Integral body turbine shroud including shot peening screen integrally formed therein and turbine system thereof

Abstract

The present invention discloses a turbine shroud (100) including a shot peening screen (300) integrally formed therein. The shroud may include a monolithic body (102) having a support portion (104), an intermediate portion (134), and a sealing portion (154); the support portion is directly coupled to a turbine (28) casing (36) of a turbine system (10); the intermediate portion is integral with the support portion (104) and extends away from the support portion; the sealing portion is integral with the intermediate portion (134) and opposite the support portion (104). The monolithic body (102) may also include an inlet opening (168, 168A, 168B), a plenum (200), and a cooling passage (202); the inlet opening is formed in the support portion (104); the plenum is in fluid communication with the inlet opening (168, 168A, 168B); and the cooling passage extends through the sealing portion (154) and is in fluid communication with the plenum (200). Additionally, the monolithic body (102) may include a shot peening screen (300) positioned within the plenum (200) and extending within the intermediate portion (134). The shot peening screen (300) may include a plurality of apertures formed therethrough and may prevent shot from passing through the shot peening screen (300) when a shot peening process is performed on the monolithic body (102).

Description

Background Art

[0001] The present disclosure relates generally to turbine system components and turbine systems thereof, and more particularly, to a single-body turbine shroud for a turbine system including a shot peening screen integrally formed therein.

[0002] Conventional turbines such as gas turbine systems generate electricity for generators. Typically, a gas turbine system generates power by passing a fluid (e.g., hot gas) through a turbine component of a gas turbine system. More specifically, inlet air can be drawn into a compressor and compressed. Once compressed, the inlet air is mixed with fuel to form combustion products, which can be reacted by the combustor of the gas turbine system to form an operating fluid (e.g., hot gas) for the gas turbine system. The fluid can then flow through a fluid flow path for rotating a plurality of rotating blades and a rotor or shaft of the turbine component for generating power. The fluid can be directed through the turbine component via a plurality of rotating blades and a plurality of fixed nozzles or blades positioned between the rotating blades. When the plurality of rotating blades rotate the rotor of the gas turbine system, a generator coupled to the rotor can generate electricity from the rotation of the rotor.

[0003] To improve operating efficiency, the turbine component may include hot gas path components (such as a turbine shroud and / or nozzle band) to further define the flow path of the operating fluid. For example, the turbine shroud may be positioned radially adjacent to the rotating blades of the turbine component and may guide the operating fluid within the turbine component and / or define the outer boundary of the flow path for the operating fluid. During operation, the turbine shroud may be exposed to the high temperature operating fluid flowing through the turbine component. Over time and / or during exposure, the turbine shroud may experience undesirable thermal expansion. Thermal expansion of the turbine shroud may cause damage to the shroud and / or may not allow the shroud to maintain a seal within the turbine component. When the turbine shroud becomes damaged or no longer forms a satisfactory seal within the turbine component, the operating fluid may leak from the flow path, which in turn reduces the operating efficiency of the turbine component and the entire turbine system.

[0004] To minimize thermal expansion, turbine shrouds are typically cooled. Conventional processes for cooling turbine shrouds include impingement cooling. Impingement cooling utilizes holes or apertures formed through the turbine shroud to provide cooling air to various portions of the turbine shroud during operation. With advances in additive manufacturing, shrouds can be additively manufactured to form complex impingement cooling circuits therein to improve cooling and / or further minimize thermal expansion. However, additively manufactured shrouds are often subjected to additional or post-build processing to improve and / or increase the operational life of the shroud. These post-build processing include, for example, shot peening and / or sand blasting of the additively manufactured shroud.

[0005] However, by performing a process such as shot peening on a shroud, there is an increased risk of pellets becoming undesirably embedded, adhered to, and / or trapped within the shroud's complex geometries. For example, pellets may become embedded or trapped within openings, ducts, and / or channels utilized for impingement cooling within the shroud. These trapped pellets block or obstruct the openings, ducts, and / or channels, thereby reducing the effectiveness of impingement cooling within the shroud. While certain holes or features of the shroud may be covered with plugs and / or tape prior to performing the shot peening process, the plugs may become disengaged during the shot peening process and may no longer prevent one or more pellets from entering the holes or features. Additionally, while gluing holes or features may prevent pellets from undesirably entering the holes or features, it may also block and / or obstruct the surfaces intended to receive the peened pellets. Furthermore, plugging or gluing each hole or feature is very time-consuming and often requires adjustments throughout the shot peening process. Summary of the Invention

[0006] A first aspect of the present disclosure provides a turbine shroud for a turbine system. The turbine shroud includes: a unitary body, the unitary body including: a support portion directly coupled to a turbine housing of the turbine system; a middle portion integral with the support portion and extending away from the support portion; a sealing portion integral with the middle portion and opposite the support portion, the sealing portion including a front end, a rear end positioned opposite the front end, and a hot gas path (HGP) surface extending between the front end and the rear end; at least one inlet opening formed in the support portion; at least one plenum in fluid communication with the at least one inlet opening, the at least one plenum being in fluid communication with the at least one inlet opening. at least one plenum extending through the support portion and the mid-portion; a cooling passage extending through the sealing portion between a front end and a rear end of the sealing portion, the cooling passage positioned between the at least one plenum and a HGP surface of the sealing portion, wherein the cooling passage is in fluid communication with the at least one plenum; and at least one shot peening screen positioned within the at least one plenum and extending within the mid-portion, the at least one shot peening screen including a plurality of apertures formed therethrough, wherein the at least one shot peening screen prevents shot from passing through the at least one shot peening screen when a shot peening process is performed on the monolithic body.

[0007] The camshaft of claim 1 further comprising a plurality of camshafts disposed on the camshaft to extend along the length of the camshaft, wherein the camshafts are connected to the camshaft housing and are adapted to move the camshafts upwardly and downwardly relative to the camshaft housing. a hot gas path (HGP) surface extending between the support portion and the intermediate portion; at least one inlet opening formed in the support portion; at least one plenum in fluid communication with the at least one inlet opening, the at least one plenum extending through the support portion and the intermediate portion; a cooling passage extending through the sealing portion between a front end and a rear end of the sealing portion, the cooling passage positioned between the at least one plenum and the HGP surface of the sealing portion, wherein the cooling passage is in fluid communication with the at least one plenum; and at least one shot peening screen positioned within the at least one plenum and extending within the intermediate portion, the at least one shot peening screen including a plurality of apertures formed therethrough, wherein the at least one shot peening screen prevents shot from passing through the at least one shot peening screen when a shot peening process is performed on the monolithic body.

[0008] The exemplary aspects of the present disclosure are designed to solve the problems described herein and / or other problems not discussed. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the disclosure taken in conjunction with the accompanying drawings which depict various embodiments of the disclosure, in which:

[0010] Figure 1 A schematic diagram of a gas turbine system according to an embodiment of the present disclosure is shown.

[0011] Figure 2 The embodiment according to the present disclosure is shown Figure 1 A side view of a portion of a turbine of a gas turbine system, the turbine including turbine blades, stator blades, a rotor, a turbine casing, and a turbine shroud.

[0012] Figure 3 The embodiment according to the present disclosure is shown Figure 2 A perspective view of the turbine shroud.

[0013] Figure 4 The embodiment according to the present disclosure is shown Figure 3 Front view of the turbine shroud.

[0014] Figure 5 The embodiment according to the present disclosure is shown Figure 3 A first side view of a turbine shroud.

[0015] Figure 6 The embodiment according to the present disclosure is shown Figure 3 A second side view of the turbine shroud.

[0016] Figure 7 The embodiment according to the present disclosure is shown Figure 3 Top view of a turbine shroud.

[0017] Figure 8 1-CS1 according to an embodiment of the present disclosure. Figure 7 A side cross-sectional view of a turbine shroud.

[0018] Figure 9 The embodiment according to the present disclosure is shown Figure 8 A perspective view of the turbine shroud.

[0019] Figure 10 1 is a diagram showing a perspective view taken along line CS1-CS1 according to an additional embodiment of the present disclosure. Figure 7 A side cross-sectional view of a turbine shroud.

[0020] Figure 11 1 shows a cross-sectional view taken along line CS1-CS1 according to another embodiment of the present disclosure. Figure 7 A side cross-sectional view of a turbine shroud.

[0021] Figure 12 Another embodiment according to the present disclosure is shown Figure 3 Front view of the turbine shroud.

[0022] Figure 13 A block diagram of an additive manufacturing process including a non-transitory computer-readable storage medium storing code representing a turbine shroud is shown according to an embodiment of the present disclosure.

