High-temperature gas path component including a rear exhaust duct and a rear flange

Abstract

To provide turbine shrouds and stator vanes that include a plurality of aft end exhaust conduits and aft end flanges.SOLUTION: A turbine shroud (100) for turbine systems includes a forward end (102) including a first hook (106) coupled to a turbine casing, an aft end (104) including a second hook (108) coupled to the turbine casing, and a base portion (126) extending between the forward end and the aft end. The base portion includes an inner surface (124) facing a hot gas flow path for the turbine system. In addition, the turbine shroud includes a flange (130) extending from the aft end and positioned radially between the base portion and the second hook, a cooling passage (132) positioned within the base portion adjacent to the inner surface, and at least one aft end exhaust conduit (138) in fluid communication with the cooling passage. The aft end exhaust conduit extends through the aft end, radially between the base portion and the flange.SELECTED DRAWING: Figure 6

Description

Technical Field

[0001] The present disclosure generally relates to high temperature gas path components for turbine systems, and more particularly to turbine shrouds and stator vanes including a plurality of rear end exhaust ducts and rear end flanges.

Background Art

[0002] Conventional turbomachines such as gas turbine systems are utilized to generate power for an electric generator. Generally, a gas turbine system generates power by passing a fluid (e.g., hot gas) through the turbine components of the gas turbine system. More specifically, the intake air can be drawn into and compressed by a compressor. Once compressed, the intake air is mixed with fuel to form combustion products, which can be ignited by a combustor of the gas turbine system to form the operating fluid (e.g., hot gas) of the gas turbine system. The fluid can then flow through a fluid flow path to rotate a plurality of rotating blades and a rotor or shaft of the turbine components to generate power. The fluid can be directed through the turbine components 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 rotate the rotor of the gas turbine system, an electric generator coupled to the rotor can generate power from the rotation of the rotor.

[0003] To improve operating efficiency, the turbine component includes a turbine shroud and / or a nozzle band and can further define a flow path for the operating fluid. The turbine shroud can be positioned, for example, radially adjacent to the rotating blades of the turbine component, guide the operating fluid within the turbine component, and / or define an outer boundary of the fluid flow path of the operating fluid. During operation, the turbine shroud may be exposed to the hot operating fluid flowing through the turbine component. Over time and / or during exposure, the turbine shroud may undergo undesirable thermal expansion. Due to the thermal expansion of the turbine shroud, the shroud may be damaged and / or the shroud may not be able to maintain a seal within the turbine component to define the fluid flow path of the operating fluid. If the turbine shroud is damaged or a sufficient seal is not formed within the turbine component, the operating fluid may leak from the flow path, thus reducing the operating efficiency of the turbine component and the entire turbine system.

[0004] To minimize thermal expansion, the turbine shroud is typically cooled. One conventional process for cooling the turbine shroud involves impingement cooling. Impingement cooling utilizes holes or openings formed through the turbine shroud to provide cooling air to various portions of the turbine shroud during operation. However, these conventional processes present new problems that reduce the operating efficiency of the system. For example, while the turbine shroud is being cooled during operation, the fluid (e.g., air) used to cool the shroud absorbs heat. When discharged from the shroud, this heated cooling fluid can flow directly adjacent to, be exposed to, and / or contact portions of the turbine casing that can support the turbine shroud and other various components. The casing and / or components that support the turbine shroud and / or other various components may be adversely affected or influenced by exposure to the hot cooling fluid. That is, exposure to the hot cooling fluid may cause the material forming the casing to degrade prematurely and undesirably, resulting in a shorter operating life.

SUMMARY OF THE INVENTION

[0005] A first aspect of the present disclosure provides a turbine shroud coupled to a turbine casing of a turbine system. The turbine shroud includes a front end including a first hook coupled to the turbine casing, a rear end positioned on the opposite side of the front end and including a second hook coupled to the turbine casing, a base portion extending between the front end and the rear end and positioned radially opposite the first and second hooks coupled to the turbine casing, the base portion including an inner surface facing a high-temperature gas flow path for the turbine system, a flange extending from the rear end and positioned radially between the base portion and the second hook, a cooling passage positioned within the base portion adjacent to the inner surface, and at least one rear-end exhaust duct in fluid communication with the cooling passage and extending radially between the base portion and the flange and through the rear end.

[0006] A second aspect of the present disclosure is a turbine system, comprising a turbine casing, a first stage positioned within the turbine casing, within the turbine casing, a plurality of turbine blades circumferentially positioned around a rotor, downstream of the plurality of turbine blades, a plurality of stator vanes positioned within the turbine casing, and a plurality of turbine shrouds radially adjacent to the plurality of turbine blades and positioned upstream of the plurality of stator vanes, each of the plurality of turbine shrouds comprising a front end including a first hook coupled to the turbine casing, a rear end positioned opposite the front end and including a second hook coupled to the turbine casing, a base portion extending between the front end and the rear end and positioned radially opposite the first hook and the second hook coupled to the turbine casing, the base portion including an inner surface facing a high-temperature gas flow path for the turbine system, a flange extending from the rear end and positioned radially between the base portion and the second hook, a cooling passage positioned within the base portion adjacent to the inner surface, and at least one rear-end exhaust duct in fluid communication with the cooling passage, the at least one rear-end exhaust duct extending radially between the base portion and the flange and through the rear end, the turbine system comprising the first stage including the plurality of turbine shrouds.

[0007] A third aspect of the present disclosure provides a stator vane positioned within a turbine casing of a turbine system. The stator vane includes a front end, a rear end positioned opposite the front end, a base portion extending between the front end and the rear end and positioned radially opposite the turbine casing, the base portion including an inner surface facing a high-temperature gas flow path for the turbine system, a flange extending from the rear end and positioned radially between the base portion and the turbine casing, a cooling passage positioned adjacent to the base portion and the inner surface, and at least one rear-end exhaust duct in fluid communication with the cooling passage, the at least one rear-end exhaust duct extending radially between the base portion and the flange and through the rear end.

[0008] Exemplary aspects of the present disclosure are designed to solve the problems described herein and / or other problems not considered.

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

Brief Description of the Drawings

[0010]

Figure 1

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Figure 17

DETAILED DESCRIPTION OF THE INVENTION

[0011] It should be noted that the drawings of the present disclosure are not to scale. The drawings are intended to illustrate only typical aspects of the present disclosure and should not be considered as limiting the scope of the present disclosure. In the drawings, like reference numerals represent like elements among the drawings.

[0012] As a first issue, in order to clearly explain the present disclosure, when referring to related mechanical components within the scope of the present disclosure, it is necessary to select specific technical terms. When doing so, to the extent possible, general industrial technical terms are used and utilized in the same meaning as their accepted meaning. Unless otherwise specified, such technical terms should be given a broad interpretation consistent with the context of this application and the appended claims. One of ordinary skill 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 a single part may include multiple components in another context and may be referred to in another context. Alternatively, what may be described herein as including multiple components may be referred to elsewhere as a single part.

[0013] In addition, several descriptive terms can be used consistently in this specification, and it will be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise stated. As used herein, "downstream" and "upstream" are terms indicating directions with respect to the working fluid passing through the turbine engine, or for example, the flow of air through a combustor, or the flow of a coolant through one of the component systems of the turbine. The term "downstream" corresponds to the direction of the fluid flow, and the term "upstream" refers to the opposite direction of the flow. The terms "forward" and "rearward" refer to directions, unless otherwise specified, where "forward" refers to the front of the engine or the compressor end, and "rearward" refers to the rear of the engine or the turbine end. In addition, the terms "leading" and "trailing" are used and / or can be understood in a similar description as the terms "forward" and "rearward", respectively. Often, it is necessary to describe components at 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 / direction of an object along the axis A that is substantially parallel to the rotational axis of the turbine system (particularly, the rotor section). Further, as used herein, the terms "radial" and / or "radially" refer to the relative position / direction of an object along the direction "R" (see FIG. 1) that is substantially perpendicular to the axis A and intersects the axis A at only one location. Finally, the term "circumferential" refers to movement or position around the axis A (e.g., direction "C").

[0014] As shown above, the present disclosure provides a high temperature gas path component for a turbine system, and more particularly, a turbine shroud and stator vanes including a plurality of rear end exhaust ducts and a rear end flange.

[0015] These and other embodiments are discussed below with reference to FIGS. 1-17. However, those skilled in the art will readily understand that the detailed description given herein with respect to these figures is for illustrative purposes only and should not be construed as limiting.

[0016] FIG. 1 shows a schematic diagram of an exemplary gas turbine system 10. The gas turbine system 10 can include a compressor 12. The compressor 12 compresses the incoming air 18 flow. The compressor 12 delivers the compressed air 20 flow to a combustor 22. The combustor 22 mixes the compressed air 20 flow with the pressurized fuel 24 flow and ignites this mixture to produce a combustion gas 26 flow. Although only a single combustor 22 is shown, the gas turbine system 10 may include any number of combustors 22. Next, the combustion gas 26 flow is typically delivered to a turbine 28 that includes a plurality of turbine blades including airfoils (see FIG. 2) and stator vanes (see FIG. 2). The combustion gas 26 flow drives the turbine 28, more specifically, the plurality of turbine blades of the turbine 28, to generate mechanical work. The mechanical work generated at the turbine 28 can be used to drive the compressor 12 via a rotor 30 extending through the turbine 28 and to drive an external load 32 such as a generator.

