Hot gas path components including the rear exhaust pipe and rear flange

Abstract

A turbine shroud (100) for a turbine system (10) may include a front end (102), a rear end (104), and a base portion (126), the front end including a first hook (106) coupled to a turbine (28) casing (36), the rear end including a second hook (108) coupled to the turbine (28) casing (36), and the base portion extending between the front end (102) and the rear end (104). The base portion (126) may include an inner surface (124) facing a hot gas flow path for the turbine system (10). Additionally, the turbine shroud (100) may include a flange (130) extending from the aft 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 the inner surface (124), and at least one aft end exhaust pipe (138) in fluid communication with the cooling passage (132). The one or more aft end exhaust pipes (138) may extend radially through the aft end (104) between the base portion (126) and the flange (126).

Description

Background Art

[0001] The present disclosure relates generally to hot gas path components for turbine systems, and more particularly, to turbine shrouds and stator blades including a plurality of aft exhaust ducts and an aft flange.

[0002] Conventional turbines such as gas turbine systems are used to generate power for generators. Generally speaking, 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 can be compressed. Once compressed, the inlet air is mixed with fuel to form combustion products, which can be ignited by a combustor of the gas turbine system to form an operating fluid (e.g., hot gas) of 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 a turbine shroud and / or a 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 boundaries of the fluid flow path for the operating fluid. During operation, the turbine shroud may be exposed to 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 to define the fluid flow path for the operating fluid. 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] In order to minimize thermal expansion, the turbine shroud is typically cooled. One conventional process for cooling the turbine shroud includes impingement cooling. Impingement cooling utilizes holes or orifices formed through the turbine shroud to provide cooling air to various portions of the turbine shroud during operation. However, these conventional processes present a new problem that reduces the operating efficiency of the system. For example, when the turbine shroud is cooled during operation, the fluid (e.g., air) used to cool the shroud absorbs heat. When discharged from the shroud, this heated cooling fluid may flow directly adjacent to the portion of the turbine housing that supports the shroud and various other components of the turbine, being exposed to and / or contacting the portion of the turbine housing that supports the shroud and various other components of the turbine. The housing and / or components of the shroud that supports the turbine and / or various other components may be negatively impacted or affected by exposure to the high temperature cooling fluid. That is, exposure to the cooling fluid having a high temperature may undesirably and prematurely degrade the material forming the housing, which in turn reduces the 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; an aft end positioned opposite the front end, the aft end including a second hook coupled to the turbine casing; a base portion extending between the front end and the aft end and positioned radially opposite the first and second hooks coupled to the turbine casing, the base portion including an inner surface facing a hot gas flow path for the turbine system; a flange extending from the aft end and positioned radially between the base portion and the second hook; a cooling passage positioned within the base portion adjacent the inner surface; and at least one aft end exhaust pipe in fluid communication with the cooling passage, the at least one aft end exhaust pipe extending radially through the aft end between the base portion and the flange.

[0006] A second aspect of the present disclosure provides a turbine system, the turbine system comprising: a turbine housing; and a first stage, the first stage being positioned within the turbine housing, the first stage comprising: a plurality of turbine blades, the plurality of turbine blades being positioned within the turbine housing and circumferentially around a rotor; a plurality of stator blades, the plurality of stator blades being positioned within the turbine housing and downstream of the plurality of turbine blades; and a plurality of turbine shrouds, the plurality of turbine shrouds being positioned adjacent to the plurality of turbine blades and radially upstream of the plurality of stator blades, each of the plurality of turbine shrouds comprising: a front end comprising a first hook coupled to the turbine housing; and a rear end positioned opposite the front end. The exhaust pipe is connected to the exhaust gas supply channel of the turbine housing and the exhaust gas supply channel of the turbine housing to form a through-hole, and the exhaust gas supply channel is connected to the exhaust gas supply channel of the turbine housing to form a through-hole.

[0007] A third aspect of the present disclosure provides a stator blade positioned within a turbine housing of a turbine system. The stator blade comprises: 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 housing, the base portion including an inner surface facing a hot gas flow path for the turbine system; a flange extending from the rear end and positioned radially between the base portion and the turbine housing; a cooling passage positioned adjacent the base portion and the inner surface; and at least one rear end exhaust pipe in fluid communication with the cooling passage, the at least one rear end exhaust pipe extending radially through the rear end between the base portion and the flange.

[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 1shows a schematic diagram of a gas turbine system according to an embodiment of the present disclosure;

[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 casing, and a turbine shroud;

[0012] Figure 3 The embodiment according to the present disclosure is shown Figure 2 Isometric view of the turbine shroud;

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

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

[0015] Figure 6 The embodiment according to the present disclosure is shown along Figure 4 a cross-sectional side view of the turbine shroud taken along line 6-6;

[0016] Figures 7 to 9 shows a cross-sectional side view of a turbine shroud according to an additional embodiment of the present disclosure;

[0017] Figure 10 A turbine shroud including a turbine shroud according to an embodiment of the present disclosure is shown. Figure 2 an enlarged side view of a portion of a turbine of a gas turbine system;

[0018] Figure 11 shows a top view of a turbine shroud according to another embodiment of the present disclosure;

[0019] Figure 12 The embodiment according to the present disclosure is shown along Figure 11 a cross-sectional side view of the turbine shroud taken along line 12-12;

[0020] Figure 13 shows a top view of a turbine shroud according to another embodiment of the present disclosure;

[0021] Figure 14 shows a side view of a stator blade according to an embodiment of the present disclosure;

[0022] Figure 15 The embodiment according to the present disclosure is shown along Figure 14a cross-sectional side view of the stator blade taken along line 15-15 in FIG.

[0023] Figure 16 and Figure 17 Another embodiment according to the present disclosure is shown Figure 14 Cross-sectional side view of a stator blade.

[0024] 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

[0025] 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.

[0026] 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 specified, 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. In addition, the terms "front" and "rear" may be used and / or understood to be similar in description to the terms "front" and "rear", respectively. Often, 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 section). 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), 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").

[0027] As indicated above, the present disclosure provides hot gas path components for turbine systems, and more particularly, relates to turbine shrouds and stator blades including a plurality of aft exhaust ducts and aft flanges.

[0028] Reference below Figures 1 to 17 These and other embodiments are discussed. However, 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.

[0029] 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.).

[0030] The gas turbine system 10 may also include an exhaust frame 34. Figure 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 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.

[0031] 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, the combustion gases 26 may flow through the exhaust frame 34 in a flow direction (D) and may 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 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.