[0023] It should be noted that the drawings of the present disclosure are not drawn to scale. The drawings are intended to depict only typical aspects of the present disclosure and therefore should not be considered to limit the scope of the present disclosure. In the drawings, similar numbers represent similar elements between the drawings. DETAILED DESCRIPTION

[0024] First, in order to clearly describe the present disclosure, it will be necessary to select certain terms when referencing and describing relevant machine components within the scope of the present disclosure. In doing so, common industry terms will be used and adopted in a manner consistent with their accepted meanings, if possible. Unless otherwise indicated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those of ordinary skill in the art will understand that several different or overlapping terms may often be used to refer to a particular component. An object that may be described herein as a single part may include multiple components and be referenced in another context as consisting of multiple components. Alternatively, an object that may be described herein as comprising multiple components may be referred to elsewhere as a single part.

[0025] In addition, several descriptive terms may be used regularly in this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, "downstream" and "upstream" are terms that indicate the direction relative to the flow of a fluid, such as the working fluid through a turbine engine, or, for example, the flow of air through a combustor or the coolant through one of the component systems of a turbine. The term "downstream" corresponds to the direction of fluid flow, and the term "upstream" refers to the direction opposite to the flow. In the absence of any further particularity, the terms "front" and "rear" refer to directions, where "front" refers to the front end or compressor end of the engine, and "rear" refers to the rear end or turbine end of the engine. Alternatively, the terms "front" and "rear" may be used and / or understood to be similar in description to the terms "front" and "rear", respectively. Typically, it is necessary to describe parts that are in different radial, axial and / or circumferential positions. The "A" axis represents the axial orientation. As used herein, the terms "axial" and / or "axially" refer to the relative position / orientation of an object along an axis A, which is substantially parallel to the axis of rotation of the turbine system (particularly the rotor portion). As further used herein, the terms "radial" and / or "radially" refer to the relative position / orientation of an object along a direction "R" (see Figure 1 and Figure 2 ), which is a direction substantially perpendicular to axis A and intersects axis A at only one location. Finally, the term "circumferential" refers to movement or position about axis A (e.g., direction "C").

[0026] As indicated above, the present disclosure generally relates to turbine system components and turbine systems thereof, and more particularly, to a unitary body turbine shroud for a turbine system including a shot peening screen integrally formed therein.

[0027] References below Figures 1 to 13However, those skilled in the art will readily appreciate that the detailed description given herein with respect to these figures is for illustration purposes only and should not be construed as limiting.

[0028] Figure 1 A schematic diagram of an exemplary gas turbine system 10 is shown. The gas turbine system 10 may include a compressor 12. The compressor 12 compresses an incoming air flow 18. The compressor 12 delivers the compressed air flow 20 to a combustor 22. The combustor 22 mixes the compressed air flow 20 with a pressurized fuel flow 24 and ignites the mixture to produce a combustion gas flow 26. Although only a single combustor 22 is shown, the gas turbine system 10 may include any number of combustors 22. The combustion gas flow 26 is then delivered to a turbine 28, which typically includes a plurality of turbine blades, including airfoils (see FIG. Figure 2 ) and stator blades (see Figure 2 The combustion gas flow 26 drives a turbine 28, and more specifically, a plurality of turbine blades of the turbine 28, to produce mechanical work. The mechanical work produced in the turbine 28 drives the compressor 12 via a rotor 30 extending through the turbine 28 and can be used to drive an external load 32 (such as an electrical generator, etc.).

[0029] The gas turbine system 10 may also include an exhaust frame 34. Figure 1 As shown, the exhaust frame 34 may be positioned adjacent to the turbine 28 of the gas turbine system 10. More specifically, the exhaust frame 34 may be positioned adjacent to the turbine 28 and may be positioned substantially downstream of the turbine 28 and / or the flow of combustion gases 26 flowing from the combustor 22 to the turbine 28. As discussed herein, a portion of the exhaust frame 34 (e.g., an outer casing) may be directly coupled to an outer shell, casing, or housing 36 of the turbine 28.

[0030] After the combustion gases 26 flow through and drive the turbine 28, the combustion gases 26 may be exhausted, flowed through, and / or discharged in a flow direction (D) through an exhaust frame 34. Figure 1 In the non-limiting example shown, the combustion gases 26 may flow through the exhaust frame 34 in a flow direction (D) and may be discharged (e.g., to the atmosphere) from the gas turbine system 10. 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 may flow in a flow direction (D) into a heat recovery steam generator of the combined cycle power plant.

[0031] Go to Figure 2 , showing a portion of the turbine 28. Specifically, Figure 2A side view of a portion of a turbine 28 is shown, including stages of turbine blades 38 (one shown), and stages of stator blades 40 (one shown) positioned within a casing 36 of the turbine 28. As discussed herein, each stage of turbine blades 38 (e.g., first stage, second stage (not shown), third stage (not shown)) may include a plurality of turbine blades 38 that may be coupled to and positioned circumferentially about or around the rotor 30, and may be driven by the combustion gases 26 to rotate the rotor 30. As shown, the plurality of turbine blades 38 may also extend radially from the rotor 30. Additionally, each stage of stator blades 40 (e.g., first stage, second stage (not shown), third stage (not shown)) may include a plurality of stator blades that may be coupled to and positioned circumferentially about the casing 36 of the turbine 28. Figure 2 In the non-limiting example shown, the stator blade 40 may include a plurality of hot gas path (HGP) components including and / or formed as an outer platform 42 and an inner platform 44 positioned opposite the outer platform 42. The stator blade 40 of the turbine 28 may also include 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 blade 40 may define a flow path (FP) for the combustion gases 26 flowing through the stator blade 40. As discussed herein, the stator blade 40 may be coupled to an adjacent and / or surrounding turbine shroud of the turbine 28.

[0032] Each turbine blade 38 of the turbine 28 may include an airfoil 46 extending radially from the rotor 30 and positioned within a flow path (FP) of the combustion gases 26 flowing through the turbine 28. Each airfoil 46 may include a tip portion 48 positioned radially adjacent the rotor 30. The turbine blade 38 may also include a platform 50 positioned opposite the tip portion 48 of the airfoil 46. In a non-limiting example, the platform 50 may partially define the flow path of the combustion gases 26 for the turbine blade 38. The turbine blade 38 and the stator blades 40 may also be positioned axially adjacent each other within the casing 36. Figure 2 In the non-limiting example shown, the stator blades 40 may be located adjacent to and axially downstream of the turbine blades 38. For clarity, not all turbine blades 38, stator blades 40, and / or all rotors 30 of the turbine 28 are shown. Figure 2 Only a portion of a single stage of turbine blades 38 and stator vanes 40 of the turbine 28 is shown, but the turbine 28 may include multiple stages of turbine blades and stator vanes positioned axially throughout the casing 36 of the turbine 28 .

[0033] The turbine 28 of the gas turbine system 10 (see Figure 1) may also include a plurality of turbine shrouds 100 included within the turbine 28. The turbine 28 may include stages (one shown) of turbine shrouds 100. The turbine shrouds 100 may correspond to stages of turbine blades 38 and / or stages of stator vanes 40. That is, and as discussed herein, stages of turbine shrouds 100 may be positioned within the turbine 28 adjacent to stages of turbine blades 38 and / or stages of stator vanes 40 to interact with and provide a seal therein and / or may define a flow path (FP) of the combustion gases 26 flowing through the turbine 28. Figure 2 In the non-limiting example shown, a stage of turbine shrouds 100 may be radially positioned adjacent to a stage of turbine blades 38 and / or may substantially surround or encircle the stage. The turbine shrouds 100 may be radially positioned adjacent to the tip portion 48 of the airfoil 46 of the turbine blade 38. Additionally, in the non-limiting example, the turbine shrouds 100 may also be positioned adjacent to and / or radially upstream of the stator blades 40 of the turbine 28. The turbine shrouds 100 may be positioned on either axial side of a single stage of turbine blades and / or between two adjacent stages of stator blades positioned thereon.