[0017] The gas turbine system 10 can also include an exhaust frame 34. As shown in FIG. 1, the exhaust frame 34 may be positioned adjacent to the turbine 28 of the gas turbine system 10. More specifically, the exhaust frame 34 can be positioned adjacent to the turbine 28 and can be positioned substantially downstream of the turbine 28 and / or the flow of the combustion gas 26 flowing from the combustor 22 to the turbine 28. As discussed herein, a portion of the exhaust frame 34 (e.g., the outer casing) may be directly coupled to the enclosure, shell, or casing 36 of the turbine 28.

[0018] After the combustion gas 26 flows through and drives the turbine 28, the combustion gas 26 can be exhausted, introduced, and / or discharged through the exhaust frame 34 in the flow direction (D). In the non-limiting example shown in FIG. 1, the combustion gas 26 can flow through the exhaust frame 34 in the flow direction (D) and can be discharged from the gas turbine system 10 (e.g., to the atmosphere). In another non-limiting example where 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 gas 26 can be discharged from the exhaust frame 34 and may flow into the heat recovery boiler of the combined cycle power plant in the flow direction (D).

[0019] Referring to FIG. 2, a portion of the turbine 28 is shown. Specifically, FIG. 2 shows a side view of a portion of the turbine 28 that includes a stage (one shown) of the turbine blades 38 and a stage (one shown) of the stator vanes 40 positioned within the casing 36 of the turbine 28. As discussed herein, each stage of the turbine blades 38 (e.g., the first stage, the second stage (not shown), the third stage (not shown)) may be coupled to the rotor 30 and circumferentially positioned around or about it, and may include a plurality of turbine blades 38 that can be driven by the combustion gas 26 to rotate the rotor 30. As shown, the plurality of turbine blades 38 can also extend radially from the rotor 30. In addition, each stage of the stator vanes 40 (e.g., the first stage, the second stage (not shown), the third stage (not shown)) may include a plurality of stator vanes that can be coupled to the casing 36 of the turbine 28 via a retaining component 41 extending from the casing 36 and / or circumferentially positioned around or about it. In the non-limiting example shown in FIG. 2, the stator vane 40 can include an outer platform 42 directly coupled to the retaining component 41 and an inner platform 44 positioned on the opposite side of the outer platform 42, and / or can include a plurality of high temperature gas path (HGP) components formed as or including them. The stator vane 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 vane 40 can define a flow path (FP) of the combustion gas 26 flowing over the stator vane 40. As discussed herein, the stator vane 40, and more specifically the outer platform 42, can be positioned downstream directly adjacent to the turbine shroud of the turbine 28.

[0020] Each turbine blade 38 of the turbine 28 can extend radially from the rotor 30 and include an airfoil 46 positioned within the flow path (FP) of the combustion gas 26 flowing through the turbine 28. Each airfoil 46 can include a tip portion 48 positioned on the radially opposite side of the rotor 30. The turbine blade 38 can also include a platform 50 positioned on the side 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 gas 26 of the turbine blade 38. The turbine blade 38 and the stator vane 40 may also be positioned axially adjacent to each other within the casing 36. In the non-limiting example shown in FIG. 2, the stator vane 40 may be positioned downstream axially adjacent to the turbine blade 38. For clarity, not all of the turbine blades 38, stator vanes 40, and / or rotor 30 of the turbine 28 are shown. Additionally, only a portion of the turbine blades 38 and stator vanes 40 of a single stage of the turbine 28 are shown in FIG. 2, but the turbine 28 can include multiple stages of turbine blades and stator vanes positioned axially throughout the entire casing 36 of the turbine 28.

[0021] The turbine 28 (see FIG. 1) of the gas turbine system 10 can also include a plurality of turbine shrouds 100 contained within the turbine 28. The turbine 28 can include a stage (one shown) of the turbine shroud 100. The turbine shroud 100 can correspond to a stage of the turbine blades 38 and / or a stage of the stator vanes 40. That is, as discussed herein, the stage of the turbine shroud 100 is positioned within the turbine 28 adjacent to the stage of the turbine blades 38 and / or the stage of the stator vanes 40 and can interact with the flow path (FP) of the combustion gas 26 flowing through the turbine 28 to provide a seal and / or define the flow path (FP). In the non-limiting example shown in FIG. 2, the stage of the turbine shroud 100 may be positioned radially adjacent to the stage of the turbine blades 38 and / or may substantially surround or enclose the stage of the turbine blades 38. The turbine shroud 100 can be positioned radially adjacent to the tip portion 48 of the airfoil 46 of the turbine blade 38. Additionally, in the non-limiting example, the turbine shroud 100 may also be positioned axially adjacent to and / or upstream of the stator vanes 40 of the turbine 28. Also, the turbine shroud 100 can be positioned between two adjacent stages of the stator vanes that surround and / or are positioned on both axial sides of a single stage of the turbine blades.

[0022] The stages of the turbine shroud can include a plurality of turbine shrouds 100 that can be directly coupled to and / or circumferentially positioned around the casing 36 of the turbine 28. In the non-limiting example shown in FIG. 2, the turbine shroud 100 can be directly coupled to the casing 36 via a coupling component 52 that extends radially inward (e.g., toward the rotor 30) from the casing 36 of the turbine 28. As discussed herein, the coupling component 52 can include an aperture 54 configured to couple to and / or receive fasteners or hooks (see FIG. 3) 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 coupling component 52 may be coupled and / or fixed to the casing 36 of the turbine 28. More specifically, the coupling component 52 may be circumferentially disposed around the casing 36 and may be positioned radially adjacent to the turbine blade 38. In another non-limiting example, the coupling component 52 may be integrally formed with and / or be a part of the casing 36 to directly couple, position, and / or secure the turbine shroud 100 to the casing 36. Similar to the turbine blade 38 and / or the stator vane 40, only a portion of the stages of the turbine shroud 100 of the turbine 28 is shown in FIG. 2, but the turbine 28 can include a plurality of stages of the turbine shroud 100 that are axially positioned throughout the casing 36 of the turbine 28 and are coupled to the casing 36 using the coupling component 52.

[0023] Referring to FIGS. 3-6, various views of the turbine shroud 100 of the turbine 28 for the gas turbine system 10 of FIG. 1 are shown. Specifically, FIG. 3 shows an isometric view of the turbine shroud 100, FIG. 4 shows a top view of the turbine shroud 100, FIG. 5 shows a side view of the turbine shroud 100, and FIG. 6 shows a cross-sectional side view of the turbine shroud 100.

[0024] In the non-limiting example shown, the turbine shroud 100 may include a single body. That is, as shown in FIGS. 3-6, the turbine shroud 100 may include a single body and / or be formed as a single body such that the turbine shroud 100 is a single, continuous, and / or non-separated component or part. In the non-limiting examples shown in FIGS. 3-6, since the turbine shroud 100 is formed from a single body, the turbine shroud 100 may not require the construction, joining, bonding, and / or assembly of various parts to fully form the turbine shroud 100, and / or may not require the construction, joining, bonding, and / or assembly of various parts before the turbine shroud 100 can be installed and / or implemented within the turbine system 10 (see FIG. 2). Rather, once a single, continuous, and / or non-separated single body for the turbine shroud 100 is constructed, as discussed herein, the turbine shroud 100 can be immediately installed within the turbine system 10.

[0025] The single body of the turbine shroud 100, as well as 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 a single body may be formed by 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. Additionally, the single body of the turbine shroud 100 can be formed from any material that can be utilized by an additive manufacturing process to form the turbine shroud 100 and / or that can withstand the operating characteristics (e.g., exposure temperature, exposure pressure, etc.) that the turbine shroud 100 within the gas turbine system 10 experiences during operation.

[0026] In another non-limiting example (see FIG. 9), the turbine shroud 100 may be formed as a plurality of separate pieces and / or sections that are constructed separately before being installed within the gas turbine system 10 and subsequently assembled, joined, bonded, and / or attached to each other. The turbine shroud 100 can be assembled using any suitable technique or process known for joining / forming components, including but not limited to welding, brazing, fusing, bonding, etc. Additionally, the turbine shroud 100 formed from separate sections and / or pieces can undergo a process for joining / forming the turbine shroud 100 from the separate pieces and can be formed from any material capable of withstanding the operating characteristics (e.g., exposure temperature, exposure pressure, etc.) that the turbine shroud 100 within the gas turbine system 10 experiences during operation.