[0032] Go to Figure 2 , showing a portion of the turbine 28. Specifically, Figure 2 A 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 via retention members 41 extending from the casing 36. Figure 2 , the stator blade 40 may include a plurality of hot gas path (HGP) components including and / or formed to be directly coupled to the retention member 41, 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, and more specifically, the outer platform 42, may be positioned directly adjacent to and downstream of a turbine shroud of the turbine 28.

[0033] 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 blade 40 may also be positioned axially adjacent to each other within the casing 36. Figure 2 In the non-limiting example shown in FIG, stator blades 40 may be located adjacent to and axially downstream of turbine blades 38. For clarity, not all turbine blades 38, stator blades 40, and / or all rotors 30 of 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 .

[0034] 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 define a flow path (FP) of the combustion gases 26 flowing through the turbine 28. Figure 2 In the non-limiting example shown in , a stage of turbine shroud 100 may be radially positioned adjacent to a stage of turbine blades 38 and / or may substantially surround or encircle the stage. The turbine shroud 100 may be radially positioned adjacent to the tip portion 48 of the airfoil 46 of the turbine blade 38. Additionally, in a non-limiting example, the turbine shroud 100 may also be positioned adjacent to and / or radially upstream of the stator blades 40 of the turbine 28. The turbine shroud 100 may also be positioned between two adjacent stages of stator blades positioned thereon, and may surround either axial side of a single stage of turbine blades.

[0035] 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 about the casing. Figure 2In the non-limiting example shown in FIG, the turbine shroud 100 may be directly coupled to the casing 36 of the turbine 28 via coupling members 52 extending radially inward (e.g., toward the rotor 30) from the casing 36. As discussed herein, the coupling members 52 may include openings 54 that may be configured to couple to and / or receive fasteners or hooks of the turbine shroud 100 (see FIG. Figure 3 ) 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 members 52 may be coupled and / or secured to the casing 36 of the turbine 28. More specifically, the coupling members 52 may be disposed circumferentially about the casing 36 and may be positioned radially adjacent the turbine blades 38. In another non-limiting example, the coupling members 52 may be integrally formed with the casing 36 and / or may be a portion of 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 in 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 coupling members 52 .

[0036] Go to Figures 3 to 6 , shows the 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 top view of a turbine shroud 100, Figure 5 A side view of the turbine shroud 100 is shown, and Figure 6 A cross-sectional side view of a turbine shroud 100 is shown.

[0037] In the non-limiting example shown, the turbine shroud 100 may include a unitary body. Figures 3 to 6 As shown in , the turbine shroud 100 may include and / or be formed as a unitary body such that the turbine shroud 100 is a single, continuous and / or non-disjointed component or portion. Figures 3 to 6 In the non-limiting example shown in , because the turbine shroud 100 is formed from a unitary body, 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 2). In contrast, as discussed herein, once a single, continuous, and / or non-disjointed, unitary body for the turbine shroud 100 is constructed, the turbine shroud 100 may be immediately installed within the turbine system 10 .

[0038] The monolithic body of the turbine shroud 100 and the various components and / or features of the turbine shroud 100 may be formed using any suitable one or more additive manufacturing processes and / or methods. For example, the turbine shroud 100 including the monolithic 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 one or more additive manufacturing processes. Additionally, the monolithic body of the turbine shroud 100 may be formed from any material that can 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] In another non-limiting example (see Figure 9 ), the turbine shroud 100 may be formed into a plurality of different pieces and / or sections that may be constructed separately and subsequently assembled, coupled, joined, and / or attached to one another prior to installation of the turbine shroud 100 within the gas turbine system 10. The turbine shroud 100 may be assembled using any suitable technique or process known for joining / forming components, including, but not limited to, welding, brazing, melting, joining, and the like. Additionally, the turbine shroud 100 formed of different sections and / or pieces may be formed of any material that can undergo the process for joining / forming the turbine shroud 100 from different pieces and that is capable of withstanding the operational characteristics (e.g., exposure temperatures, exposure pressures, etc.) to which the turbine shroud 100 is subjected during operation within the gas turbine system 10.

[0040] The turbine shroud 100 may also include various ends, sides, and / or surfaces. For example, and as Figure 3 and Figure 4 As shown in FIG, the turbine shroud 100 may include a forward end 102 and an aft end 104 positioned opposite the forward end 102. The forward end 102 may be positioned upstream of the aft end 104 such that the combustion gases 26 flowing through a flow path (FP) defined within the turbine 28 may flow past the adjacent forward end 102 before flowing past the adjacent aft end 104 of the turbine shroud 100. Figure 3 and Figure 4As shown in FIG, the front end 102 may include a first hook 106 configured to couple to and / or engage the coupling member 52 of the casing 36 of the turbine 28 to couple, position, and / or secure the turbine shroud 100 within the casing 36 (see FIG. Figure 2 ). Additionally, the rear end 104 may include a second hook 108 positioned opposite the first hook 106 and / or formed on the turbine shroud 100. Similar to the first hook 106, the second hook 108 may be configured to couple to and / or engage the coupling member 52 of the casing 36 of the turbine 28 to couple, position, and / or secure the turbine shroud 100 within the casing 36 (see Figure 2 ).

[0041] In addition, the turbine shroud 100 may further include a first oblique surface or side 110 (hereinafter referred to as “first side 110 ”) and a second oblique surface or side 112 (hereinafter referred to as “second side 112 ”) located opposite the first side 110 . Figure 3 and Figure 4 As shown in FIG, the first side 110 and the second side 112 may each be formed or positioned proximate to the front end 102 and the rear end 104 and extend and / or be positioned between the front end 102 and the rear end 104 .

[0042] like Figures 3 to 5 As shown in FIG, the turbine shroud 100 may also include an outer surface 120. The outer surface 120 may face the outer surface 120 between the turbine shroud 100 and the turbine casing 36 (see FIG. Figure 2 ) formed between the cooling chamber 122 (see Figure 5 ). More specifically, the outer surface 120 may be positioned, formed, facing, and / or directly exposed to 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 the opening 54 of the coupling member 52 of the casing 36. As discussed herein, the cooling chamber 122 formed between the turbine shroud 100 and the turbine casing 36 may receive cooling fluid and / or provide cooling fluid to the turbine shroud 100 during operation of the turbine 28. In addition to facing the cooling chamber 122, the outer surface 120 of the turbine shroud 100 may also be formed and / or positioned between the forward end 102 and the aft end 104 and between the first side 110 and the second side 112, respectively.