[0034] The stage of turbine shrouds may include a plurality of turbine shrouds 100 that may be directly coupled to the casing 36 of the turbine 28 and / or positioned circumferentially around the casing. Figure 2 In the non-limiting example shown, the turbine shroud 100 may be directly coupled to the casing 36 of the turbine 28 via an extension 52 that extends radially inward (e.g., toward the rotor 30) from the casing 36 of the turbine 28. The extension 52 may include an opening 54 that may be configured to couple to and / or receive a portion of the turbine shroud 100 to couple, position, and / or secure the turbine shroud 100 to the casing 36 of the turbine 28. In a non-limiting example, the extension 52 may be coupled and / or secured to the casing 36 of the turbine 28. More specifically, the extension 52 may be disposed circumferentially about the casing 36 and may be positioned radially adjacent to the turbine blades 38. In another non-limiting example, the extension 52 may be integrally formed with the casing 36 for directly coupling, positioning, and / or securing the turbine shroud 100 to the casing 36. Similar to the turbine blades 38 and / or stator vanes 40, although Figure 2 Only a portion of the stages of the turbine shroud 100 of the turbine 28 are shown in , but the turbine 28 may include multiple stages of turbine shrouds 100 positioned axially within the casing 36 of the entire turbine 28 and coupled to the casing 26 using extensions 52 .

[0035] Figures 3 to 7 Shown for Figure 1 Various views of the turbine shroud 100 of the turbine 28 of the gas turbine system 10 are shown. Specifically, Figure 3 An isometric view of a turbine shroud 100 is shown, Figure 4 shows a front view of a turbine shroud 100, Figure 5 A first side view of a turbine shroud 100 is shown, Figure 6 A second view of the turbine shroud 100 is shown, and Figure 7 A top view of the turbine shroud 100 is shown.

[0036] All can be found in this article Figures 3 to 7 The non-limiting examples of the turbine shroud 100 and its various components are addressed to ensure that each of the various components is fully and accurately described and illustrated. When applicable, reference may be made to the collection when discussing components or features of the turbine shroud 100. Figures 3 to 7 In addition, in this article, Figure 3 and Figure 7 Use regularly Figure 1 and Figure 2 Several reference lines or directions are shown. For example, Figures 3 to 7 In each of the figures, as discussed herein, “A” may refer to an axial orientation or axis, “R” may refer to a radial axis substantially perpendicular to axis A, and “C” may refer to a circumferential direction, movement and / or position along a path centered about axis “A”.

[0037] The turbine shroud 100 may include a body 102. Figures 3 to 7 In the non-limiting example shown, the turbine shroud 100 may include and / or be formed as a unitary body 102 such that the turbine shroud 100 is a single, continuous, and / or non-disjointed component or part. Figures 3 to 7 In the illustrated non-limiting example, because the turbine shroud 100 includes a unitary body 102, the turbine shroud 100 may not require the construction, joining, coupling, and / or assembly of various parts to fully form the turbine shroud 100 and / or may not require the construction, joining, coupling, and / or assembly of various parts before the turbine shroud 100 can be installed and / or implemented within the turbine system 10 (see Figure 1 In contrast, as discussed herein, once the single, continuous, and / or non-disjointed, unitary body 102 for the turbine shroud 100 is constructed, the turbine shroud 100 may be immediately installed within the turbine system 10 .

[0038] In a non-limiting example, the monolithic body 102 of the turbine shroud 100 and the various components and / or features of the turbine shroud 100 may be formed using any suitable additive manufacturing process and / or method. For example, the turbine shroud 100 including the monolithic body 102 may be formed using direct metal laser melting (DMLM) (also known as selective laser melting (SLM)), direct metal laser sintering (DMLS), electron beam melting (EBM), stereolithography (SLA), binder jetting, or any other suitable additive manufacturing process. In this way, the monolithic body 102 of the turbine shroud 100 and the various components and / or features integrally formed thereon and / or therein may be formed during a single additive manufacturing process and / or method. Additionally, the monolithic body 102 of the turbine shroud 100 may be formed from any material that may be utilized by one or more additive manufacturing processes to form the turbine shroud 100 , and / or that is capable of withstanding the operational characteristics (e.g., exposure temperatures, exposure pressures, etc.) experienced by the turbine shroud 100 within the gas turbine system 10 during operation.

[0039] Being formed from a unitary body 102, the turbine shroud 100 may include various integrally formed portions, each of which may include different features, components, and / or sections that may provide a seal in and / or define the flow path (FP) of the combustion gases 26 flowing through the turbine 28 (see FIG. Figure 2 That is, and because the turbine shroud 100 includes a monolithic body 102 formed using any suitable (single) additive manufacturing process and / or method, features, components, and / or sections of the turbine shroud 100 may be integrally formed with the monolithic body 102. The terms "integral feature" or "integrally formed feature" may refer to a feature formed on or in the monolithic body 102 during a (single) additive manufacturing process, a feature formed from the same material as the monolithic body 102, and / or a feature formed on or in the monolithic body 102 such that the feature is not manufactured using one or more different processes and / or raw material components that are separately and subsequently constructed, joined, coupled, and / or assembled on or in the monolithic body 102 of the turbine shroud 100.

[0040] For example, the turbine shroud 100 may include a monolithic body 102 having a support portion 104. The support portion 104 may be directly coupled to the turbine shroud 100 and / or assist in coupling the turbine shroud to the turbine casing 36 and / or the extension 52. The support portion 104 of the monolithic body 102 may include a forward end 106 and an aft end 108 positioned opposite the forward end 106. The forward end 106 may be positioned axially upstream of the aft end 108.

[0041] exist Figure 3 、 Figure 4 and Figure 7 In the non-limiting example shown, the front end 106 may include a protruding and / or converging shape, orientation, and / or configuration 110 (hereinafter referred to as "configuration 110"). That is, and as Figure 3 、 Figure 4 and Figure 7 As shown in the non-limiting example of FIG, the front end 106 of the support portion 104 can be formed to include a configuration 110 that can include opposing angled and / or curved walls 112, 118 extending axially from opposing side or inclined surfaces 120, 122 of the monolithic body 102 and converging at a central wall 124. The central wall 124 of the front end 106 can be positioned and / or formed upstream of the walls 112, 118 and / or can be positioned axially forward of the remainder of the support portion 104 of the monolithic body 102. That is, the central wall 124 can be the axially forward-most portion for the front end 106 of the support portion 104 of the monolithic body 102.

[0042] Additionally, the support portion 104 may further include a first surface 126 and a second surface 128. The first surface 126 and the second surface 128 may extend (axially) between the front end 106 and the rear end 108. Additionally, the first surface 126 and the second surface 128 may be formed or extend substantially perpendicular to the front end 106 and / or the rear end 108 of the support portion 104. As shown in the non-limiting example, the second surface 128 of the support portion 104 may be positioned and / or formed to be (radially) opposite the first surface 110.

[0043] exist Figures 3 to 7 In the non-limiting example shown, the monolithic body 102 of the turbine shroud 100 may also include an intermediate portion 134. The intermediate portion 134 may be integrally formed with the support portion 104 and extend from the support portion. For example, the intermediate portion 134 may be integrally formed with the support portion 104 and extend away from the support portion. More specifically, the intermediate portion 134 of the monolithic body 102 may be integrally formed with the second surface 128 of the support portion 104 and may extend radially away from the second surface. In the non-limiting example, the intermediate portion 134 of the turbine shroud 100 may be positioned radially between the support portion 104 of the monolithic body 102 and the turbine blades 38 of the turbine 28 (see FIG. Figure 2 ).

[0044] The intermediate portion 134 may include various features and / or sections of the monolithic body 102 of the turbine shroud 100. The various features and / or sections discussed herein may extend and / or be formed between the opposing inclined surfaces 120, 122 of the monolithic body 102. For example, the intermediate portion 134 may include a rearward section 136 that extends vertically and / or radially away from the second surface 128 of the support portion 104. Additionally, as Figure 3 、 Figure 5 and Figure 6 As shown, the rear section 136 of the intermediate portion 134 can extend from the second surface 128 substantially adjacent the rear end 108 of the support portion 104. In a non-limiting example, at least a portion of the rear section 136 of the intermediate portion 134 can be positioned axially upstream of the rear end 108 of the support portion 104 of the monolithic body 102.

[0045] The intermediate portion 134 may also include a non-linear section 142 that extends away from the second surface 128 of the support portion 104. Figure 3 、 Figure 5 and Figure 6 As shown, the nonlinear section 142 of the intermediate portion 134 can extend substantially radially from the second surface 128, between the forward end 106 and the rearward end 108 of the support portion 104 of the monolithic body 102, and axially adjacent the rearward section 136. The nonlinear section 142 of the intermediate portion 134 can include a first end 144 integrally formed with the second surface 128 of the support portion 104 between the forward end 106 and the rearward end 108. Additionally, the nonlinear section 142 can include a second end 146 positioned opposite the first end 144. The second end 146 of the nonlinear section 142 can be positioned radially adjacent to and axially upstream of the first end 144. Additionally, the second end 146 of the nonlinear section 142 of the intermediate portion 134 can also be positioned axially upstream of the forward end 106 of the support portion 104. A curved portion 148 can extend between the first end 144 and the second end 146 of the nonlinear section 142. That is, the non-linear section 142 may further include a curved portion 148 extending between the first end 144 and the second end 146. Figure 3 、 Figure 5 and Figure 6 In the non-limiting example shown, the curved portion 148 extending between the first end 144 and the second end 146 may include a generally concave shape or configuration such that a side view of the intermediate portion 134 of the turbine shroud 100 and / or the monolithic body 102 may appear as an inverted “C.” As a result of extending between the first end 144 and the second end 146, at least a portion of the curved portion 148 may also be positioned or extend axially upstream of the forward end 106 of the support portion 104.