[0027] The turbine shroud 100 can also include various ends, sides, and / or surfaces. For example, as shown in FIGS. 3 and 4, the turbine shroud 100 can include a front end 102 and a rear end 104 positioned on the opposite side of the front end 102. The front end 102 can be positioned upstream of the rear end 104 such that the combustion gas 26 flowing through the flow path (FP) defined within the turbine 28 can flow through the adjacent front end 102 before flowing through the adjacent rear end 104 of the turbine shroud 100. As shown in FIGS. 3 and 4, the front end 102 can include a first hook 106 configured to couple and / or engage with the coupling component 52 of the casing 36 so that the turbine 28 can couple, position, and / or secure the turbine shroud 100 within the casing 36 (see FIG. 2). Additionally, the rear end 104 can include a second hook 108 positioned and / or formed on the turbine shroud 100 on the opposite side of the first hook 106. Similar to the first hook 106, the second hook 108 can be configured to couple and / or engage with the coupling component 52 of the casing 36 so that the turbine 28 can couple, position, and / or secure the turbine shroud 100 within the casing 36 (see FIG. 2).

[0028] Additionally, the turbine shroud 100 can also include a first slash surface or side 110 (hereinafter, "the first side 110") and a second slash surface or side 112 (hereinafter, "the second side 112") positioned on the opposite side of the first side 110. As shown in FIGS. 3 and 4, the first side 110 and the second side 112 can each be formed or positioned proximate to the front end 102 and the rear end 104, and can also extend between and / or be positioned between the front end 102 and the rear end 104.

[0029] As shown in FIGS. 3-5, the turbine shroud 100 may also include an outer surface 120. The outer surface 120 can face a cooling chamber 122 (see FIG. 5) formed between the turbine shroud 100 and the turbine casing 36 (see FIG. 2). More specifically, the outer surface 120 can be positioned, formed, face, and / or directly expose a cooling chamber 122 formed between the turbine shroud 100 and the turbine casing 36 of the turbine 28. In a non-limiting example, the cooling chamber 122 may be at least partially defined by an opening 54 of a coupling component 52 for the casing 36. As discussed herein, the cooling chamber 122 formed between the turbine shroud 100 and the turbine casing 36 can receive and / or provide a cooling fluid during operation of the turbine 28. In addition to facing the cooling chamber 122, the outer surface 120 of the turbine shroud 100 can also be formed and / or positioned between a front end 102 and a rear end 104, as well as between a first side surface 110 and a second side surface 112, respectively.

[0030] The turbine shroud 100 may also include an inner surface 124 formed on the opposite side of the outer surface 120. That is, as shown in the non-limiting examples of FIGS. 3 and 5, the inner surface 124 of the turbine shroud 100 may be formed on the radially opposite side of the outer surface 120. Returning briefly to FIG. 2 and continuing to refer to FIGS. 3 and 5, the inner surface 124 may face the high-temperature gas flow path (FP) of the combustion gas 26 flowing through the turbine 28 (see FIG. 2). More specifically, the inner surface 124 can be positioned, formed, face, and / or directly exposed to the high-temperature gas flow path (FP) of the combustion gas 26 flowing through the turbine casing 36 of the turbine 28 for the gas turbine system 10. In addition, the inner surface 124 of the turbine shroud 100 can be positioned radially adjacent to the tip portion 48 of the airfoil 46 (see FIG. 2). The inner surface 124 is formed between the front end 102 and the rear end 104 of the turbine shroud 100 and / or can extend axially. In addition, the inner surface 124 is formed between the opposing side surfaces 110, 112 of the turbine shroud 100 and / or can extend circumferentially. The inner surface 124 may also be formed on the radially opposite sides of the first hook 106 and the second hook 108, respectively.

[0031] Referring to FIG. 6 and continuing to refer to FIGS. 3-5, additional features of the turbine shroud 100 are discussed herein. The turbine shroud 100 may include a base portion 126. As shown in FIG. 6, the base portion 126 can be formed as an integral part of the turbine shroud 100. Additionally, the base portion 126 may include an inner surface 124, and / or the inner surface 124 may be formed on the base portion 126 of the turbine shroud 100. The base portion 126 of the turbine shroud 100 can be formed, positioned, and / or extend between a front end 102 and a rear end 104, as well as between a first side surface 110 and a second side surface 112, respectively. The base portion 126 may also be formed integrally with the first side surface 110 and the second side surface 112 of the turbine shroud 100. In a non-limiting example, the base portion 126 may also be positioned radially opposite and / or radially inward from first hook 106 and second hook 108 of the turbine shroud 100 that are coupled to the turbine casing 36 (see FIG. 2). As discussed herein, the base portion 126 of the turbine shroud 100 can at least partially form and / or define at least one cooling passage within the turbine shroud 100.

[0032] The turbine shroud 100 may include a collision portion 128. Similar to the base portion 126, as shown in FIG. 6, the collision portion 128 can be formed as an integral part of the turbine shroud 100. The collision portion 128 may include an outer surface 120, and / or the outer surface 120 may be formed on the collision portion 128 of the turbine shroud 100. The collision portions 128 of the turbine shroud 100 can be formed, positioned, and / or extend between the front end 102 and the rear end 104, as well as between the first side surface 110 and the second side surface 112, respectively. Additionally, similar to the base portion 126, the collision portion 128 can be formed integrally with the first side surface 110 and the second side surface 112 of the turbine shroud 100. As shown in FIG. 6, the collision portion 128 can be positioned radially adjacent to the base portion 126 and / or can be positioned radially between the base portion 126 and the first hook 106 and the second hook 108, respectively. The collision portions 128 of the turbine shroud 100, together with the base portion 126, can at least partially form and / or define at least one cooling passage within the turbine shroud 100 as discussed herein.

[0033] As shown in FIG. 6, the turbine shroud 100 may also include a flange 130. The flange 130 can extend from the rear end 104 of the turbine shroud 100. More specifically, the flange 130 can extend (substantially) axially from the rear end 104 and can be positioned radially between the base portion 126 of the turbine shroud 100 and the second hook 108. Additionally, the flange 130 can extend (circumferentially) from the rear end 104 between the first side surface 110 and the second side surface 112. In the non-limiting example shown in FIG. 6, the flange 130 can be substantially planar, axially oriented, and / or substantially parallel to the axis (A) of the base portion 126 and / or the inner surface 124. In other non-limiting examples (see FIGS. 7 and 8), the flange 130 can be inclined and / or can extend obliquely from the rear end 104. As shown, the flange 130 can be formed integrally with the rear end 104 of the turbine shroud 100. In another non-limiting example (not shown), the flange 130 can be formed as a separate feature and / or component that can be installed and / or attached subsequent to the rear end 104 of the turbine shroud 100 before the turbine shroud 100 is installed within the gas turbine system 10 (see FIGS. 1 and 2). Additionally, as shown in the non-limiting example of FIG. 6, the base portion 126 of the turbine shroud 100 can extend axially beyond the flange 130 and / or can extend further axially than the flange 130. In other non-limiting examples, the flange 130 can extend axially beyond the base portion 126 (see FIG. 9) or can extend axially from the rear end 104 and be radially aligned with the base portion 126 (not shown). As discussed herein, the flange 130 can direct post-cooling fluid from the turbine shroud 100 away from the casing 36 and / or the coupling component 52 (see FIGS. 2 and 10) and / or can block post-cooling fluid from the turbine shroud 100 from contacting the casing 36 and / or the coupling component 52.In addition, as discussed herein, the flange 130 may also absorb heat transferred to the cooled fluid previously used to cool the turbine shroud 100.

[0034] The turbine shroud 100 may also include at least one cooling passage formed therein for cooling the turbine shroud 100 during operation of the turbine 28 of the gas turbine system 10. As shown in FIGS. 4 and 6, the turbine shroud 100 can include cooling passages 132 formed, positioned, and / or extending within the turbine shroud 100. More specifically, referring briefly back to FIG. 4, the cooling passages 132 (shown in phantom lines in FIG. 4) of the turbine shroud 100 can extend within and / or adjacent to the turbine shroud 100 between and / or adjacent to the front end 102, the rear end 104, the first side surface 110, and the second side surface 112, respectively. In addition, as shown in FIG. 6, the cooling passages 132 can extend (radially) within the turbine shroud 100 between and / or be at least partially defined by the base portion 126 and the impact portion 128. The cooling passages 132 can also be substantially positioned and / or formed within the base portion 126 adjacent to the inner surface 124. As discussed herein, the cooling passages 132 can receive cooling fluid from the cooling chamber 122 to cool the turbine shroud 100. The size of the cooling passages 132 (e.g., the radial opening height) can depend on various factors including, but not limited to, the size of the turbine shroud 100, the thickness of the base portion 126 and / or the impact portion 128, the cooling requirements for the turbine shroud 100, and / or the geometry or shape of the front end 102 and / or the rear end 104 of the turbine shroud 100.

[0035] To provide cooling fluid to the cooling passage 132, the turbine shroud 100 may also include a plurality of impingement openings 134 formed therethrough. That is, as shown in FIGS. 4 and 6, the turbine shroud 100 can include a plurality of impingement openings 134 formed through the outer surface 120 of the turbine shroud 100, more specifically, through the impingement portion 128. The plurality of impingement openings 134 formed through the outer surface 120 and / or the impingement portion 128 can fluidly couple the cooling passage 132 to the cooling chamber 122. As discussed herein, during operation of the gas turbine system 10 (see FIG. 1), the cooling fluid flowing through the cooling chamber 122 passes through or flows through the plurality of impingement openings 134 to reach the cooling passage 132 and can substantially cool the turbine shroud 100.