[0043] The turbine shroud 100 may also include an inner surface 124 formed opposite the outer surface 120. Figure 3 and Figure 5 As shown in the non-limiting example of FIG, the inner surface 124 of the turbine shroud 100 may be formed radially opposite the outer surface 120. In short, returning to Figure 2 , and continue to refer to Figure 3and Figure 5 , the inner surface 124 may face the flow through the turbine 28 (see Figure 2 ). More specifically, the inner surface 124 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. Additionally, the inner surface 124 of the turbine shroud 100 may be positioned radially adjacent the tip portion 48 of the airfoil 42 (see FIG. Figure 2 The inner surface 124 may be formed and / or extend axially between the front end 102 and the rear end 104 of the turbine shroud 100. Additionally, the inner surface 124 may be formed and / or extend circumferentially between the opposing sides 110, 112 of the turbine shroud 100. The inner surface 124 may also be formed radially opposite the first hook 106 and the second hook 108, respectively.

[0044] Go to Figure 6 , continue to refer to Figures 3 to 5 , additional features of the turbine shroud 100 are now discussed. The turbine shroud 100 may include a base portion 126. Figure 6 , the base portion 126 can be formed as an integral part of the turbine shroud 100. In addition, the base portion 126 can include an inner surface 124 and / or the inner surface 124 can 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 the front end 102 and the rear end 104, and between the first side 110 and the second side 112, respectively. The base portion 126 can also be formed integrally with the first side 110 and the second side 112 of the turbine shroud 100. In a non-limiting example, the base portion 126 can also be radially opposite and / or positioned radially inward from the first hook 106 and the second hook 108 of the turbine shroud 100 that are coupled to the turbine casing 36 (see Figure 2 As discussed herein, the base portion 126 of the turbine shroud 100 may at least partially form and / or define at least one cooling passage within the turbine shroud 100 .

[0045] The turbine shroud 100 may include an impact portion 128. Similar to the base portion 126, as shown Figure 6As shown in , the impact portion 128 can be formed as an integral part of the turbine shroud 100. The impact portion 128 can include the outer surface 120 and / or the outer surface 120 can be formed on the impact portion 128 of the turbine shroud 100. The impact portion 128 of the turbine shroud 100 can be formed, positioned, and / or extend between the front end 102 and the rear end 104, and between the first side 110 and the second side 112, respectively. Additionally, and also similar to the base portion 126, the impact portion 128 can be integrally formed with the first side 110 and the second side 112 of the turbine shroud 100. As shown in Figure 6 , the impact portion 128 may be positioned radially adjacent to the base portion 126 and / or may be positioned radially between the base portion 126 and the first and second hooks 106, 108, respectively. As discussed herein, the impact portion 128 of the turbine shroud 100, along with the base portion 126, may at least partially form and / or define at least one cooling channel within the turbine shroud 100.

[0046] like Figure 6 As shown in , the turbine shroud 100 may further include a flange 130. The flange 130 may extend from the aft end 104 of the turbine shroud 100. More specifically, the flange 130 may extend (substantially) axially from the aft end 104 and may be positioned radially between the base portion 126 and the second hook 108 of the turbine shroud 100. Additionally, the flange 130 may extend (circumferentially) from the aft end 104 between the first side 110 and the second side 112. Figure 6 In the non-limiting example shown in , 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 Figure 7 and Figure 8 ), the flange 130 may be angled and / or may extend at an angle from the aft end 104. As shown, the flange 130 may be integrally formed with the aft end 104 of the turbine shroud 100. In another non-limiting example (not shown), the flange 130 may be formed as a different feature and / or component that may be subsequently installed and / or attached to the aft end 104 of the turbine shroud 100 before the turbine shroud 100 is implemented within the gas turbine system 10 (see FIG. Figure 1 and Figure 2 ). In addition, Figure 6 As shown in the non-limiting example of FIG, the base portion 126 of the turbine shroud 100 may extend axially beyond the flange 130 and / or may extend axially further than the flange 130. In other non-limiting examples, the flange 130 may extend axially beyond the base portion 126 (see FIG. Figure 9), or may extend axially from the aft end 104 to be radially aligned with the base portion 126 (not shown). As discussed herein, the flange 130 may direct cooling fluid from the turbine shroud 100 away from the casing 36 and / or the coupling component 52 (see Figure 2 and Figure 10 ) and / or may block the cooling fluid from the turbine shroud 100 from contacting the housing 36 and / or the coupling component 52. Additionally, and as discussed herein, the flange 130 may also absorb heat transferred to the cooling fluid previously used to cool the turbine shroud 100.

[0047] 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. Figure 4 and Figure 6 As shown in FIG, the turbine shroud 100 may include cooling passages 132 formed, positioned, and / or extending within the turbine shroud 100. More specifically, and briefly returning to FIG. Figure 4 , the cooling passage 132 of the turbine shroud 100 ( Figure 4 ) may extend within the turbine shroud 100 between and / or adjacent the front end 102, the rear end 104, the first side 110, and the second side 112, respectively. Figure 6 As shown in FIG, cooling passages 132 may extend (radially) within the turbine shroud 100 between the base portion 126 and the impingement portion 128 and / or may be at least partially defined by the base portion and the impingement portion. The cooling passages 132 may also be positioned substantially adjacent to the inner surface 124 and / or formed within the base portion 126. As discussed herein, the cooling passages 132 may receive cooling fluid from the cooling chamber 122 to cool the turbine shroud 100. The dimensions (e.g., radial opening height) of the cooling passages 132 may depend on a variety of factors, including, but not limited to, the dimensions of the turbine shroud 100, the thickness of the base portion 126 and / or the impingement portion 128, the cooling requirements of the turbine shroud 100, and / or the geometry or shape of the forward end 102 and / or aft end 104 of the turbine shroud 100.

[0048] To provide cooling fluid to the cooling passages 132, the turbine shroud 100 may also include a plurality of impingement openings 134 formed therethrough. Figure 4 and Figure 6As shown in FIG, the turbine shroud 100 may include a plurality of impingement openings 134 formed through the outer surface 120 (and more specifically, the impingement portion 128) of the turbine shroud 100. The plurality of impingement openings 134 formed through the outer surface 120 and / or the impingement portion 128 may fluidly couple the cooling passages 132 to the cooling chamber 122. As discussed herein, during operation of the gas turbine system 10 (see FIG. Figure 1 ), the cooling fluid flowing through the cooling chamber 122 may pass through or flow through the plurality of impingement openings 134 to reach the cooling passages 132 to substantially cool the turbine shroud 100 .