[0046] The monolithic body 102 of the turbine shroud 100 may also include a sealing portion 154. The sealing portion 154 may be integrally formed with the intermediate portion 134. That is, the sealing portion 154 of the monolithic body 102 may be integrally formed with the intermediate portion 134. The sealing portion 154 may be positioned opposite the support portion 104, for example, radially opposite the support portion 104. In a non-limiting example, and as discussed herein, the sealing portion 154 of the turbine shroud 100 may be radially positioned between the intermediate portion 134 of the monolithic body 102 and the turbine blades 38 of the turbine 28 and at least partially define a flow path (FP) of the combustion gases 26 flowing through the turbine 28 (see Figure 2 ).

[0047] In a non-limiting example, the sealing portion 154 can include a forward end 156. The forward end 156 of the sealing portion 154 can be formed and / or extend between the opposing inclined surfaces 120, 122 of the monolithic body 102. The forward end 156 can be formed substantially adjacent to the second end 146 of the non-linear section 142, perpendicular to the second end, and / or axially upstream of the second end. The forward end 156 of the sealing portion 154 can also be positioned axially upstream of the forward end 106 of the support portion 104. As discussed herein, because the monolithic body 102 includes the support member 104 and the intermediate portion 134 having the non-linear section 142, the forward end 156 of the sealing portion 154 can be positioned axially upstream of the support portion 104 in a substantially cantilevered manner or approach without being directly coupled or connected to the support portion 104 and / or being integrally formed therewith. Thus, the leading end 156 and other portions of the seal portion 154 may thermally expand during operation of the turbine 28 without inducing undesirable mechanical stress or strain on other portions of the turbine shroud 100 (eg, the support portion 104 , the intermediate portion 134 ).

[0048] The sealing portion 154 may also include an aft end 158 that is positioned and / or formed opposite the forward end 156. The aft end 158 may also be positioned downstream of the forward end 156 so that the combustion gases 26 flowing through the flow path (FP) defined within the turbine 28 may flow past the adjacent forward end 156 before flowing past the adjacent aft end 158 of the sealing portion 154 of the monolithic body 102 (see FIG. Figure 2 The rear end 158 of the sealing portion 154 can be integrally formed with, radially adjacent to, and / or radially aligned with the rear section 136 of the intermediate portion 134 .

[0049] exist Figures 3 to 7In the non-limiting example shown, the sealing portion 154 may also include a hot gas path (HGP) surface 160. The HGP surface 160 of the sealing portion 154 may be integrally formed and / or extend axially between the forward end 156 and the aft end 158. Additionally, the HGP surface 160 may be integrally formed and / or extend circumferentially between the opposing inclined surfaces 120, 122 of the monolithic body 102. The HGP surface 160 may also be formed radially opposite the first surface 126 of the support portion 104 of the monolithic body 102. As discussed herein, the HGP surface 160 may be positioned adjacent to the hot gas flow path (FP) of the combustion gases 26 of the turbine 28. That is, and as Figure 2 As shown, the HGP surface 160 may be positioned, formed, facing, and / or directly exposed to the hot gas flow path (FP) of the combustion gases 26 flowing through the turbine casing 36 of the turbine 28 of the gas turbine system 10 (see Figure 2 ). Additionally, when included in the turbine casing 36, the HGP surface 160 of the monolithic body 102 of the turbine shroud 100 may be positioned radially adjacent the tip portion 48 of the airfoil 46 (see Figure 2 ).

[0050] As discussed herein, the monolithic body 102 of the turbine shroud 100 may include a first beveled surface 120 and a second beveled surface 122. Figure 5 and Figure 6 As shown in the non-limiting example of FIG, the opposed inclined surfaces 120, 122 of the monolithic body 102 may form a radially extending sidewall above the monolithic body 102 of the turbine shroud 100. More specifically, the first inclined surface 120 may be adjacent to and radially extend between the first surface 126 of the support portion 104 and the HGP surface 160 of the sealing portion 154, and the second inclined surface 122 may be adjacent to and radially extend between the first surface 126 of the support portion 104 and the HGP surface 160 of the sealing portion 154, circumferentially opposing the first inclined surface 120. In this way, the inclined surfaces 120, 122 may extend above various portions forming the monolithic body 102. Specifically, the inclined surfaces 120, 122 may extend above the support portion 104, the intermediate portion 134, and / or the sealing portion 154 to form a circumferential boundary, sidewall, and / or side surface of the monolithic body 102.

[0051] exist Figure 3 and Figure 7In the non-limiting example shown, the monolithic body 102 of the turbine shroud 100 may also include at least one inlet opening 168. The inlet opening 168 may be formed in the support portion 104. For example, the inlet opening 168 may be formed in and / or through the first surface 126 of the support portion 104 between the forward end 106 and the aft end 108. Additionally, one or more inlet openings 168 may also be formed in the first surface 126 and / or through the support portion 104 axially downstream of the non-linear section 142 of the intermediate portion 134. In a non-limiting example, the inlet opening 168 may be aligned with a cooling passage (see FIG. 1 ) formed through the monolithic body 102. Figure 8 More specifically, the inlet opening 168 formed in the first surface 126 may extend through at least a portion of the support portion 104 and may be in fluid communication with a cooling passage formed through and / or included in the support portion 104, the intermediate portion 134, and / or the sealing portion 154 of the monolithic body 102.

[0052] The turbine shroud 100 may also include one or more plenums and / or one or more cooling passages formed therein for cooling the turbine shroud 100 during operation of the turbine 28 of the gas turbine system 10 . Figures 8 and 9 , continue to refer to Figure 3-7 , depicting various plenums and / or cooling passages of the turbine shroud 100 . Figure 8 Shown along Figure 7 A side cross-sectional view of the turbine shroud 100 taken along line CS1-CS1 in FIG. Figure 9 Shown Figure 8 A perspective cross-sectional view of a turbine shroud 100 is shown. It should be understood that similarly numbered and / or named components may function in a substantially similar manner. For the sake of clarity, redundant explanations of these components have been omitted.

[0053] like Figures 8 and 9As shown, the turbine shroud 100 may include at least one plenum 200. The plenum 200 may be formed and / or extend through a portion of the monolithic body 102 of the turbine shroud 100. The plenum 200 may extend through the support portion 104 and the intermediate portion 134. More specifically, the plenum 200 may extend (radially) through at least a portion of the support portion 104, the intermediate portion 134, and / or the sealing portion 154 of the monolithic body 102. In the non-limiting example shown, the plenum 200 may extend through the entire support portion 104 and the intermediate portion 134, but may only extend through a portion of the sealing portion 154. In other non-limiting examples (not shown), the plenum 200 may not extend into the sealing portion 154 and / or extend (partially) through the sealing portion, but may terminate within the intermediate portion 134. In short, returning to Figure 4 , portions of the plenum 200 formed within the intermediate portion 134 and the sealing portion 154 (shown in phantom) may extend between and / or adjacent the opposing inclined surfaces 120, 122. Figure 8 and Figure 9 Only a single plenum 200 is shown in FIG, but it should be understood that the turbine shroud 100 may include more plenums (see FIG. Figure 12 ). Thus, the number of plenum chambers 200 depicted in the figure is merely exemplary.

[0054] In a non-limiting example, the plenum 200 may be fluidly coupled to and / or in direct fluid communication with one or more inlet openings 168 formed in the support portion 104. Figures 7 to 9 As shown, the plenum 200 can be in direct fluid communication with each inlet opening 168 formed in the first surface 126 of the support portion 104 of the turbine shroud 100. As discussed herein, the plenum 200 can receive cooling fluid (CF) flowing within the turbine 28 via the inlet openings 168 (see, Figure 8 and Figure 9 ), and a cooling fluid (CF) may be provided to different cooling channels formed in the turbine shroud 100 to cool the turbine shroud 100 during operation.