[0036] It is understood that the size and / or number of the impingement openings 134 formed through the outer surface 120 and / or the impingement portion 128 are merely illustrative, as shown in FIGS. 4 and 6. Thus, the turbine shroud 100 can include larger or smaller impingement openings 134 and / or can include a greater or lesser number of impingement openings 134 formed therein. Additionally, although the plurality of impingement openings 134 are shown as having substantially uniform size and / or shape, it is understood that each of the plurality of impingement openings 134 formed on the turbine shroud 100 can include a distinct size and / or shape. The size, shape, and / or number of the impingement openings 134 formed in the turbine shroud 100 can 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 134 formed in the turbine shroud 100 can depend at least in part on the characteristics of the turbine shroud 100 / cooling passage 132 (e.g., thickness of the base portion 126, thickness of the impingement portion 128, height of the cooling passage 132, volume of the cooling passage 132, etc.).

[0037] Also, as shown in FIGS. 4 and 6, the turbine shroud 100 may include a plurality of front exhaust ducts 136 (shown in phantom lines in FIG. 4). The plurality of front exhaust ducts 136 can be in fluid communication with the cooling passage 132 and then the cooling chamber 122. More specifically, each of the plurality of front exhaust ducts 136 may be in fluid communication with the cooling passage 132 of the turbine shroud 100 and may extend axially therefrom. In the non-limiting example shown in FIG. 6, the plurality of front exhaust ducts 136 can extend through the turbine shroud 100 from the cooling passage 132 to the front end 102 of the turbine shroud 100. In addition to being in fluid communication with the cooling passage 132, the plurality of front exhaust ducts 136 may be in fluid communication with an area within the turbine 28 (see FIG. 2) that is positioned upstream and axially aligned with the front end 102 of the turbine shroud 100. During operation, and as discussed herein, the plurality of front exhaust ducts 136 can discharge cooling fluid (e.g., cooled fluid) from the cooling passage 132 upstream and adjacent to the front end 102 of the turbine shroud 100.

[0038] It is understood that the turbine shroud 100 can include any number of front exhaust ducts 136 formed therein and in fluid communication with the cooling passage 132. Additionally, although shown as being substantially round / circular and linear, it is understood that the front exhaust ducts 136 can be non-round and / or non-linear openings, channels, and / or manifolds. When the front exhaust ducts 136 are formed non-round and / or non-linear, the direction of the cooling fluid flow can be varied to improve the cooling of the front end 102 of the turbine shroud 100. Further, the front exhaust ducts 136 may also have various sizes among each of the front exhaust ducts 136 depending on the cooling requirements of the operating turbine shroud 100.

[0039] Also, as shown in FIG. 6, the turbine shroud 100 may include a plurality of rear end exhaust ducts 138. The plurality of rear end exhaust ducts 138 can be in fluid communication with the cooling passage 132 and then can be in fluid communication with the cooling chamber 122. More specifically, the plurality of rear end exhaust ducts 138 may be in fluid communication with and extend from the cooling passage 132 of the turbine shroud 100. Additionally, as a result of the cooling passage 132 being in direct fluid communication with the cooling chamber 122, each of the plurality of rear end exhaust ducts 138 may also be in fluid communication with the cooling chamber 122. As shown in FIG. 6, the plurality of rear end exhaust ducts 138 can pass through the turbine shroud 100, extend from the cooling passage 132 toward the rear end 104 of the turbine shroud 100, and extend through the rear end 104. Additionally, the plurality of rear end exhaust ducts 138 may also extend radially and / or be positioned between the base portion 126 and the flange 130 of the turbine shroud 100. In a non-limiting example, the plurality of rear end exhaust ducts 138 may also extend through the turbine shroud 100 at an angle (α). That is, as shown in FIG. 6, the plurality of rear end exhaust ducts 138 may be inclined radially outward from the cooling passage 132 toward the flange 130 and / or may extend through the turbine shroud 100 at a radial angle (α). The plurality of rear end exhaust ducts 138 may also be in fluid communication with a region of the turbine 28 (see FIG. 2) that may be positioned axially adjacent and downstream of the rear end 104 of the turbine shroud 100. As discussed herein, the plurality of rear end exhaust ducts 138 can discharge cooling fluid (e.g., cooled fluid) from the cooling passage 132 downstream and adjacent to the rear end 104 of the turbine shroud 100.

[0040] Similar to the front exhaust duct 136, it is understood that the turbine shroud 100 may include any number of rear exhaust ducts 138 that are formed internally, in fluid communication with the cooling passage 132, and then in fluid communication with the cooling chamber 122. Additionally, although shown as being substantially round / circular and linear, it is understood that the rear exhaust ducts 138 can be non-round and / or non-linear openings, channels, and / or manifolds. When the rear exhaust ducts 138 are formed non-round and / or non-linear, the direction of the flow of the cooling fluid can be varied to improve the cooling of the rear end 104 of the turbine shroud 100. Further, the rear exhaust ducts 138 may also have various sizes between each rear exhaust duct 138, depending on the cooling requirements of the operating turbine shroud 100.

[0041] During operation of the gas turbine system 10 (see FIG. 1), the cooling fluid (CF) can flow through the turbine shroud 100 to cool the turbine shroud 100. More specifically, as the turbine shroud 100 is exposed to the combustion gas 26 flowing through the high-temperature gas flow path of the turbine 28 (see FIG. 2) during operation of the gas turbine system 10 and its temperature rises, the cooling fluid (CF) can be provided to and / or flow through the cooling passage 132 formed between the base portion 126 and the impingement portion 128 to cool the turbine shroud 100. With respect to FIG. 6, the various arrows can represent and / or indicate the flow path of the cooling fluid (CF) flowing through the turbine shroud 100. In a non-limiting example, the cooling fluid (CF) may first flow from the cooling chamber 122 to the cooling passage 132 through a plurality of impingement openings 134 formed through the outer surface 120 and / or the impingement portion 128 of the turbine shroud 100. The cooling fluid (CF) flowing in and / or through the cooling passage 132 can cool and / or receive heat from the outer surface 120 / impingement portion 128 and / or the inner surface 124 / base portion 126. Upon entering the cooling passage 132, the cooling fluid (CF) can be dispersed and / or flow axially toward one of the front end 102 or the rear end 104 of the turbine shroud 100. In addition, the cooling fluid (CF) can be dispersed and / or flow circumferentially toward one of the first side surface 110 or the second side surface 112 of the turbine shroud 100.

[0042] When the cooling fluid (CF) in the cooling passage 132 flows to the respective ends 102, 104 / side surfaces 110, 112 of the turbine shroud 100, the cooling fluid (CF) can flow through the respective exhaust ducts 136, 138. For example, a portion of the cooling fluid (CF) flowing axially through the cooling passage 132 toward the front end 102 can be distributed and / or exhausted from the turbine shroud 100 via a plurality of front-end exhaust ducts 136 formed or extending through the front end 102 of the turbine shroud 100 and in fluid communication with the cooling passage 132.

[0043] Furthermore, a portion of the cooling fluid (CF) that flows axially through the cooling passage 132 toward the rear end 104 can be distributed and / or exhausted from the turbine shroud 100 via a plurality of rear end exhaust ducts 138 that are in fluid communication with the cooling passage 132 and that form or extend through the rear end 104 of the turbine shroud 100. When exhausted from the rear end exhaust ducts 138, the cooling fluid (e.g., the cooled fluid) can flow toward the flange 130 of the turbine shroud 100, contact the flange 130, and / or be redirected by the flange 130. That is, as a result of the plurality of rear end exhaust ducts 138 extending through the rear end 104 at a radial angle (α) upwardly from the cooling passage 132 / toward the flange 130, the cooling fluid can likewise be exhausted directly from the rear end exhaust ducts 138 toward the flange 130. The flange 130 can then direct the cooled fluid radially back toward the base portion 126 and / or radially away from the second hook 108 of the turbine shroud 100. Additionally, the flange 130 can prevent the cooled fluid exhausted from the rear end exhaust ducts 138 from flowing radially around the flange 130 and away from the base portion 126. As discussed herein, the redirection of the cooled fluid by the flange 130 can prevent the cooled fluid from flowing over and / or contacting components of the turbine 28 (e.g., the casing 36, the coupling component 52 (see FIGS. 2 and 10)) that are radially adjacent to the flange 130 and positioned radially opposite or outside of the base portion 126 of the turbine shroud 100. Further, the flange 130 can also absorb and / or dissipate at least a portion of the heat transferred from the turbine shroud 100 to the cooled fluid while the cooling fluid flows through the cooling passage 132. The cooled fluid that can contact the flange 130 and / or be redirected by the flange 130 can continue to flow axially away from / downstream of the turbine shroud 100 toward downstream components of the turbine 28 (e.g., the stator vanes 40). As discussed herein, the downstream components can utilize the cooled fluid from the turbine shroud 100 for additional processing (e.g., for cooling purposes).