[0049] It should be understood that Figure 4 and Figure 6 As shown in FIG, the size and / or number of impingement openings 134 formed through the outer surface 120 and / or the impingement portion 128 are merely illustrative. As such, the turbine shroud 100 may include larger or smaller impingement openings 134 and / or may include more or fewer impingement openings 134 formed therein. Additionally, while the size and / or shape of the plurality of impingement openings 134 are shown as being substantially uniform, it should be understood that each of the plurality of impingement openings 134 formed on the turbine shroud 100 may include a different size and / or shape. The size, shape, and / or number of the impingement openings 134 formed in 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 impingement openings 134 formed in the turbine shroud 100 may depend, at least in part, on characteristics of the turbine shroud 100 / cooling passages 132 (e.g., thickness of the base portion 126 , thickness of the impingement portion 128 , height of the cooling passages 132 , volume of the cooling passages 132 , etc.).

[0050] Figure 4 and Figure 6 Also shown in FIG. 1 , the turbine shroud 100 may include a plurality of front exhaust pipes 136 (in FIG. Figure 4 132 and the cooling chamber 122. More specifically, the plurality of front exhaust pipes 136 may each be in fluid communication with the cooling passage 132 of the turbine shroud 100 and may extend axially therefrom. Figure 6 In the non-limiting example shown in FIG, a plurality of front exhaust ducts 136 may 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 connected to the turbine 28 (see FIG. Figure 2), which is positioned upstream of and axially aligned with the forward end 102 of the turbine shroud 100. During operation, and as discussed herein, the plurality of forward exhaust ducts 136 may discharge cooling fluid (e.g., cooled fluid) from the cooling passages 132 adjacent to and upstream of the forward end 102 of the turbine shroud 100.

[0051] It should be understood that the turbine shroud 100 may include any number of front end ducts 136 formed therein and in fluid communication with the cooling passages 132. Additionally, while illustrated as being substantially circular / round and linear, it should be understood that one or more of the front end ducts 136 may be non-circular and / or non-linear openings, passages, and / or manifolds. Where one or more of the front end ducts 136 are formed as non-circular and / or non-linear, the flow direction of the cooling fluid may vary to improve cooling of the front end 102 of the turbine shroud 100. Furthermore, the one or more front end ducts 136 may also have varying sizes between each of the front end ducts 136, depending on the cooling needs of the turbine shroud 100 during operation.

[0052] Also like Figure 6 As shown in , the turbine shroud 100 may include a plurality of rear exhaust ducts 138. The plurality of rear exhaust ducts 138 may be in fluid communication with the cooling passage 132, and in turn, may be in fluid communication with the cooling chamber 122. More specifically, the plurality of rear exhaust ducts 138 may be in fluid communication with the cooling passage 132 of the turbine shroud 100 and may extend from the cooling passage. Additionally, and because the cooling passage 132 is in direct fluid communication with the cooling chamber 122, each of the plurality of rear exhaust ducts 138 may also be in fluid communication with the cooling chamber 122. Figure 6 As shown in FIG, a plurality of rear exhaust ducts 138 may extend through the turbine shroud 100 from the cooling passage 132 to the rear end 104 of the turbine shroud 100 and through the rear end of the turbine shroud. In addition, the plurality of rear exhaust ducts 138 may also extend and / or be positioned radially between the base portion 126 and the flange 130 of the turbine shroud 100. In a non-limiting example, the plurality of rear exhaust ducts 138 may also extend through the turbine shroud 100 at an angle (α). That is, and as shown in FIG. Figure 6 As shown in FIG, the plurality of aft exhaust ducts 138 may be angled 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 aft exhaust ducts 138 may also be aligned with the region of the turbine 28 (see FIG. Figure 2) in fluid communication with the turbine, a region of the turbine may be positioned downstream of and axially adjacent the aft end 104 of the turbine shroud 100. As discussed herein, a plurality of aft end exhaust ducts 138 may discharge cooling fluid (e.g., post-cooling fluid) from the cooling passages 132 adjacent and downstream of the aft end 104 of the turbine shroud 100.

[0053] Similar to the front exhaust ducts 136, it should be understood that the turbine shroud 100 may include any number of rear exhaust ducts 138 formed therein and in fluid communication with the cooling passages 132, and in turn, the cooling chamber 122. Additionally, while illustrated as being substantially circular / round and linear, it should be understood that the rear exhaust ducts 138 may be non-circular and / or non-linear openings, passages, and / or manifolds. Where one or more of the rear exhaust ducts 138 are formed as non-circular and / or non-linear, the flow direction of the cooling fluid may vary to improve cooling of the rear end 104 of the turbine shroud 100. Furthermore, the one or more rear exhaust ducts 138 may also have varying dimensions between each rear exhaust duct 138, depending on the cooling needs of the turbine shroud 100 during operation.

[0054] In the gas turbine system 10 (see Figure 1 ), the cooling fluid (CF) may flow through and 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 (see FIG. 1 ) flowing through the hot gas flow path of the turbine 28 during operation of the gas turbine system 10, the cooling fluid (CF) may flow through and cool the turbine shroud 10 ... Figure 2 ) and the temperature increases, a cooling fluid (CF) may be provided to and / or may flow through the cooling passages 132 formed between the base portion 126 and the impingement portion 128 to cool the turbine shroud 100. Figure 6 , various arrows may represent and / or may illustrate the flow path of the cooling fluid (CF) as it flows 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 passages 132 via 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 into / through the cooling passages 132 may cool the outer surface 120 / impingement portion 128 and / or the inner surface 124 / base portion 126 and / or receive heat therefrom. Once in the cooling passages 132, the cooling fluid (CF) may be dispersed and / or may flow axially toward one of the forward end 102 or the aft end 104 of the turbine shroud 100. Additionally, the cooling fluid (CF) may be dispersed and / or flow circumferentially toward one of the first side 110 or the second side 112 of the turbine shroud 100.

[0055] Once the cooling fluid (CF) within the cooling passages 132 has flowed to the opposite ends 102, 104 / sides 110, 112 of the turbine shroud 100, the cooling fluid (CF) may flow through respective exhaust ducts 136, 138. For example, a portion of the cooling fluid (CF) flowing axially through the cooling passages 132 toward the forward end 102 may be distributed and / or exhausted from the turbine shroud 100 via a plurality of forward exhaust ducts 136 that are in fluid communication with the cooling passages 132 and formed or extend through the forward end 102 of the turbine shroud 100.