[0055] like Figure 8 and Figure 9 As shown, the turbine shroud 100 may include cooling passages 202 formed, positioned, and / or extending within the monolithic body 102 of the turbine shroud 100. More specifically, the cooling passages 202 of the turbine shroud 100 may be positioned within and / or extend through the sealing portion 154 of the monolithic body 102, positioned between and / or adjacent the forward end 156 and the aft end 158 of the sealing portion 154. Additionally, and as shown Figure 4As shown, a cooling passage 202 (shown in phantom) may extend through the sealing portion 154 of the monolithic body 102 between and / or adjacent the opposing inclined surfaces 120, 122. The cooling passage 202 may be positioned between the plenum 200 and the HGP surface 160 of the sealing portion 154. For example, the cooling passage 202 may be positioned radially within the sealing portion 154 between the plenum 200 and the HGP surface 160 of the sealing portion 154. Figure 8 and Figure 9 In the non-limiting example shown, and as discussed herein, at least a portion of the cooling passage 202 can be radially aligned with the plenum 200. Also as discussed herein, the cooling passage 202 can be in fluid communication with the plenum 200.

[0056] The plenum 200 and cooling passages 202 formed in the monolithic body 102 of the turbine shroud 100 may be separated by ribs 210. That is, and as Figure 8 and Figure 9 As shown, a rib 210 can be formed in the sealing portion 154 of the monolithic body 102 and located between the cooling passage 202 and the plenum 200, and can separate the cooling passage 202 from the plenum 200. Similar to other features discussed herein, the rib 210 can be integrally formed with the monolithic body 102 of the turbine shroud 100 and can be formed within the sealing portion 154 radially outward from the HGP surface 160. Additionally, the rib 210 can extend within the monolithic body 102 between the opposing ramps 120, 122 and can be integrally formed with the opposing ramps 120, 122.

[0057] To provide cooling fluid to the cooling passages 202, the unitary body 102 of the turbine shroud 100 may also include a plurality of impingement openings 212 formed therethrough. Figure 8 and Figure 9 As shown, the monolithic body 102 may include a plurality of impingement openings 212 formed through the ribs 210. The plurality of impingement openings 212 formed through the ribs 210 may fluidly couple the plenum 200 and the cooling passages 202. As discussed herein, in the gas turbine system 10 (see Figure 1 ), cooling fluid may flow from the plenum 200 through the plurality of impingement openings 212 to the cooling passages 202 to substantially cool the turbine shroud 100 .

[0058] It should be understood that Figure 8 and Figure 9As shown, the size and / or number of the impingement openings 212 formed through the ribs 210 are exemplary only. As such, the turbine shroud 100 may include larger or smaller impingement openings 212 and / or may include more or fewer impingement openings 212 formed therein. Additionally, while the size and / or shape of the plurality of impingement openings 212 are shown as being substantially uniform, it should be understood that each of the plurality of impingement openings 212 formed on the turbine shroud 100 may include a different size and / or shape. The size, shape, and / or number of the impingement openings 212 formed in the monolithic body 102 of the turbine shroud 100 may depend, at least in part, on the operating characteristics of the gas turbine system 10 during operation (e.g., exposure temperature, exposure pressure, location within the turbine casing 36, etc.). Additionally or alternatively, the size, shape, and / or number of the impingement openings 212 may depend, at least in part, on characteristics of the turbine shroud 100 / cooling passages 202 (e.g., thickness of the ribs 210 , size of the cooling passages 202 , volume of the cooling passages 202 , size / volume of the plenum 200 , etc.).

[0059] Also like Figure 8 and Figure 9 As shown, the monolithic body 102 of the turbine shroud 100 may include a plurality of front exhaust holes 224. The plurality of front exhaust holes 224 may be in fluid communication with the cooling passage 202. More specifically, each of the plurality of front exhaust holes 224 may be in fluid communication with the cooling passage 202 of the turbine shroud 100 and may extend axially therefrom. Figure 8 and Figure 9 In the non-limiting example shown, a plurality of forward exhaust holes 224 may extend through the monolithic body 102 from the cooling passage 202 to the forward end 156 of the sealing portion 154. That is, each of the plurality of forward exhaust holes 224 may be formed through the forward end 156 of the sealing portion 154 and may extend axially through the monolithic body 102 to fluidly couple to the cooling passage 202. During operation, and as discussed herein, the plurality of forward exhaust holes 224 may discharge cooling fluid from the cooling passage 202 adjacent the forward end 156 of the sealing portion 154 and into the hot gas flow path (FP) of the combustion gases 26 flowing through the turbine 28.

[0060] It should be understood that Figure 8 and Figure 9 The number of front exhaust holes 224 shown in the non-limiting example is merely exemplary. Thus, the front end 156 of the sealing portion 154 may include more than Figure 8 and 9The front exhaust apertures shown are more or fewer than the front exhaust apertures 224. Additionally, while shown as being substantially rectangular and linear, it should be understood that the front exhaust apertures 224 may be substantially circular and / or non-linear openings, passages, and / or manifolds.

[0061] Also like Figure 8 and Figure 9 As shown, the turbine shroud 100 may include a plurality of aft exhaust holes 232. The plurality of aft exhaust holes 232 may be in fluid communication with the cooling passage 202. More specifically, each of the plurality of aft exhaust holes 232 may be in fluid communication with the cooling passage 202 of the turbine shroud 100 and may extend axially therefrom. In a non-limiting example, the plurality of aft exhaust holes 232 may extend axially through the monolithic body 102 from the cooling passage 202 to the aft end 158 of the seal portion 154. That is, each of the plurality of aft exhaust holes 232 may be formed through the aft end 158 of the seal portion 154 and may extend axially through the monolithic body 102 to fluidly couple to the cooling passage 202. As discussed herein, the plurality of aft exhaust holes 232 may be adjacent to the aft end 158 of the seal portion 154, discharge cooling fluid from the cooling passage 202, and discharge it into the hot gas flow path (FP) of the combustion gases 26 flowing through the turbine 28.

[0062] Similar to the plurality of front exhaust holes 224, it should be understood that Figure 8 and Figure 9 The number of rear exhaust holes 232 shown in the non-limiting example is merely exemplary. Thus, the rear end 158 of the sealing portion 154 may include more than Figure 8 and 9 The rear exhaust holes shown may include more or fewer rear exhaust holes 232. Additionally, the shapes of the rear exhaust holes 232 (e.g., substantially rectangular and linear) are exemplary only, and each of the plurality of exhaust holes 232 included in the monolithic body 102 may be formed in a substantially different shape (e.g., a non-linear opening, passageway, and / or manifold).

[0063] like Figure 8 and Figure 9 As shown, the turbine shroud 100 may also include at least one shot peening screen 300. More specifically, the monolithic body 102 of the turbine shroud 100 may include the shot peening screen 300 integrally formed therein. In a non-limiting example, the monolithic body 102 may include a single shot peening screen 300. In other non-limiting examples discussed herein (see Figure 12), the monolithic body 102 may include more than one shot peening screen 300. As described herein, the shot peening screen 300 included in the monolithic body 102 may prevent shot from passing through the shot peening screen 300 when a shot peening process is performed on the monolithic body 102 of the turbine shroud 100. Additionally, the shot peening screen 300 integrally formed within the monolithic body 102 may provide additional support, structure, and / or rigidity to the monolithic body 102 (e.g., the middle portion 134) during operation.

[0064] The shot peening screen 300 may be positioned within the plenum 200 and may extend and / or be positioned within the middle portion 134 of the monolithic body 102. Additionally, the shot peening screen 300 may extend between the opposing inclined surfaces 120, 122 of the monolithic body 102. Thus, the shot peening screen 300 may extend over the entire circumferential length of the plenum 200 between the opposing inclined surfaces 120, 122 of the monolithic body 102 of the turbine shroud 100. Figure 8 and Figure 9 In the non-limiting example shown, the shot peening screen 300 also extends between the rear section 136 of the intermediate portion 134 and the non-linear section 142 of the intermediate portion 134. The shot peening screen 300 may be integrally formed within the plenum 200. The integrally formed shot peening screen prevents shot particles from passing through the shot peening screen during a shot peening process performed on the monolithic body of the turbine shroud. More specifically, the shot peening screen 300 may be integrally formed within the plenum 200 with the rear section 136 of the intermediate portion 134 and the non-linear section 142 of the intermediate portion 134, extending axially between the rear section 136 and the non-linear section 142. Thus, the shot peening screen 300 may extend along the entire axial length of the plenum 200, between the rear section 136 and the non-linear section 142. In a non-limiting example, the shot peening screen 300 may be integrally formed with the inner surface 234 of the rear section 136 and the inner surface 236 of the non-linear section 142 and may extend axially from and / or between the inner surfaces 234 and 236. Figure 8 and Figure 9 As shown, the inner surfaces 234 , 236 may define the plenum 200 of the monolithic body 102 of the turbine shroud 100 .