[0044] Figures 7-9 show additional non-limiting examples of the turbine shroud 100. More specifically, Figures 7-9 show side cross-sectional views of various non-limiting examples of the turbine shroud 100 that can be used within the turbine 28 (see Figure 1) of the gas turbine system 10. It is understood that components with like reference numerals and / or names may function in substantially the same manner. Redundant descriptions of these components are omitted for clarity.

[0045] As shown in Figure 7, the flange 130 of the turbine shroud 100 can be substantially inclined. That is, the flange 130 can extend at an angle (β) from the rear end 104 of the turbine shroud 100. In a non-limiting example, the flange 130 may extend at an angle (β) radially toward the second hook 108 of the turbine shroud 100. More specifically, the flange 130 can extend radially outwardly toward the second hook 108 and / or radially outwardly from or away from the base portion 126 of the turbine shroud 100. The angle (β) at which the flange 130 extends from the rear end 104 may be substantially the same as or different from the angle (α) at which the plurality of rear end exhaust ducts 138 extend through the turbine shroud 100.

[0046] Referring to Figure 8, similar to the non-limiting examples shown and discussed herein with respect to Figure 7, the flange 130 of the turbine shroud 100 can be substantially inclined. That is, the flange 130 can extend at an angle (β) from the rear end 104 of the turbine shroud 100. Different from Figure 7, the flange 130 shown in Figure 8 may extend at an angle (β) radially toward the base portion 126 of the turbine shroud 100. More specifically, the flange 130 can extend radially inwardly toward the base portion 126 and / or radially inwardly from or away from the second hook 108 of the turbine shroud 100. Additionally, as shown in Figure 8, the flange 130 can extend radially inwardly toward the plurality of rear end exhaust ducts 138.

[0047] In the non-limiting example shown in FIG. 9, the flange 130 extending axially from the rear end 104 may be substantially planar, axially oriented, and / or substantially parallel to the axis (A) and / or the inner surface 124 of the base portion 126, as discussed herein. However, unlike the non-limiting examples shown and discussed herein with respect to FIG. 6, the flange 130 can extend axially beyond the base portion 126. That is, as shown in FIG. 9, the flange 130 can extend axially from the rear end 104 beyond the base portion 126 such that the most downstream portion of the rear end 104 of the turbine shroud 100 is the flange 130.

[0048] In addition, as shown in FIG. 9, the turbine shroud 100 can be formed from two separate and / or distinct components or parts. More specifically, the impact portion 128 of the turbine shroud 100 may be different from the remainder of the turbine shroud 100, including the hooks 106, 108, the base portion 126, the flange 130, etc. In a non-limiting example, the impact portion 128 may be formed from a separate plate 140 that is coupled or attached to the remainder of the turbine shroud 100 and positioned adjacent to the cooling chamber 122. The plate 140 forming the impact portion 128 can include an outer portion 120 and an impact opening formed through the outer portion 120. As discussed herein, the plate 140 can define / form the cooling passage 132 and be coupled or attached to the remainder of the turbine shroud 100 using any suitable joining process that ultimately forms the turbine shroud 100.

[0049] FIG. 10 shows an enlarged view of a portion of FIG. 2. More specifically, FIG. 10 shows an enlarged view of a portion of the turbine 28 (see FIG. 1) of the gas turbine system 10, including the casing 36, the coupling component 52, the stator vane 40, and a portion of the turbine shroud 100. It is understood that components with like reference numerals and / or names can function in a substantially similar manner. Redundant descriptions of these components are omitted for clarity.

[0050] In addition, as shown in FIG. 10, the turbine 28 of the gas turbine system 10 may also include a seal 142. The seal 142 can extend between the stator vane 40 and the turbine shroud 100. More specifically, the seal 142 can extend between the rear end 104 of the turbine shroud 100 and the front end of the stator vane 40. As shown in a non-limiting example, the seal 142 can also be in contact with and / or adhered to the base portion 126 of the turbine shroud 100 and the outer platform 42 of the stator vane 40 adjacent to the rear end 104. The seal 142 is in contact with and / or adhered to the base portion 126 of the turbine shroud 100 and the outer platform 42 of the stator vane 40 and can form or define a part of the flow path (FP) between the turbine shroud 100 and the stator vane 40. In addition, the seal 142 can also at least partially define and / or form a cooling fluid path 144 that can be formed between the turbine shroud 100 and the stator vane 40 together with the casing 36. As discussed herein, the seal 142 prevents the combustion gas 26 from undesirably exiting the flow path (FP) defined by the turbine shroud 100 and the outer platform 42 of the stator vane 40, and also prevents the cooling fluid (e.g., cooled fluid) exhausted from the turbine shroud 100 from entering the flow path (FP) and mixing undesirably with the combustion gas 26.

[0051] The seal 142 can also be positioned radially on the turbine shroud between the flange 130 of the turbine shroud 100 and the base portion 126. Thus, as shown in FIG. 10, the plurality of rear end exhaust ducts 138 can be positioned radially between the flange 130 and the seal 142 in contact with the base portion 126. Further, the flange 130 can also be positioned radially between the turbine casing 36 / coupling component 52 of the turbine 28 (see FIGS. 2 and 10) and the cooling passage 132 formed or positioned within the base portion 126 and / or the plurality of rear end exhaust ducts 138. As discussed herein, during operation, the cooling fluid exhausted from the plurality of rear end exhaust ducts 138 that extend obliquely through the rear end 104 of the turbine shroud 100 can contact the flange 130 and can be prevented from directly contacting the coupling component 52 of the casing 36. In addition, the flange 130 can deflect the cooling fluid exhausted from the coupling component 52 and / or the casing 36 radially inward and / or away radially, and / or toward the seal 142. When the cooling fluid is deflected by the flange 130, the cooling fluid can flow downstream toward the stator vane 40 and can then be utilized by the stator vane 40. For example, the cooling fluid exhausted from the turbine shroud 100 and deflected by the flange 130 can be used to cool the holding component 41 and / or the outer platform 42 of the stator vane 40 during operation of the turbine 28.

[0052] The portion of the turbine 28 shown in FIG. 10 may represent, for example, the first stage of the blades 38 and the stator vanes 40. Thus, the seal 142 can be positioned only between the rear end 104 of the turbine shroud 100 and the outer platform 42 of the stator vane 40. In a downstream stage (e.g., an intermediate or final stage), the plurality of blades 38 within that stage may include stator vanes 40 positioned both upstream and downstream of the blades 38 and / or the turbine shroud 100. In these stages of the turbine 28, the seal 142 may be presented and / or positioned between each set of stator vanes 40. More specifically, the seal 142 can be positioned and / or in contact with the base portion 126 of the turbine shroud 100 adjacent to the rear end 104 and the front end of the outer platform 42 of the stator vane 40 positioned downstream of the turbine shroud 100, as discussed herein with respect to FIG. 10. Additionally, a separate seal 142 can be positioned and / or in contact with the base portion 126 of the turbine shroud 100 adjacent to the front end 102 and the rear end of the outer platform 42 of the stator vane 40 positioned upstream of the turbine shroud 100. As discussed herein, the seal 142 can define and / or separate the flow path (FP) with respect to the combustion gas 26 and the cooling fluid path 144 of the turbine 28.

[0053] FIGS. 11-13 show additional non-limiting examples of the turbine shroud 100. More specifically, FIGS. 11-13 show various views of non-limiting examples of the turbine shroud 100 that can be used within the turbine 28 (see FIG. 1) of the gas turbine system 10. It is understood that components with like reference numerals and / or names may function in a substantially similar manner. Redundant descriptions of these components are omitted for clarity.

[0054] Figures 11 and 12 show various views of additional non-limiting examples of the turbine shroud 100 of the turbine 28 for the gas turbine system 10 of FIG. 1. Specifically, FIG. 11 shows a top view of the turbine shroud 100, and FIG. 12 shows a cross-sectional side view of the turbine shroud 100. The turbine shroud 100 shown in FIGS. 11 and 12 may include a non-limiting example of a serpentine pattern 146 formed adjacent to the rear end 104. That is, as shown in FIGS. 11 and 12, the serpentine pattern 146 extends between the first side surface 110 and the second side surface 112 adjacent to the rear end 104 of the turbine shroud 100, includes a plurality of turns that meander and / or spread therebetween, and can include a plurality of turns that meander and / or spread therebetween. Each portion of the opening of the serpentine pattern 146 can also extend radially between the base portion 126 and the collision portion 128 of the turbine shroud 100. In a non-limiting example, the serpentine pattern 146 formed adjacent to the rear end 104 may be in fluid communication with each of the cooling passage 132 and the plurality of rear end exhaust ducts 138 that extend through the rear end 104 of the turbine shroud 100. The serpentine pattern 146 can assist in heat transfer and / or cooling of the turbine shroud 100 during operation of the gas turbine system 10, as discussed herein. As shown in FIG. 12, the cooling fluid can flow back and forth between the first side surface 110 and the second side surface 112 through the serpentine pattern 146 from the cooling passage 132 and through the serpentine pattern 146 before being exhausted from one of the plurality of rear end exhaust ducts 138 that extend at a radial angle (α). The number of turns included in the serpentine pattern 146 is understood to be exemplary. Thus, the serpentine pattern 146 formed adjacent to the rear end 104 may include more or fewer turns than shown in FIGS. 11 and 12. Additionally, it is understood that the serpentine pattern 146 can be formed at the front end 102 in addition to or instead of being formed at the rear end 104 as shown in FIGS. 11 and 12.