[0056] For example, a portion of the cooling fluid (CF) flowing axially through the cooling passages 132 toward the aft end 104 may be distributed and / or discharged from the turbine shroud 100 via a plurality of aft exhaust ducts 138 that are in fluid communication with the cooling passages 132 and formed or extend through the aft end 104 of the turbine shroud 100. Once discharged from the aft exhaust ducts 138, the cooling fluid (e.g., cooled fluid) may flow toward, contact, and / or be redirected by the flange 130 of the turbine shroud 100. That is, because the plurality of aft exhaust ducts 138 extend upward from the cooling passages 132 toward the flange 130 through the aft end 104 at a radial angle (α), the cooling fluid may also be discharged from the aft exhaust ducts 138 directly toward the flange 130. The flange 130 may 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 cooling fluid exhausted from the aft exhaust duct 138 from flowing radially around the flange 130 and away from the base portion 126. As discussed herein, redirecting the cooling fluid by the flange 130 can prevent the cooling fluid from flowing through and / or contacting components of the turbine 28 that are located radially adjacent to the flange 130 and radially opposite or outwardly from the base portion 126 of the turbine shroud 100 (e.g., the casing 26, the coupling member 52 (see Figure 2 and Figure 10 ). In addition, 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 as the cooling fluid flows through the cooling passages 132. The cooled fluid that may contact 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., stator blades 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).

[0057] Figure 7-9 Additional non-limiting examples of turbine shrouds 100 are shown. More specifically, Figure 7-9An example of a turbine 28 that may be used in a gas turbine system 10 is shown (see FIG. Figure 1 ) are cross-sectional side views of various non-limiting examples of turbine shrouds 100. 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.

[0058] like Figure 7 As shown in FIG, the flange 130 of the turbine shroud 100 can be substantially angled. That is, the flange 130 can extend at an angle (β) from the aft end 104 of the turbine shroud 100. In a non-limiting example, the flange 130 can extend at an angle (β) radially toward the second hook 108 of the turbine shroud 100. More specifically, the flange 130 can extend radially outward toward the second hook 108 and / or radially outward or away from the base portion 126 of the turbine shroud 100. The angle (β) at which the flange 130 extends from the aft end 104 can be substantially similar to or different from the angle (α) at ​​which the plurality of aft end exhaust pipes 138 extend through the turbine shroud 100.

[0059] Go to Figure 8 , and similar to this paper with respect to Figure 7 For the non-limiting example shown and discussed, the flange 130 of the turbine shroud 100 may be substantially angled. That is, the flange 130 may extend at an angle (β) from the aft end 104 of the turbine shroud 100. Figure 7 Different, such as Figure 8 The flange 130 shown in FIG can extend radially toward the base portion 126 of the turbine shroud 100 at an angle (β). More specifically, the flange 130 can extend radially inward toward the base portion 126 and / or radially inward or away from the second hook 108 of the turbine shroud 100. Additionally, and as shown in FIG. Figure 8 As shown in FIG, the flange 130 may extend radially inwardly toward the plurality of rear exhaust pipes 138 .

[0060] exist Figure 9 In the non-limiting example shown in , the flange 130 extending axially from the rear end 104 can be substantially planar, axially oriented, and / or substantially parallel to the axis (A) and / or inner surface 124 of the base portion 126, as similarly discussed herein. However, unlike the embodiments described herein with respect to Figure 6 As shown and discussed in the non-limiting example, the flange 130 may extend axially beyond the base portion 126. That is, and as Figure 9 As shown in , the flange 130 may extend axially from the aft end 104 beyond the base portion 126 such that the most downstream portion of the aft end 104 of the turbine shroud 100 is the flange 130 .

[0061] In addition, if Figure 9, the turbine shroud 100 may be formed from two separate and / or distinct components or parts. More specifically, the impact portion 128 of the turbine shroud 100 may be distinct from the remainder of the turbine shroud 100, including the hooks 106, 108, the base portion 126, the flange 130, etc. The non-restrictive impact portion 128 may be formed from a separate plate 140 that may be coupled or attached to the remainder of the turbine shroud 100 and positioned adjacent the cooling chamber 122. The plate 140 forming the impact portion 128 may include the outer portion 120 and an impact opening formed therethrough. As discussed herein, the plate 140 may be coupled or attached to the remainder of the turbine shroud 100 using any suitable joining process to define / form the cooling passages 132 and ultimately form the turbine shroud 100.

[0062] Figure 10 Shown Figure 2 More specifically, Figure 10 A gas turbine system 10 is shown (see Figure 1 ), which includes the casing 36, the coupling member 52, the stator blades 40, and a portion of the turbine shroud 100. 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.

[0063] In addition, if Figure 10 As shown in FIG, the turbine 28 of the gas turbine system 10 may further include a seal 142. The seal 142 may extend between the stator blade 40 and the turbine shroud 100. More specifically, the seal 142 may extend between the aft end 104 of the turbine shroud 100 and the forward end of the stator blade 40. As shown in the non-limiting example, the seal 142 may also contact and / or be secured to the base portion 126 of the turbine shroud 100 adjacent the aft end 104 of the stator blade 40 and the outer platform 42. The seal 142 may contact and / or be secured to the base portion 128 of the turbine shroud 100 and the outer platform 42 of the stator blade 40 to form or define a portion of a flow path (FP) between the turbine shroud 100 and the stator blade 40. Additionally, the seal 142 may also, together with the casing 36, at least partially define and / or form a cooling fluid path 144 that may be formed between the turbine shroud 100 and the stator blade 40. As discussed herein, the seal 142 may prevent the combustion gases 26 from undesirably exiting the flow path (FP) defined by the turbine shroud 100 and the outer platform 42 of the stator blades 40 , and prevent cooling fluid (e.g., post-cooling fluid) exhausted from the turbine shroud 100 from entering the flow path (FP) and undesirably mixing with the combustion gases 26 .

[0064] The seal 142 may also be positioned radially on the turbine shroud 100 between the flange 130 and the base portion 126. Figure 10 As shown in FIG, a plurality of rear exhaust pipes 138 may be radially positioned between the flange 130 and the seal 142, thereby contacting the base portion 126. In addition, the flange 130 may also be radially positioned between the turbine housing 36 / coupling member 52 of the turbine 28 (see FIG. Figure 2 and Figure 10 ) and cooling passages 132 formed or positioned within the base portion 126 and / or the plurality of aft exhaust ducts 138. As discussed herein, during operation, cooling fluid discharged from the plurality of aft exhaust ducts 138 extending at an angle through the aft end 104 of the turbine shroud 100 may contact the flange 130 and be prevented from directly contacting the coupling member 52 of the casing 36. Additionally, the flange 130 may redirect the discharged cooling fluid radially inward and / or radially away from the coupling member 52 and / or the casing 36 and / or toward the seal 142. When the cooling fluid is redirected by the flange 130, it may flow downstream toward the stator blades 40 and may subsequently be utilized by the stator blades 40. For example, the cooling fluid discharged from the turbine shroud 100 and redirected by the flange 130 may be used to cool the retaining member 41 and / or the outer platform 42 of the stator blades 40 during operation of the turbine 28.