[0065] Figure 8 and Figure 9 Also shown, the shot peening screen 300 may be positioned between the support portion 104 and the sealing portion 154. More specifically, the shot peening screen 300 may be integrally formed within the monolithic body 102 and positioned radially between the inlet opening 168 formed in the support portion 104 and the cooling passage 202 formed in the sealing portion 154. Figure 8In the non-limiting example shown, the shot blasting screen 300 may be spaced a first distance (D1) from the inlet opening 168 formed in the support portion 104. Figure 8 As shown, the shot peening screen 300 can be spaced apart from the cooling passage 202 formed in the sealing portion 154 by a second distance (D2). In a non-limiting example, the second distance (D2) can be greater than the first distance (D1). Therefore, the shot peening screen 300 can be positioned radially closer to the inlet opening 168 than the cooling passage 202. In other non-limiting examples (see Figure 10 and 11 ), the shot peening screen 300 can be formed in different radial positions within the plenum chamber 200.

[0066] The shot peening screen 300 may include a top surface 302 and a bottom surface 304. The top surface 302 of the shot peening screen 300 may be positioned within the plenum 200 radially adjacent to the inlet opening 168 formed in the support portion 104 and / or may face the inlet opening 168. The bottom surface 304 of the shot peening screen 300 may be formed or positioned radially opposite the top surface 302. Additionally, the bottom surface 304 may be positioned within the plenum 200 radially adjacent to the ribs 210 and / or the cooling channels 202 formed in the sealing portion 154 and / or may face the ribs 210 and / or the cooling channels 202.

[0067] like Figure 8 and Figure 9 As shown, the shot peening screen 300 may also include a plurality of apertures 306 formed therethrough. That is, the plurality of apertures 306 may be formed in the shot peening screen 300 and / or may extend through the shot peening screen and be located between the top surface 302 and the bottom surface 304. The plurality of apertures may be spaced apart on the shot peening screen 300 to allow cooling fluid (CF) to flow from the inlet opening 168 through the plenum 200 and the shot peening screen 300 and to the cooling passage 200 during operation to cool the turbine shroud 100, as described herein. In a non-limiting example, each aperture in the plurality of apertures 306 may include a predetermined size (DIM). 306 ) (eg, diameter). The predetermined size (DIM) of each of the plurality of apertures 306 of the shot peening screen 300 is 306 ) may be sized to be smaller than the size (e.g., diameter) of shot that may be used in a shot peening process performed on the monolithic body 102. That is, the monolithic body 102 of the turbine shroud 100 may be subjected to a shot peening process after construction. To prevent shot from contacting the ribs 210 and / or becoming embedded in and subsequently blocking the impingement openings 212, a shot peening screen 300 may be integrally formed within the plenum 200. The plurality of apertures of the shot peening screen 300 are formed to include a predetermined size (DIM) that is smaller than the size of shot used during the shot peening process.306 ) can ensure that the shot cannot reach and / or contact the ribs 210 and / or the impingement openings 212. Instead, all shot that may flow through the inlet opening 168 may contact the shot blasting screen 300 and / or be captured / blocked by the shot blasting screen.

[0068] The predetermined size (DIM) of each of the plurality of apertures 306 formed in the shot blasting screen 300 is 306 ) may also be larger than the size (DIM) of the impact opening 212 formed in the rib 210. 212 ) (eg, diameter). In a non-limiting example, the predetermined size (DIM) of each of the plurality of apertures 306 is 306 ) may be the size of the impingement opening 212 (DIM 212 ) by about two (2) to six (6) times. 306 ) is larger than the size of the impact opening 212 (DIM 212 ), which ensures that the cooling fluid (CF) flowing through the plenum 200 does not experience a pressure drop when flowing through the apertures 306 and before flowing through the impingement openings 212 to the cooling passage 200, as described herein.

[0069] It should be understood that Figure 8 and Figure 9 As shown, the size and / or number of apertures 306 formed through the shot peening screen 300 are exemplary only. Thus, the shot peening screen 300 may include larger or smaller apertures 306 and / or may include more or fewer apertures 306 formed therein. Additionally, while the size and / or shape of the plurality of apertures 306 are shown as being substantially uniform, it should be understood that each of the plurality of apertures 306 formed through the shot peening screen may include a different size and / or shape. The size, shape, and / or number of apertures 306 formed through the shot peening screen 300 may depend, at least in part, on the size, number, and / or firing rate of the shot during the shot peening process performed on the turbine shroud 100.

[0070] In the gas turbine system 10 (see Figure 1 ), a cooling fluid (CF) may flow through the monolithic body 102 to cool the turbine shroud 100 during operation of the gas turbine system 10. More specifically, when the turbine shroud 100 is exposed to the combustion gases 26 flowing through the hot gas flow path of the turbine 28 during operation of the gas turbine system 10 (see Figure 2) and the temperature increases, cooling fluid may be provided to and / or may flow through various features (e.g., inlet openings 168, plenum 200, passages 202, holes 224, 232, etc.) formed through and / or extending through the monolithic body 102 to cool the turbine shroud 100. In a non-limiting example, cooling fluid may first be provided to the turbine shroud 100 from different portions, features, and / or regions of the turbine 28, adjacent the support portion 104 of the monolithic body 102. The cooling fluid may flow into the plenum 200 through one or more inlet openings 168 formed in the first surface 126 of the support portion 104. In a non-limiting example, the monolithic body 102 may include a plurality of inlet openings 168 formed in the first surface 126 of the support portion 104. Figure 8 and Figure 9 In the non-limiting example shown, cooling fluid may flow radially through each inlet opening 168 and may collect and / or mix within the plenum 200 .

[0071] The cooling fluid may flow from the inlet opening 168 through the plenum 200. More specifically, the cooling fluid may flow from the inlet opening 168 through the plenum 200 and toward the shot peening screen 300. The cooling fluid may then flow through the shot peening screen 300, and more specifically through the plurality of apertures 306 formed through the shot peening screen 300, and may continue to flow through the remainder of the plenum 200 toward the HGP surface 160 of the seal portion 154 and / or radially toward the cooling passages 202 formed within the seal portion 154. In a non-limiting example, the cooling fluid provided to the plenum 200 and flowing through the shot peening screen 300 may flow radially toward the ribs 210 and then through the plurality of impingement openings 212 to the cooling passages 202. In a non-limiting example, the cooling fluid may flow through the plurality of impingement openings 212 formed in the ribs 210 and may enter the cooling passages 202. The cooling fluid flowing into / through the cooling passage 202 may cool and / or receive heat from the HGP surface 160 of the sealing portion 154 of the turbine shroud 100. That is, once entering the cooling passage 202, the cooling fluid may be dispersed and / or may flow axially toward one of the forward end 156 or the aft end 158 of the sealing portion 154. Due to, for example, internal pressure within the cooling passage 202, the cooling fluid may flow through the cooling passage 202 to the opposite forward end 156 or the aft end 158.

[0072] Once the cooling fluid has flowed or dispersed through the cooling passage 202, the cooling fluid may flow to various exhaust holes 224, 232 formed through the sealing portion 154 of the monolithic body 102. For example, cooling fluid flowing to a portion of the cooling passage 202 located adjacent the forward end 156 may flow through the plurality of forward exhaust holes 224 and may then be exhausted adjacent the forward end 156 of the sealing portion 154 and into the hot gas flow path of the combustion gases 26 flowing through the turbine 28 (see FIG. Figure 2 ). In addition, cooling fluid flowing to a portion of the cooling passage 202 located adjacent the aft end 158 of the sealing portion 154 may flow through the plurality of aft exhaust holes 232, be discharged adjacent the aft end 158, and ultimately flow into the hot gas flow path of the combustion gases 26 flowing through the turbine 28 (see Figure 2 ).

[0073] Figures 10 and 11 An additional non-limiting example of a turbine shroud 100 including a unitary body 102 is shown. More specifically, Figure 10 and Figure 11 Shows something like Figure 8 A side cross-sectional view of a non-limiting example turbine shroud 100 is shown. It should be understood that similarly numbered and / or named components may function in a substantially similar manner. For the sake of clarity, repeated explanation of these components has been omitted.