[0055] In additional non-limiting examples, the serpentine pattern 146 may be oriented separately within the turbine shroud 100. For example, the turbine shroud 100 may include a separate serpentine pattern 146 (not shown) that extends between the base portion 126 and the impingement portion 128, snakes, and / or spreads therebetween, and may include a plurality of turns. In a non-limiting example (not shown), the serpentine pattern 146 may have a final turn that is in fluid communication with each of a plurality of aft exhaust ducts 138 that extend through the aft end 104 of the turbine shroud 100.

[0056] FIG. 13 shows another non-limiting example of the turbine shroud 100. In a non-limiting example, the turbine shroud 100 may include a plurality of channels 148, 150. More specifically, the turbine shroud 100 may include a plurality of channels 148, 150, each channel 148, 150 including a corresponding (single) opening 152 formed in and / or through the impingement portion 128, and may be in direct fluid communication and / or fluidly coupled. Additionally, as shown in FIG. 13, channel 148 may extend toward the front end 102, and channel 150 may extend toward the aft end 104. Thus, each channel 148 may be in fluid communication with and / or integrally formed with a front exhaust duct 136 that extends through the front end 102 of the turbine shroud 100. Further, each channel 150 may be in fluid communication with and / or integrally formed with an aft exhaust duct 138 that extends through the aft end 102 of the turbine shroud 100 at a radial angle (α) (see FIG. 6).

[0057] Figures 14 to 17 show various views of the stator vane 200. More specifically, FIGS. 14 to 16 show various views of non-limiting examples of the stator vane 200 that can be used within the turbine 28 (see FIGS. 1 and 2) of the gas turbine system 10. The stator vane 200 shown in FIG. 14 may include substantially the same components and / or features as those discussed herein with respect to the stator vane 40 shown in FIG. 2. For example, the stator vane 200 may each include an outer platform 202, an inner platform 204 positioned on the opposite side of the outer platform 202, and an airfoil 206 positioned between the outer platform 202 and the inner platform 204. It is understood that components with the same reference numerals and / or names may function in substantially the same manner. Redundant descriptions of these components are omitted for clarity.

[0058] In addition, as shown in FIG. 14, the stator vane 200 may also include a retaining component 208. The retaining component 208 is shown in FIG. 14 as an optional dashed line. That is, in some non-limiting examples, the stator vane 200 may include a retaining component 208 for circumferentially coupling and / or positioning the stator vane 200 around the casing 36 (see FIG. 2) of the turbine 28. As shown in the non-limiting example, the retaining component 208 may be coupled and / or connected to the outer platform 202 of the stator vane 200. In other non-limiting examples, the stator vane 200 may not include the retaining component 208 (see FIG. 16). Rather, the outer platform 202 may contact and / or be coupled to a separate part or component of the turbine 28 (e.g., the turbine shroud 100) and be positioned and / or fixed within the turbine 28 during operation.

[0059] Referring to FIG. 15, a cross-sectional side view of the stator vane 200 is shown. Specifically, FIG. 15 shows a partial cross-sectional side view of the stator vane 200 along line 15-15 of FIG. 14. As shown in FIG. 15 and as discussed herein, the stator vane 200 can include features similar to those discussed herein with respect to the turbine shroud 100 shown in FIGS. 3-9, which can assist in guiding the cooled fluid exhausted from the stator vane 200. The stator vane 200 can also include various ends, sides, and / or surfaces. For example, as shown in FIG. 15, the stator vane 200 can include a front end 210 and a rear end 212 positioned on the opposite side of the front end 210. The front end 210 can be positioned upstream of the rear end 212 such that the combustion gas 26 flowing through the flow path (FP) defined within the turbine 28 can flow through the adjacent front end 210 before flowing through the adjacent rear end 212. As shown in FIG. 15, the stator vane 200 can also include an outer surface 218. More specifically, in a non-limiting example where the stator vane 200 includes a holding component 208, the holding component 208 can include the outer surface 218. The outer surface 218 can face a cooling chamber 220 formed between the stator vane 200 and the turbine casing 36 (see FIG. 2). More specifically, the outer surface 218 can be positioned, formed, face, and / or directly expose a cooling chamber 220 formed between the holding component 208 of the stator vane 200 and the turbine casing 36 of the turbine 28. As discussed herein, the cooling chamber 220 formed between the stator vane 200 and the turbine casing 36 can receive and / or provide a cooling fluid during operation of the turbine 28. In addition to facing the cooling chamber 220, the outer surface 218 of the stator vane 200 can also be formed and / or positioned between the front end 210 and the rear end 212 of the stator vane 200.

[0060] The stator vane 200 may also include an inner surface 222 formed on the opposite side of the outer surface 218. That is, as shown in the non-limiting example of FIG. 15, the inner surface 222 of the stator vane 200 may be formed on the radially opposite side of the outer surface 218. In a non-limiting example, the inner surface 222 may include and / or be at least partially defined by the outer platform 202 of the stator vane 200, which faces the high-temperature gas flow path (FP) of the combustion gas 26 flowing through the turbine 28 (see FIG. 2). As discussed herein, the inner surface 222 at least partially defined by the outer platform 202 of the stator vane 200 may at least partially form and / or define at least one cooling passage within the stator vane 200 / holding component 208 for cooling the holding component 208 and / or the outer platform 202 during operation of the turbine 28. In a non-limiting example, it may be determined that the entire outer platform 202 may form the "base portion 236" of the stator vane 200.

[0061] The stator vane 200 may include a collision portion 224. The collision portion 224 can be formed as an integral part of the stator vane 200. The collision portion 224 may include the outer surface 218, and / or the outer surface 218 may be formed on the collision portion 224 of the stator vane 200. The collision portion 224 of the stator vane 200 can be formed, positioned, and / or extend between the front end 210 and the rear end 212 of the stator vane 200. As shown in FIG. 15, the collision portion 224 can be positioned radially adjacent to the inner surface 222 and / or can be positioned radially adjacent to the outer platform 202. The collision portion 224 of the stator vane 200 can at least partially form and / or define at least one cooling passage within the stator vane 200 as discussed herein.

[0062] As shown in FIG. 15, the stator vane 200 may also include a flange 226. The flange 226 can extend from the rear end 212 of the stator vane 200. More specifically, the flange 226 can extend (substantially) axially from the rear end 212 of the retaining component 208 and can be positioned radially adjacent to the outer platform 202. In the non-limiting example shown in FIG. 15, the flange 226 may be substantially planar, axially oriented, and / or substantially parallel to the axis (A). As shown, the flange 226 can be formed integrally with the rear end 212 of the retaining component 208 for the stator vane 200. In another non-limiting example (not shown), the flange 226 may be formed as a separate feature and / or component that can be installed and / or attached following the rear end 212 of the retaining component 208 before the stator vane 200 is installed within the gas turbine system 10 (see FIGS. 1 and 2). Additionally, as shown in the non-limiting example of FIG. 15, the outer platform 202 of the stator vane 200 can extend axially beyond the flange 226 and / or can extend further axially than the flange 226. In other non-limiting examples, the flange 226 may extend axially beyond the outer platform 202 or may extend axially from the rear end 212 and be radially aligned with the outer platform 202 (not shown). As discussed herein, the flange 226 can direct the cooled fluid from the stator vane 200 away from the casing 36 and / or can block the cooled fluid from the stator vane 200 from contacting the casing 36. Additionally, as discussed herein, the flange 226 can also absorb heat transferred to the previously used cooled fluid for cooling the stator vane 200.

[0063] The stator vane 200 may also include at least one cooling passage formed therein for cooling the stator vane 200 during operation of the turbine 28 of the gas turbine system 10. As shown in FIG. 15, the stator vane 200 can include a cooling passage 228 formed, positioned, and / or extending within the stator vane 200. More specifically, the cooling passage 228 of the stator vane 200 can extend within the retaining component 208 of the stator vane 200 between and / or adjacent to the front end 210 and the rear end 212. Additionally, as shown in FIG. 15, the cooling passage 228 may extend (radially) within the stator vane 200 between and / or be at least partially defined by the outer platform 202 and the impingement portion 224. The cooling passage 228 can also be substantially positioned and / or formed adjacent to the inner surface 222. As discussed herein, the cooling passage 228 can receive cooling fluid from the cooling chamber 220 to cool the stator vane 200. The size of the cooling passage 228 (e.g., the radial opening height) can depend on various factors including, but not limited to, the size of the stator vane 200, the thickness of the outer platform 202 and / or the impingement portion 224, the cooling requirements for the stator vane 200, etc.

[0064] To provide cooling fluid to the cooling passage 228, the stator vane 200 may also include a plurality of impingement openings 230 formed therethrough. That is, as shown in FIG. 15, the stator vane 200 can include a plurality of impingement openings 230 formed through the outer surface 218 of the stator vane 200, more specifically, through the impingement portion 224. The plurality of impingement openings 230 formed through the outer surface 218 and / or the impingement portion 224 can fluidly couple the cooling passage 228 to the cooling chamber 220. As discussed herein, during operation of the gas turbine system 10 (see FIG. 1), the cooling fluid flowing through the cooling chamber 220 can pass through or flow through the plurality of impingement openings 230 to reach the cooling passage 228 and substantially cool the stator vane 200.