[0065] Figure 10 The portion of the turbine 28 shown in FIG. 1 may represent, for example, a first stage of blades 38 and stator vanes 40. As such, seals 142 may be positioned only between the aft end 104 of the turbine shroud 100 and the outer platforms 42 of the stator vanes 40. In downstream stages (e.g., intermediate or final stages), 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, seals 142 may be present and / or positioned between each set of stator vanes 40. More specifically, the seal 142 may be positioned between and / or contact the base portion 126 of the turbine shroud 100 adjacent the aft end 104 and the forward ends of the outer platforms 42 of the stator blades 40 positioned downstream of the turbine shroud 100, as described herein with respect to FIG. Figure 10Additionally, a different seal 142 may be positioned between and / or contact the base portion 126 of the blades 38 of the turbine shroud 100 adjacent the forward end 102 and the aft end of the outer platform 42 of the stator blades 40 positioned upstream of the turbine shroud 100. As similarly discussed herein, the seal 142 may define and / or separate a flow path (FP) of the combustion gases 26 of the turbine 28 and a cooling fluid path 144.

[0066] Figure 11-13 Additional non-limiting examples of turbine shrouds 100 are shown. More specifically, Figure 11-13 An example of a turbine 28 that may be used in a gas turbine system 10 is shown (see FIG. Figure 1 ) are various views of a non-limiting example of a turbine shroud 100. 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.

[0067] Figure 11 and Figure 12 Shown for Figure 1 Various views of additional non-limiting examples of a turbine shroud 100 for a turbine 28 of a gas turbine system 10 are provided. Specifically, Figure 11 A top view of the turbine shroud 100 is shown, and Figure 12 A cross-sectional side view of a turbine shroud 100 is shown. Figure 11 and Figure 12 The turbine shroud 100 shown in FIG. 1 may include a non-limiting example of a serpentine pattern 146 formed adjacent the aft end 104. That is, and as Figure 11 and Figure 12 As shown in , the serpentine pattern 146 may extend, meander, and / or include a plurality of turns spanning between the first side 110 and the second side 112 adjacent the aft end 118 of the turbine shroud 100. Each portion of the opening of the serpentine pattern 146 may also extend radially between the base portion 126 and the impingement portion 128 of the turbine shroud 100. In a non-limiting example, the serpentine pattern 146 formed adjacent the aft end 104 may be in fluid communication with the cooling passage 132 and each of the plurality of aft end exhaust ducts 138 extending through the aft end 104 of the turbine shroud 100. The serpentine pattern 146 may facilitate heat transfer and / or cooling of the turbine shroud 100 during operation of the gas turbine system 10, as discussed herein. Figure 12As shown in FIG, the cooling fluid may flow from the cooling passage 132 to and through the serpentine pattern 164 and back and forth between the first side 11 and the second side 112 before exiting one of the plurality of rear end exhaust pipes 138 extending at a radial angle (α). It should be understood that the number of turns included in the serpentine pattern 146 is exemplary. Thus, the serpentine pattern 146 formed adjacent the rear end 104 may include more than Figure 11 and Figure 12 In addition, it should be understood that in addition to or in place of the turns shown in Figure 11 and Figure 12 As shown in FIG. 1 , formed in the rear end 104 , the serpentine pattern 146 may also be formed in the front end 102 .

[0068] In additional non-limiting examples, the serpentine pattern 146 may be oriented differently within the turbine shroud 100. For example, the turbine shroud 100 may include different serpentine patterns 146 (not shown) that may extend, snake, and / or include multiple turns spanning between the base portion 126 and the impingement portion 128. In a non-limiting example (not shown), the serpentine pattern 146 may have a final turn that may be in fluid communication with each of the plurality of aft exhaust ducts 138 extending through the aft end 104 of the turbine shroud 100.

[0069] Figure 13 Another non-limiting example of a turbine shroud 100 is shown. 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, wherein each channel 148, 150 may include, be in direct fluid communication with, and / or be fluidly coupled to a corresponding (single) opening 152 formed in / through the impact portion 128. Additionally, as Figure 13 As shown in FIG, the passages 148 may extend toward the front end 102 and the passages 150 may extend toward the rear end 104. Thus, each passage 148 may be in fluid communication with and / or may be integrally formed with the front exhaust duct 136 extending through the front end 102 of the turbine shroud 100. Additionally, each passage 150 may be in fluid communication with and / or may be integrally formed with the rear exhaust duct 138 extending through the rear end 102 of the turbine shroud 100 at a radial angle (α) (see FIG. Figure 6 ).

[0070] Figures 14 to 17 Various views of a stator blade 200 are shown. More specifically, Figure 14-16 An example of a turbine 28 that may be used in a gas turbine system 10 is shown (see FIG. Figure 1 and Figure 2 ) various views of a non-limiting example of a stator blade 200. Figure 14 The stator blade 200 shown in FIG. 1 may include the stator blade 200 shown in FIG. 1 . Figure 2 . For example, stator blade 200 may include an outer platform 202, an inner platform 204 positioned opposite outer platform 202, and airfoils 206 positioned between outer platform 202 and inner platform 204, respectively. 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.

[0071] In addition, if Figure 14 As shown in FIG, the stator blade 200 may further include a retaining member 208. The retaining member 208 is Figure 14 That is, in some non-limiting examples, the stator blade 200 may include a retaining member 208 for circumferentially coupling and / or positioning the stator blade 200 around the casing 36 of the turbine 28 (see Figure 2 ). As shown in a non-limiting example, the retention member 208 may be coupled and / or connected to the outer platform 202 of the stator blade 200. In other non-limiting examples, the stator blade 200 may not include the retention member 208 (see Figure 16 Instead, the outer platform 202 may contact and / or be coupled to a different portion or component of the turbine 28 (eg, the turbine shroud 100 ) to be positioned and / or secured within the turbine 28 during operation.