[0074] As described herein, the shot peening screen 300 integrally formed within the plenum 200 of the monolithic body 102 may be spaced a first distance (D1) from the inlet opening 168 formed in the support portion 104 and may be spaced a second distance (D2) from the cooling passage 202 formed in the sealing portion 154. Figure 10 In the non-limiting example shown, the first distance (D1) and the second distance (D2) may be substantially equal or identical. Thus, the shot peening screen 300 may be positioned equidistant from the inlet opening 168 formed in the support portion 104 and the cooling channel 202 formed in the sealing portion 154.

[0075] and Figure 8 and Figure 10 The non-limiting examples shown are different, such as Figure 11 As shown, the second distance (D2) between the shot peening screen 300 and the cooling passage 202 may be less than the first distance (D1) between the shot peening screen 300 and the inlet opening 168. Thus, the shot peening screen 300 may be positioned radially closer to the cooling passage 202 formed in the sealing portion 154 than to the inlet opening 168 formed in the support portion 102.

[0076] Figure 12 Another non-limiting example of a turbine shroud 100 is shown. Specifically, Figure 12 A front view of a turbine shroud 100 is shown, which is similar to Figure 4 It should be understood that similarly numbered and / or named components may function in a substantially similar manner. For clarity, repeated explanations of these components have been omitted.

[0077] like Figure 12As shown, the monolithic body 102 of the turbine shroud 100 may include a plurality of plenums 200A, 200B (shown in phantom). In a non-limiting example, the turbine shroud 100 may include two distinct plenums 200A, 200B formed therein and separated by a wall 244. Both plenums 200A, 200B may extend (radially) through at least a portion of the support portion 104, the intermediate portion 134, and the sealing portion 154 of the monolithic body 102. A first plenum 200A may also extend and / or be formed circumferentially between the wall 244 and the first bevel surface 120, and a second plenum 200B may extend and / or be formed circumferentially between the wall 244 and the second bevel surface 122. Additionally, the first plenum 200A may be fluidly coupled to and / or in direct fluid communication with the inlet opening 168A formed in the support portion 104, and the second plenum 200B may be fluidly coupled to and / or in direct fluid communication with the inlet opening 168B formed in the support portion 104. Figure 8 and Figure 9 The plenum 200 discussed, the first plenum 200A and the second plenum 200B may each be in fluid communication with and / or fluidly coupled to the cooling passage 202 via a plurality of impingement openings 212 formed through the rib 210 (see FIG. Figure 8 During operation of the turbine system 10 (see Figure 1 ), the cooling fluid provided to the first plenum 200A and the separate cooling fluid provided to the second plenum 200B may both flow to the cooling channel 202 and / or be mixed within the cooling channel 202.

[0078] Additionally, as shown in a non-limiting example, the monolithic body 102 of the turbine shroud 100 may include a plurality of shot peening screens 300A, 300B. That is, where the turbine shroud 100 includes a plurality of different plenums 200A, 200B, the monolithic body 102 of the turbine shroud 100 may also include a plurality of different shot peening screens 300A, 300B formed therein. Figure 12 As shown, the first shot blasting screen 300A may be positioned within the first plenum 200A and may extend within the middle portion 134 of the monolithic body 102. The first shot blasting screen 300A may extend between the first inclined surface 120 of the opposing inclined surfaces 120, 122 of the monolithic body 102 and the wall 244 separating the first plenum 200A from the second plenum 200B. Figure 8 and Figure 9The shot peening screen 300, including the first shot peening screen 300A, may be integrally formed with the rear section 136 of the intermediate portion 134 and the non-linear section 142 of the intermediate portion 134 within the first plenum 200A and may extend axially between the rear section 136 and the non-linear section 142. Furthermore, the first shot peening screen 300A may be positioned within the first plenum 200A radially between the inlet opening 168A formed in the support portion 104 and the cooling passage 202 formed in the sealing portion 154.

[0079] Similar to the first shot peening screen 300A, the second shot peening screen 300B may be positioned within the second plenum 200B. More specifically, the second shot peening screen 300B may be positioned within the second plenum 200B and may extend within the middle portion 134 of the monolithic body 102. The second shot peening screen 300B may extend between the second middle inclined surface 122 of the opposing inclined surfaces 120, 122 of the monolithic body 102 and the wall 244. The second shot peening screen 300B may also be integrally formed with the rear section 136 of the middle portion 134 and the nonlinear section 142 of the middle portion 134 within the second plenum 200B and may extend axially between the rear section 136 and the nonlinear section 142. Furthermore, the second shot peening screen 300B may be positioned within the second plenum 200B radially between the inlet opening 168B formed in the support portion 104 and the cooling passage 202 formed in the sealing portion 154.

[0080] The turbine shroud 100 may be formed in a variety of ways. In one embodiment, the turbine shroud 100 may be made by casting. However, as described herein, additive manufacturing is particularly suitable for manufacturing the turbine shroud 100 including the monolithic body 102. As used herein, additive manufacturing (AM) may include any process that produces an object by successively layering material rather than removing material (as is the case with conventional processes). Additive manufacturing can form complex geometries without the use of any kind of tools, molds, or fixtures, and with little or no waste of material. Instead of machining a part from a solid plastic or metal blank (much of which is cut away and discarded), the only material used in additive manufacturing is that required to form the part. Additive manufacturing processes may include, but are not limited to, 3D printing, rapid prototyping (RP), direct digital manufacturing (DDM), binder jetting, selective laser melting (SLM), and direct metal laser melting (DMLM). In the present setting, DMLM or SLM has been found to be advantageous.

[0081] To illustrate an example of an additive manufacturing process, Figure 13A schematic diagram / block diagram of an exemplary computerized additive manufacturing system 900 for producing an object 902 is shown. In this example, the system 900 is arranged for DMLM. It should be understood that the general teachings of the present disclosure are equally applicable to other forms of additive manufacturing. The object 902 is shown as a turbine shroud 100 (see FIG. Figures 2 to 12 ). The AM system 900 generally includes a computerized additive manufacturing (AM) control system 904 and an AM printer 906. As will be described, the AM system 900 executes code 920, which includes a set of computer executable instructions defining the turbine shroud 100, to physically generate the object 902 using the AM printer 906. Each AM process may use a different raw material in the form of, for example, a fine-grained powder, a liquid (e.g., a polymer), a sheet, etc., a stock solution of which may be maintained in a chamber 910 of the AM printer 906. In this case, the turbine housing 100 may be made of a material that can withstand the gas turbine system 10 (see Figure 1 ) environment. As shown, the applicator 912 can form a thin layer of raw material 914, which is spread out as a blank canvas on the build plate 915 of the AM printer 906, and each consecutive slice of the final object will be formed from this blank canvas. In other cases, the applicator 912 can apply or print the next layer directly onto the previous layer as defined by code 920, such as when using a metal binder jetting process. In the example shown, the laser or electron beam 916 melts the particles for each slice as defined by code 920, but this may not be necessary when using a fast-setting liquid plastic / polymer. Various parts of the AM printer 906 can move to accommodate the addition of each new layer, for example, after each layer, the build platform 918 can be lowered and / or the chamber 910 and / or the applicator 912 can be raised.

[0082] AM control system 904 is shown as being implemented as computer program code on computer 930. To this extent, computer 930 is shown as including memory 932, processor 934, input / output (I / O) interface 936, and bus 938. Furthermore, computer 930 is shown in communication with external I / O devices / resources 940 and storage system 942. Generally, processor 934 executes computer program code stored in memory 932 and / or storage system 942 under instructions from code 920 representing the turbine shroud 100 described herein, such as AM control system 904. While executing the computer program code, processor 934 can read and / or write data to / from memory 932, storage system 942, I / O devices 940, and / or AM printer 906. Bus 938 provides a communication link between each component in computer 930, and I / O devices 940 can include any device that enables a user to interact with computer 940 (e.g., a keyboard, pointing device, display, etc.). Computer 930 merely represents various possible combinations of hardware and software. For example, processor 934 may include a single processing unit or one or more processing units distributed across one or more locations (e.g., on a client and a server). Similarly, memory 932 and / or storage system 942 may reside at one or more physical locations. Memory 932 and / or storage system 942 may include 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 930 may include any type of computing device, such as a network server, a desktop computer, a laptop computer, a handheld device, a mobile phone, a pager, a personal digital assistant, etc.