[0065] The size and / or number of collision openings 230 formed through the outer surface 218 and / or the collision portion 224 are, as shown in FIG. 15, to be understood as merely illustrative. Thus, the stator vane 200 can include larger or smaller collision openings 230 and / or can include a greater or fewer number of collision openings 230 formed therein. Additionally, although a plurality of collision openings 230 are shown as having substantially uniform size and / or shape, it is understood that each of the plurality of collision openings 230 formed on the stator vane 200 can include distinct sizes and / or shapes. The size, shape, and / or number of the collision openings 230 formed in the stator vane 200 can depend at least in part on the operating characteristics of the gas turbine system 10 in operation (e.g., exposure temperature, exposure pressure, position within the turbine casing 36, etc.). Additionally or alternatively, the size, shape, and / or number of the collision openings 230 formed in the stator vane 200 can depend at least in part on the characteristics of the stator vane 200 / cooling passage 228.

[0066] The stator vane 200 can include a plurality of front-end exhaust ducts 232 (one shown). The plurality of front-end exhaust ducts 232 can be in fluid communication with the cooling passage 228. More specifically, each of the plurality of front-end exhaust ducts 232 can be in fluid communication with and extend axially from the cooling passage 228 of the stator vane 200. In the non-limiting example shown in FIG. 15, the plurality of front-end exhaust ducts 232 can extend from the cooling passage 228 to the front end 210 through the holding component 208 of the stator vane 200. In addition to being in fluid communication with the cooling passage 228, the plurality of front-end exhaust ducts 232 can be in fluid communication with a region within the turbine 28 (see FIG. 2) that is positioned upstream and axially aligned with the front end 210 of the stator vane 200. During operation, and as discussed herein, the plurality of front-end exhaust ducts 232 can discharge cooling fluid (e.g., cooled fluid) from the cooling passage 228 upstream and adjacent to the front end 210 of the stator vane 200.

[0067] It is understood that the stator vane 200 may include any number of front exhaust ducts 232 formed therein and in fluid communication with the cooling passage 228. Additionally, although shown as being substantially round / circular and linear, it is understood that the front exhaust ducts 232 may be non-round and / or non-linear openings, channels, and / or manifolds. When the front exhaust ducts 232 are formed non-round and / or non-linear, the direction of the flow of the cooling fluid can be varied to improve the cooling of the front end 210 of the stator vane 200. Further, the front exhaust ducts 232 may also have various sizes between each front exhaust duct 232, depending on the cooling requirements of the stator vane 200 during operation.

[0068] Also, as shown in FIG. 15, the stator vane 200 may include a plurality of rear-end exhaust ducts 234. The plurality of rear-end exhaust ducts 234 can be in fluid communication with the cooling passage 228 and then can be in fluid communication with the cooling chamber 220. More specifically, the plurality of rear-end exhaust ducts 234 may be in fluid communication with and extend from the cooling passage 228 of the stator vane 200. Additionally, as a result of the cooling passage 228 being in direct fluid communication with the cooling chamber 220, each of the plurality of rear-end exhaust ducts 234 may also be in fluid communication with the cooling chamber 220. As shown in FIG. 15, the plurality of rear-end exhaust ducts 234 can extend through the retaining component 208 of the stator vane 200, from the cooling passage 228 to the rear end 212 of the stator vane 200 and through the rear end 212. Additionally, the plurality of rear-end exhaust ducts 234 may also extend radially and / or be positioned between the outer platform 202 (e.g., base portion 236) of the stator vane 200 and the flange 226. In a non-limiting example, the plurality of rear-end exhaust ducts 234 may also extend through the stator vane 200 at an angle (α). That is, as shown in FIG. 15, the plurality of rear-end exhaust ducts 234 may be inclined radially outward from the cooling passage 228 toward the flange 226 and / or may extend through the stator vane 200 at a radial angle (α). The plurality of rear-end exhaust ducts 234 may also be in fluid communication with a region of the turbine 28 (see FIG. 2) positioned axially adjacent downstream of the rear end 212 of the stator vane 200. As discussed herein, the plurality of rear-end exhaust ducts 234 can discharge cooling fluid (e.g., cooled fluid) from the cooling passage 228 downstream adjacent to the rear end 212 of the stator vane 200.

[0069] Similar to the front exhaust duct 232, it is understood that the stator vane 200 can include any number of rear exhaust ducts 234 that are formed internally, in fluid communication with the cooling passage 228, and then in fluid communication with the cooling chamber 220. Additionally, although shown as being substantially round / circular and linear, it is understood that the rear exhaust ducts 234 can be non-round and / or non-linear openings, channels, and / or manifolds. When the rear exhaust ducts 234 are formed non-round and / or non-linear, the direction of the flow of the cooling fluid can be varied to improve the cooling of the rear end 212 of the stator vane 200. Further, the rear exhaust ducts 234 can also have various sizes between each rear exhaust duct 234, depending on the cooling requirements of the stator vane 200 during operation.

[0070] During operation of the gas turbine system 10 (see FIG. 1), the cooling fluid (CF) can flow through the stator vane 200 to cool the stator vane 200. More specifically, as the stator vane 200 is exposed to the combustion gas 26 flowing through the high-temperature gas flow path of the turbine 28 (see FIG. 2) during operation of the gas turbine system 10 and its temperature rises, the cooling fluid (CF) can be provided to and / or flow through the cooling passage 228 formed between the outer platform 222 and the impingement portion 224 to cool the holding component 208 and / or the outer platform 222 of the stator vane 200. With respect to FIG. 15, various arrows can represent and / or indicate the flow path of the cooling fluid (CF) flowing through the stator vane 200. In a non-limiting example, the cooling fluid (CF) may first flow from the cooling chamber 220 to the cooling passage 228 through a plurality of impingement openings 230 formed through the outer surface 218 and / or the impingement portion 224 of the stator vane 200. The cooling fluid (CF) flowing through the cooling passage 228 can cool and / or receive heat from the outer surface 218 / impingement portion 224 and / or the inner surface 222 / outer platform 222. Upon entering the cooling passage 228, the cooling fluid (CF) can be dispersed and / or flow axially towards one of the front end 210 or the rear end 212 of the stator vane 200. Additionally, the cooling fluid (CF) can be dispersed and / or flow circumferentially towards one of the first side surface 110 or the second side surface 112 of the stator vane 200.

[0071] When the cooling fluid (CF) in the cooling passage 228 flows to the respective ends 102, 104 / side surfaces 110, 112 of the stator vane 200, the cooling fluid (CF) can flow through the respective exhaust ducts 232, 234. For example, a portion of the cooling fluid (CF) flowing axially through the cooling passage 228 towards the front end 210 can be distributed and / or exhausted from the stator vane 200 through a plurality of front-end exhaust ducts 232 formed or extending through the front end 210 of the stator vane 200 and in fluid communication with the cooling passage 228.

[0072] Furthermore, a portion of the cooling fluid (CF) flowing axially through the cooling passage 228 toward the rear end 212 can be distributed and / or exhausted from the stator vane 200 via a plurality of rear end exhaust ducts 234 that are in fluid communication with the cooling passage 228 and that form or extend through the rear end 212 of the stator vane 200. When exhausted from the rear end exhaust ducts 234, the cooling fluid (e.g., the cooled fluid) can flow toward the flange 226 of the stator vane 200, contact the flange 226, and / or be redirected by the flange 226. That is, as a result of the plurality of rear end exhaust ducts 234 extending through the rear end 212 at a radial angle (α) upwardly from the cooling passage 228 / toward the flange 226, the cooling fluid can likewise be exhausted directly from the rear end exhaust ducts 234 toward the flange 226. The flange 226 can then direct the cooled fluid radially back toward the outer platform 202 and / or radially away from a separate portion of the retaining component 208 of the stator vane 200 / casing 36 (see FIG. 2). Additionally, the flange 226 can prevent the cooled fluid exhausted from the rear end exhaust ducts 234 from flowing radially around the flange 226 and away from the outer platform 202. As discussed herein, the redirection of the cooled fluid by the flange 226 can prevent the cooled fluid from flowing over and / or contacting components (e.g., the casing 36) (see FIG. 2) of the turbine 28 that are positioned radially opposite or outwardly from the outer platform 202 of the stator vane 200 and that are radially adjacent to the flange 226. Further, the flange 226 can also absorb and / or dissipate at least a portion of the heat transferred from the stator vane 200 to the cooled fluid while the cooling fluid flows through the cooling passage 228. The cooled fluid that can contact the flange 226 and / or be redirected by the flange 226 can continue to flow axially away from / downstream of the stator vane 200 toward downstream components (e.g., the turbine shroud 100) of the turbine 28. As discussed herein, the downstream components can utilize the cooled fluid from the stator vane 200 for additional processing (e.g., for cooling purposes).