[0072] Go to Figure 15 , shows a cross-sectional side view of the stator blade 200. Specifically, Figure 15 Shown along Figure 14 A cross-sectional side view of a portion of the stator blade 200 taken along line 15-15 is shown. Figure 15 As shown in and as discussed herein, stator blade 200 may include the stator blade 200 described herein with respect to Figure 3-9 The turbine shroud 100 shown in FIG may include features similar to those discussed above, which may help direct the cooling fluid away from the stator blade 200. The stator blade 200 may also include various ends, sides, and / or surfaces. For example, and as Figure 15 As shown in FIG, the stator blade 200 may include a front end 210 and a rear end 212 positioned opposite the front end 210. The front end 210 may be positioned upstream of the rear end 212 such that the combustion gases 26 flowing through a flow path (FP) defined within the turbine 28 may flow past the adjacent front end 210 before flowing past the adjacent rear end 212 of the stator blade 200. Figure 15As shown in FIG, the stator blade 200 may also include an outer surface 218. More specifically, in the non-limiting example where the stator blade 200 includes a retaining member 208, the retaining member 208 may include an outer surface 218. The outer surface 218 may face the stator blade 200 and the turbine casing 36 (see FIG. Figure 2 ) formed between the stator blade 200 and the turbine casing 36. More specifically, the outer surface 218 may be positioned, formed, facing, and / or directly exposed to the cooling chamber 220 formed between the retaining member 208 of the stator blade 200 and the turbine casing 36 of the turbine 28. As discussed herein, the cooling chamber 220 formed between the stator blade 200 and the turbine casing 36 may receive and / or provide cooling fluid to the stator blade 200 during operation of the turbine 28. In addition to facing the cooling chamber 220, the outer surface 218 of the stator blade 200 may also be formed and / or positioned between the leading end 210 and the trailing end 212 of the stator blade 200.

[0073] The stator blade 200 may further include an inner surface 222 formed opposite the outer surface 218. Figure 15 As shown in the non-limiting example of FIG, the inner surface 222 of the stator blade 200 can be formed radially opposite the outer surface 218. In a non-limiting example, the inner surface 222 can include and / or can be at least partially defined by the outer platform 202 of the stator blade 200, which faces the hot gas flow path (FP) of the combustion gases 26 flowing through the turbine 28 (see FIG. Figure 2 As discussed herein, the inner surface 222 at least partially defined by the outer platform 202 of the stator blade 200 may at least partially form and / or define at least one cooling passage within the stator blade 200 / retention member 208, which may be used to cool the retention member 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 blade 200.

[0074] The stator blade 200 may include an impact portion 224. The impact portion 224 may be formed as an integral part of the stator blade 200. The impact portion 224 may include the outer surface 218 and / or the outer surface 218 may be formed on the impact portion 224 of the stator blade 200. The impact portion 224 of the stator blade 200 may be formed, positioned, and / or extend between the front end 210 and the rear end 212 of the stator blade 200. Figure 15 As shown in , the impact portion 224 may be positioned radially adjacent to the inner surface 222 and / or may be positioned radially adjacent to the outer platform 202. As discussed herein, the impact portion 224 of the stator blade 200 may at least partially form and / or define at least one cooling passage within the stator blade 200.

[0075] like Figure 15 As shown in , the stator blade 200 may further include a flange 226. The flange 226 may extend from the aft end 212 of the stator blade 200. More specifically, the flange 226 may extend (substantially) axially from the aft end 212 of the retaining member 208 and may be positioned radially adjacent to the outer platform 202. Figure 15 In the non-limiting example shown in FIG, the flange 226 may be substantially planar, axially oriented, and / or substantially parallel to the axis (A). As shown, the flange 226 may be integrally formed with the aft end 212 of the retaining member 208 of the stator blade 200. In another non-limiting example (not shown), the flange 226 may be formed as a different feature and / or component prior to the stator blade 200 being implemented within the gas turbine system 10, which feature and / or component may then be mounted and / or attached to the aft end 212 of the retaining member 208 (see FIG. Figure 1 and Figure 2 ). In addition, Figure 15 As shown in the non-limiting example of FIG, the outer platform 202 of the stator blade 200 can extend axially beyond the flange 226 and / or can extend axially further than the flange 226. In other non-limiting examples, the flange 226 can extend axially beyond the outer platform 202, or can extend axially from the aft end 212 to be radially aligned with the outer platform 202 (not shown). As discussed herein, the flange 226 can direct cooling fluid from the stator blade 200 away from the casing 36 and / or can block cooling fluid from the stator blade 200 from contacting the casing 36. Additionally, and as discussed herein, the flange 226 can also absorb heat transferred to the cooling fluid previously used to cool the stator blade 200.

[0076] The stator blade 200 may also include at least one cooling passage formed therein for cooling the stator blade 200 during operation of the turbine 28 of the gas turbine system 10. Figure 15 As shown in , the stator blade 200 may include a cooling passage 228 formed, positioned, and / or extending within the stator blade 200. More specifically, the cooling passage 228 of the stator blade 200 may extend between and / or adjacent the front end 210 and the rear end 212 within the retaining member 208 of the stator blade 200. Additionally, and as shown Figure 15, a cooling passage 228 may extend (radially) within the stator blade 200 between the outer platform 202 and the impingement portion 224 and / or may be at least partially defined by the outer platform and the impingement portion. The cooling passage 228 may also be positioned and / or formed substantially adjacent to the inner surface 222. As discussed herein, the cooling passage 228 may receive cooling fluid from the cooling chamber 220 to cool the stator blade 200. The size (e.g., radial opening height) of the cooling passage 228 may depend on a variety of factors, including, but not limited to, the size of the stator blade 200, the thickness of the outer platform 202 and / or the impingement portion 224, the cooling requirements of the stator blade 200, etc.

[0077] To provide cooling fluid to the cooling passages 228, the stator blade 200 may also include a plurality of impingement openings 230 formed therethrough. Figure 15 As shown in FIG, the stator blade 200 may include a plurality of impingement openings 230 formed through the outer surface 218 (and more specifically, the impingement portion 224) of the stator blade 200. The plurality of impingement openings 230 formed through the outer surface 218 and / or the impingement portion 224 may fluidly couple the cooling passage 228 to the cooling chamber 220. As discussed herein, during operation of the gas turbine system 10 (see FIG. Figure 1 ), the cooling fluid flowing through the cooling chamber 220 may pass through or flow through the plurality of impingement openings 230 to reach the cooling passage 228 to substantially cool the stator blade 200 .

