured to engage respective recesses in the turbomachine casing (26, 36).

9. The body (102) a front end (115) positioned opposite a rear end (117); a first sidewall (126) extending between said front end (115) and said rear end (117); a second side wall (128) extending between the front end (115) and the rear end (117) and facing the first side wall (126); an outer surface (112) extending between the first sidewall (126) and the second sidewall (128), the outer surface (112) being oriented toward the cooling chamber (111) and having the structural member thereon; A blade structure for a turbomachine and an inner surface (114) oriented towards a hot gas path (FP); The turbine shroud (100) of claim 1, further comprising:

10. 10. The turbine shroud of claim 9, wherein the structural members are a first rib and a second rib, each of the first rib and the second rib extending between the forward end and the aft end and including the inlet passage to a respective cooling circuit.

11. 11. The turbine shroud of claim 10, wherein the cooling circuit further includes a second plenum fluidly coupled to the first plenum and within a different structural member of the body, the second plenum fluidly coupling the first plenum to the outlet passage defined in one of the forward end or the aft end.

12. 11. The turbine shroud of claim 10, wherein the cooling circuit further includes at least two second plenums fluidly coupled to respective first plenums and within different structural members of the body, the at least two second plenums fluidly coupling the respective first plenums to outlet passages defined in the forward end and the aft end.

13. 10. The turbine shroud of claim 9, wherein the structural member is a first rib extending between the first sidewall and the second sidewall, the first rib defining at least one first plenum in fluid communication with the inlet passage.

14. 14. The turbine shroud of claim 13, wherein the cooling circuit further includes a second plenum fluidly coupled to the at least one first plenum and within a different structural member of the body, the second plenum fluidly coupling the at least one first plenum to the outlet passage defined in at least one of the first sidewall or the second sidewall.

15. A turbomachine, comprising: a blade structure configured to rotate about an axis of rotation of a rotor (30); a turbine shroud (100) oriented toward the blade structure and coupled to a turbomachine casing (26, 36), the turbine shroud (100) comprising: A body (102) including a structural member at an upper portion, said body (102) being coupled to either a turbomachine casing (26, 36) or an intermediate component (50, 101) for coupling said body (102) to said turbomachine casing (26, 36). a turbine shroud (100) including: a cooling circuit (106) within the body (102) and in fluid communication with a cooling chamber (111) adjacent the body (102), the cooling circuit (106) comprising: an inlet passage (107, 108) extending through the structural member of the body (102); and outlet passages (109, 110) fluidly coupled to the inlet passages (107, 108) and extending through an outer surface of the body (102); a cooling circuit (106) including A turbomachine comprising:

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