[0073] FIG. 16 shows another non-limiting example of the stator vane 200. In the non-limiting example, the stator vane 200 may or may not include a retaining component 208 (shown in phantom lines as an option). In the non-limiting example, features used to cool the stator vane 200 may be formed and / or positioned directly within the outer platform 202 of the stator vane 200. That is, as shown in FIG. 16, the outer surface 218, the inner surface 222, the impact portion 224, the cooling passage 228, and the opening 230 can all be formed on the outer platform 202 of the stator vane 200 and / or integrally with the outer platform 202. Further, as shown in FIG. 16, the flange 226 of the stator vane 200 can be formed integrally with the outer platform 202. More specifically, the flange 226 can be formed integrally within the outer platform 202, radially on or adjacent to the base portion 236 of the outer platform 202 that can be exposed to the hot gas during the operation of the turbine 28 (see FIG. 2) as discussed herein. Additionally, as shown in FIG. 16, the flange 226 can extend substantially axially from the cooling passage 228 formed in the outer platform 202.

[0074] Furthermore, as shown in FIG. 16, the exhaust ducts 232, 234 can be formed within and extend through the outer platform 202. More specifically, the plurality of front-end exhaust ducts 232 can extend through the front end 210 of the outer platform 202 and exhaust the cooling fluid from the cooling chamber 228 formed within the outer platform 202. Additionally, each of the plurality of rear-end exhaust ducts 234 can extend through the rear end 212 of the outer platform 202 for the stator vane 200. In a non-limiting example, the plurality of rear-end exhaust ducts 234 may extend between and / or through the rear end 212 of the outer platform 202 in a radially outer direction between the base portion 236 and the flange 226 of the outer platform 202, and may also be formed integrally with the outer platform 202. As discussed herein, the plurality of rear-end exhaust ducts 234 can extend through the rear end 212 of the outer platform 202 at a radial angle (α) upwardly toward the flange 226, whereby the cooling fluid can be exhausted directly from the rear-end exhaust ducts 234 toward the flange 226.

[0075] FIG. 17 shows an additional non-limiting example of the stator vane 200. In a non-limiting example, the cooling passage 228 formed in a portion of the outer platform 202 of the stator vane 200 may be fully exposed and / or open to the cooling chamber 220 of the stator vane 200. In one example, the cooling chamber 220 may be formed within the holding component 208 (shown in phantom lines as an option). In another non-limiting example, the cooling chamber 220 can represent the space between the outer platform 202 of the stator vane 200 and the casing 36 (see FIG. 2) of the turbine 28. Thus, the cooling fluid (CF) used to cool the outer platform 202 of the stator vane 200 can flow directly from the cooling chamber 220 to the cooling passage 228 and subsequently be exhausted from the ducts 232, 234, as discussed herein.

[0076] The technical effect is to provide a high-temperature gas path component (e.g., a turbine shroud, a stator vane) including a plurality of inclined exhaust ducts and a rear-end flange. The high-temperature gas path component including the inclined exhaust ducts and the rear-end flange prevents the fluid after cooling from being undesirably exhausted directly toward and / or coming into undesired contact with the turbine casing or the coupling component of the turbine that fixes the high-temperature gas path component therein.

[0077] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprise" and / or "comprising", as used herein, specify the presence of the stated features, integers, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. "Optional" or "optionally" means that the subsequently described event or circumstance may or may not occur, and this description includes instances where the event occurs and instances where it does not.

[0078] As used throughout this specification and the claims, the language representing approximation can be applied to modify any quantitative expression that can vary within a reasonable extent without causing a change in the relevant basic function. Thus, values modified by terms such as "about," "approximately," and "substantially" are not limited to the precisely stated value. In at least some instances, the language representing approximation can correspond to the accuracy of the equipment used to measure the value. Here, as well as throughout this specification and the claims, limitations of ranges are combinable and / or replaceable, and such ranges are identified and include all sub-ranges subsumed therein, unless the context and language specifically indicate otherwise. "About" applied to a particular value of a range can be applied to both values and can indicate + / - 10% of the stated value, unless specifically dependent on the accuracy of the equipment used to measure the value.

[0079] All corresponding structures, materials, acts, and equivalents of the means-plus-function or step-plus-function elements in the following claims are intended to include any structure, material, or act for performing the function in combination with other claimed elements as specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the disclosure to the forms disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the present disclosure. The embodiments were chosen and described in order to best explain the principles of the disclosure and its practical application and to enable others of ordinary skill in the art to understand the disclosure in various embodiments with various modifications as are suited to the particular use contemplated.

Description of Reference Numerals

[0080] 10 Gas turbine system 12 Compressor 18 Air 20 Compressed air 22 Combustor 24 Fuel 26 Combustion gas 28 Turbine 30 Rotor 32 External load 34 Exhaust frame 36 Casing 38 Turbine blade 40 Stator vane 41 Holding component 42 Outer platform 44 Inner platform 45 Airfoil 46 Airfoil 48 Tip portion 50 Platform 52 Coupling component 54 Opening 100 Turbine shroud 102 Front end / End portion 104 Rear end / End portion 106 First hook 108 Second hook 110 First side 112 Second side 120 Outer surface / Outer portion 122 Cooling chamber 124 Inner surface 126 Base portion 128 Impact portion 130 Flange 132 Cooling passage 134 Impact opening 136 Front end exhaust duct 138 Rear end exhaust duct 140 Plate 142 Seal 144 Cooling fluid path 146 Serpentine pattern 148 Channel 150 Channel 152 Opening 200 Stator vane 202 Outer platform 204 Inner platform 206 Airfoil 208 Holding component 210 Front end 212 Rear end 218 Outer surface 220 Cooling chamber 222 Inner surface 224 Collision part 226 Flange 228 Cooling passage / cooling chamber 230 Collision opening 232 Front-end exhaust duct 234 Rear-end exhaust duct 236 Base part Axis A Direction C Flow direction D Direction R CF Cooling fluid FP Flow path Angle α Angle β

Claims

1. A turbine shroud (100) coupled to a turbine (28) casing (36) of a turbine system (10), the turbine shroud (100) comprising: a front end (102) including a first hook (106) coupled to the turbine (28) casing (36); a rear end (104) positioned opposite the front end (102), the rear end (104) including a second hook (108) coupled to the turbine (28) casing (36); a base portion (126) extending between the front end (102) and the rear end (104) and positioned radially opposite the first hook (106) and the second hook (108) coupled to the turbine (28) casing (36), the base portion (126) including an inner surface (124) facing a high temperature gas flow path for the turbine system (10); a flange (130) extending from the rear end (104) and positioned radially between the base portion (126) and the second hook (108); a cooling passage (132) positioned within the base portion (126) adjacent to the inner surface (124); at least one rear end exhaust duct (138) in fluid communication with the cooling passage (132), the at least one rear end exhaust duct (138) extending radially between the base portion (126) and the flange (130) and through the rear end (104); and wherein the at least one rear end exhaust duct (138) is inclined radially outward from the cooling passage (132, 228) toward the flange (130, 226), a turbine shroud (100).

2. a first side surface (110) formed to extend proximate between the front end (102) and the rear end (104); a second side surface (112) positioned opposite the first side surface (110), the second side surface (112) being formed to extend proximate between the front end (102) and the rear end (104); The turbine shroud (100) according to claim 1, further comprising.

3. The turbine shroud (100) according to claim 2, wherein the flange (130) extends from the rear end (104) between the first side surface (110) and the second side surface (112).

4. The flange (130) extends obliquely from the rear end (104), radially outwardly towards the second hook (108), or radially inwardly towards the base portion (126) The turbine shroud (100) according to claim 1, which extends. **Claim 5** The turbine shroud (100) according to claim 1, wherein the flange (130) extends axially beyond the base portion (126). **Claim 6** The turbine shroud (100) according to claim 1, wherein the flange (130) is positioned radially between the cooling passage (132) and the turbine (28) casing (36). **Claim 7** A turbine system (10), wherein the turbine system (10) comprises a turbine (28) casing (36), and a first stage positioned within the turbine (28) casing (36), The first stage comprising a plurality of turbine blades (38) circumferentially positioned around a rotor (30) within the turbine (28) casing (36), a plurality of stator vanes (40, 200) positioned within the turbine (28) casing (36) downstream of the plurality of turbine blades (38), and a plurality of turbine shrouds (100) radially adjacent to the plurality of turbine blades (38) and positioned upstream of the plurality of stator vanes (40, 200), The turbine system (10), wherein each of the plurality of turbine shrouds (100) is the turbine shroud (100) according to any one of claims 1 to 6. **Claim 8** A seal (142) extending between each of the plurality of stator vanes (40, 200) and each of the plurality of turbine shrouds (100), adjacent to the rear end (104), the base portion (126) of each of the plurality of turbine shrouds (100), and the outer platform (42) of each of the plurality of stator vanes (40, 200) The seal (142) in contact with The turbine system (10) according to claim 7, further comprising. **Claim 9** The turbine system (10) according to claim 8, wherein each of the at least one rear end exhaust duct (138) of the plurality of turbine shrouds (100) is positioned radially between the flange (130) and the seal (142) in contact with the base portion (126).

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