[0083] The additive manufacturing process begins with a non-transitory computer-readable storage medium (e.g., memory 932, storage system 942, etc.) storing code 920 representing the turbine shroud 100. As noted, the code 920 includes a set of computer-executable instructions defining the outer electrode that can be used to physically generate the tip when the code is executed by the system 900. For example, the code 920 can include a precisely defined 3D model of the turbine shroud 100 and can be executed by various well-known computer-aided design (CAD) software systems such as In this regard, code 920 may be generated in any file format, whether currently known or developed in the future, such as 3D Systems' stereolithography CAD program (e.g., DesignCAD, 3DMax, etc.). For example, code 920 may be in the Standard Tessellation Language (STL) format created by 3D Systems' stereolithography CAD program, or in the Additive Manufacturing File (AMF) format, a standard of the American Society of Mechanical Engineers (ASME), which is an Extensible Markup Language (XML)-based format designed to allow any CAD software to describe the shape and composition of any three-dimensional object to be manufactured on any AM printer. Code 920 may be converted between different formats, converted into a set of data signals, and transmitted, received, converted into code, stored, etc. as a set of data signals, as needed. Code 920 may be an input to system 900 and may originate from a part designer, an intellectual property (IP) provider, a design firm, an operator or owner of system 900, or from another source. In any case, AM control system 904 executes code 920 to separate turbine shroud 100 into a series of thin sheets that are assembled using AM printer 906 in successive layers of liquid, powder, sheet, or other material. In the DMLM example, each layer is melted into the precise geometry defined by the code 920 and fused to the previous layer. The turbine shroud 100 can then be exposed to any of a variety of finishing processes, such as those described herein for reshaping or other minor machining, sealing, polishing, shot peening, etc.

[0084] Technical effects of the present disclosure include, for example, providing a turbine shroud formed from a monolithic body including at least one shot peening screen integrally formed therein. During a shot peening process performed on the monolithic body of the turbine shroud, the integrally formed shot peening screen prevents shot particles from passing through the shot peening screen. The integrally formed shot peening screen reduces or eliminates the possibility of shot particles undesirably contacting and / or becoming embedded in the turbine shroud, ultimately blocking impingement openings and / or cooling passages also integrally formed therein.

[0085] The terms used herein are only used to describe the purpose of specific embodiments and are not intended to limit the present disclosure. As used herein, the singular forms "a", "an" and "the" are intended to also include the plural forms, unless the context clearly indicates otherwise. It will be further understood that when used in the specification, the terms "comprise" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, parts and / or their groups. "Optional" or "optionally" means that the event or situation described subsequently may or may not occur, and the description includes instances where the event occurs and instances where the event does not occur.

[0086] As used throughout the specification and claims, approximate language may be used to modify any quantitative representation that can be permissibly varied without resulting in a change in the basic function to which it relates. Accordingly, a value modified by one or more terms, such as "about," "approximately," and "substantially," is not limited to the precise value specified. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Here and throughout the specification and claims, range limitations may be combined and / or interchanged, and such ranges are identified and include all subranges contained therein unless the context or language indicates otherwise. "About" applied to a particular value of a range applies to both values ​​and may indicate + / - 10% of one or more of the stated values ​​unless otherwise dependent on the precision of the instrument used to measure the value.

[0087] The corresponding structures, materials, actions and equivalents of all means or step plus function elements in the following claims are intended to include any structure, material or action for performing the function in conjunction with other claimed elements for specific protection. The description of the present disclosure has been given for the purpose of illustration and description, but it is not intended to be exhaustive or to limit the disclosure to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and essence of the present disclosure. The embodiments have been selected and described in order to best explain the principles and practical applications of the present disclosure and to enable others skilled in the art to understand the various embodiments of the present disclosure with various modifications suitable for the intended specific use.

Claims

1. A turbine shroud (100) for a turbine system (10), the turbine shroud (100) comprising: A monolithic body (102), comprising: a support portion (104) directly coupled to a turbine (28) housing (36) of the turbine system (10); a middle portion (134) integral with the support portion (104) and extending away from the support portion; a sealing portion (154) integral with the middle portion (134) and opposite to the support portion (104), the sealing portion (154) including a front end (156) and a rear end (158) positioned opposite to the front end (156), and a hot gas path surface (160) extending between the forward end (156) and the aft end (158); at least one inlet opening (168, 168A, 168B) formed in the support portion (104); at least one plenum (200) in fluid communication with the at least one inlet opening (168, 168A, 168B), the at least one plenum (200) extending through the support portion (104) and the intermediate portion (134); a cooling passage (202) extending through the sealing portion (154) between the forward end (156) and the aft end (158) of the sealing portion (154), the cooling passage (202) being positioned between the at least one plenum (200) and the hot gas path surface (160) of the sealing portion (154), wherein the cooling channel (202) is in fluid communication with the at least one plenum (200); and at least one shot blasting screen (300) positioned within the at least one plenum (200) and extending within the intermediate portion (134), the at least one shot blasting screen (300) including a plurality of apertures (306) formed therethrough, When a shot peening process is performed on the monolithic body (102), the at least one shot peening screen (300) prevents shot particles from passing through the at least one shot peening screen (300).

2. The turbine shroud (100) of claim 1, wherein the at least one shot peening screen (300) is positioned between the at least one inlet opening (168, 168A, 168B) formed in the support portion (104) and the cooling passage (202).

3. The turbine shroud (100) of claim 2, wherein the at least one shot peening screen (300) is positioned as one of: equidistant from the at least one inlet opening (168, 168A, 168B) formed in the support portion (104) and the cooling channel (202), or radially closer to the at least one inlet opening (168, 168A, 168B) than the cooling passage (202), or Radially closer to the cooling passage (202) than the at least one inlet opening (168, 168A, 168B).

4. The turbine shroud (100) of claim 1, wherein the unitary body (102) includes two opposing inclined surfaces extending adjacent to and between the support portion (104) and the sealing portion (154), and the two opposing inclined surfaces are positioned opposite each other, and The at least one shot blasting screen (300) extends between the two opposing inclined surfaces.

5. The turbine shroud (100) of claim 4, wherein the intermediate portion (134) of the monolithic body (102) further comprises: a rear section (136) extending between the support portion (104) and the sealing portion (154), adjacent to the at least one plenum chamber (200), the rear section (136) extending between the two opposing inclined surfaces; and A nonlinear section (142) extends between the support portion (104) and the sealing portion (154), is adjacent to the at least one plenum chamber (200) and is axially opposite to the rear section (136), and extends between the two opposing inclined surfaces.

6. The turbine shroud (100) of claim 5, wherein the at least one shot peening screen (300) is integrally formed with the rear section (136) of the middle portion (134) and the non-linear section (142) of the middle portion (134) within the at least one plenum (200) and extends between the rear section and the non-linear section.

7. The turbine shroud (100) of claim 4, wherein the at least one plenum (200) further comprises: a first plenum (200A) extending through the support portion (104) and the intermediate portion (134) and adjacent a first of the two opposing inclined surfaces; and A second plenum chamber (200B) extends through the support portion (104) and the intermediate portion (134), adjacent to the second of the two opposing inclined surfaces, and the second plenum chamber (200B) is separated from the first plenum chamber (200A) by a wall (244) extending between the support portion (104) and the sealing portion (154).

8. The turbine shroud (100) of claim 7, wherein the at least one shot peening screen (300) further comprises: a first shot blasting screen (300A) positioned within the first plenum (200A) and extending within the intermediate portion (134), the first shot blasting screen (300A) extending between the first of the two opposing inclined surfaces and the wall (244); and A second shot blasting screen (300B) is positioned within the second plenum (200B) and extends within the intermediate portion (134), the second shot blasting screen (300B) extending between the second of the two opposing inclined surfaces and the wall (244).

9. The turbine shroud (100) of claim 1, wherein the monolithic body (102) further comprises: a rib (210) formed in the sealing portion (154), the rib (210) being positioned between the at least one plenum (200) and the cooling channel (202) and separating the at least one plenum from the cooling channel; and a plurality of impingement openings (212) formed through the rib (210) to fluidly couple the cooling channel (202) to the at least one plenum (200), wherein a size of each of the plurality of apertures (306) of the at least one shot peening screen (300) is larger than a size of each of the plurality of impingement openings (212) formed through the rib (210).

10. A turbine system (10), comprising: a turbine (28) housing (36); a rotor (30) extending axially through the turbine (28) housing (36); a plurality of turbine blades (38) positioned circumferentially about the rotor (30) and extending radially from the rotor; and A plurality of turbine shrouds (100) are directly coupled to the turbine (28) casing (36) and positioned radially between the turbine (28) casing (36) and the tip portions (48) of the plurality of turbine blades (38), each turbine shroud of the plurality of turbine shrouds (100) being a turbine shroud (100) according to any one of claims 1 to 9.

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