[0078] It should be understood that Figure 15 As shown in FIG, the size and / or number of impingement openings 230 formed through the outer surface 218 and / or the impingement portion 224 are merely illustrative. Thus, the stator blade 200 may include larger or smaller impingement openings 230 and / or may include more or fewer impingement openings 230 formed therein. Furthermore, while the size and / or shape of the plurality of impingement openings 230 are shown as being substantially uniform, it should be understood that each of the plurality of impingement openings 230 formed on the stator blade 200 may include a different size and / or shape. The size, shape, and / or number of impingement openings 230 formed in the stator blade 200 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 impingement openings 230 formed in the stator blade 200 may depend, at least in part, on the characteristics of the stator blade 200 / cooling passage 228.

[0079] The stator blade 200 may include a plurality of front exhaust ducts 232 (one shown). The plurality of front exhaust ducts 232 may be in fluid communication with the cooling passage 228. More specifically, the plurality of front exhaust ducts 232 may each be in fluid communication with the cooling passage 228 of the stator blade 200 and may extend axially therefrom. Figure 15 In the non-limiting example shown in FIG, a plurality of front exhaust ducts 232 may extend from the cooling passage 228 to the front end 210 through the retaining member 208 of the stator blade 200. In addition to being in fluid communication with the cooling passage 228, the plurality of front exhaust ducts 232 may be connected to the turbine 28 (see FIG. Figure 2 ) is fluidly connected to a region within the cooling passage 228 that is positioned upstream of and axially aligned with the leading end 210 of the stator blade 200. During operation, and as discussed herein, the plurality of leading end exhaust ducts 232 may discharge cooling fluid (e.g., post-cooling fluid) from the cooling passage 228 adjacent to and upstream of the leading end 210 of the stator blade 200.

[0080] It should be understood that the stator blade 200 may include any number of front end ducts 232 formed therein and in fluid communication with the cooling passages 228. Additionally, while illustrated as being substantially circular / round and linear, it should be understood that one or more of the front end ducts 232 may be non-circular and / or non-linear openings, passages, and / or manifolds. Where one or more of the front end ducts 232 are formed as non-circular and / or non-linear, the flow direction of the cooling fluid may vary to improve cooling of the front end 210 of the stator blade 200. Furthermore, the one or more front end ducts 232 may also have varying sizes between each of the front end ducts 232, depending on the cooling needs of the stator blade 200 during operation.

[0081] Also like Figure 15 As shown in , the stator blade 200 may include a plurality of rear exhaust ducts 234. The plurality of rear exhaust ducts 234 may be in fluid communication with the cooling passage 228, and in turn may be in fluid communication with the cooling chamber 220. More specifically, the plurality of rear exhaust ducts 234 may be in fluid communication with the cooling passage 228 of the stator blade 200 and may extend from the cooling passage. In addition, and because the cooling passage 228 is in direct fluid communication with the cooling chamber 220, each of the plurality of rear exhaust ducts 234 may also be in fluid communication with the cooling chamber 220. As shown in FIG. Figure 15As shown in , a plurality of aft exhaust ducts 234 may extend through the retaining member 208 of the stator blade 200, extending from the cooling channel 228 to the aft end 212 of the stator blade 200 and extending through the aft end 212 of the stator blade 200. In addition, the plurality of aft exhaust ducts 234 may also extend and / or may be radially positioned between the outer platform 202 (e.g., the base portion 236) and the flange 226 of the stator blade 200. In a non-limiting example, the plurality of aft exhaust ducts 234 may also extend through the stator blade 200 at an angle (α). That is, and as Figure 15 As shown in FIG, the plurality of rear exhaust ducts 234 may be angled radially outward from the cooling passage 228 toward the flange 226 and / or may extend through the stator blade 200 at a radial angle (α). The plurality of rear exhaust ducts 234 may also be aligned with a region of the turbine 28 (see FIG. Figure 2 ) fluidly connected to the turbine, the region of the turbine may be positioned downstream of and axially adjacent the aft end 212 of the stator blade 200. As discussed herein, the plurality of aft end exhaust ducts 234 may be adjacent to and discharge cooling fluid (e.g., post-cooling fluid) from the cooling passages 228 downstream of the aft end 212 of the stator blade 200.

[0082] Similar to the front exhaust ducts 232, it should be understood that the stator blade 200 may include any number of rear exhaust ducts 234 formed therein and in fluid communication with the cooling passages 228, and in turn, the cooling chamber 220. Additionally, while illustrated as being substantially circular / round and linear, it should be understood that the rear exhaust ducts 234 may be non-circular and / or non-linear openings, channels, and / or manifolds. Where one or more of the rear exhaust ducts 234 are formed as non-circular and / or non-linear, the flow direction of the cooling fluid may vary to improve cooling of the rear end 212 of the stator blade 200. Furthermore, the one or more rear exhaust ducts 234 may also have varying dimensions between each rear exhaust duct 234, depending on the cooling needs of the stator blade 200 during operation.

[0083] In the gas turbine system 10 (see Figure 1 ), the cooling fluid (CF) may flow through and cool the stator blades 200. More specifically, when the stator blades 200 are exposed to the combustion gases 26 (see FIG. 1 ) flowing through the hot gas flow path of the turbine 28 during operation of the gas turbine system 10, ... Figure 2 ) and the temperature increases, a cooling fluid (CF) may be provided to and / or may flow through a cooling passage 228 formed between the outer platform 202 and the impingement portion 224 to cool the retaining member 208 of the stator blade 200 and / or the outer platform 202. Figure 15, various arrows may represent and / or may illustrate the flow path of the cooling fluid (CF) as it flows through the stator blade 200. In a non-limiting example, the cooling fluid (CF) may first flow from the cooling chamber 220 to the cooling passages 228 via a plurality of impingement openings 230 formed through the outer surface 218 and / or the impingement portion 224 of the stator blade 200. The cooling fluid (CF) flowing into / through the cooling passages 228 may cool the outer surface 218 / impingement portion 224 and / or the inner surface 222 / outer platform 202 and / or receive heat therefrom. Once in the cooling passages 228, the cooling fluid (CF) may be dispersed and / or may flow axially toward one of the front end 210 or the rear end 212 of the stator blade 200. Additionally, the cooling fluid (CF) may be dispersed and / or flow circumferentially toward one of the first side 110 or the second side 112 of the stator blade 200.

[0084] Once the cooling fluid (CF) within the cooling passages 228 has flowed to the opposite ends 102, 104 / sides 110, 112 of the stator blade 200, the cooling fluid (CF) may flow through corresponding exhaust ducts 232, 234. For example, a portion of the cooling fluid (CF) flowing axially through the cooling passages 228 toward the leading end 210 may be distributed and / or discharged from the stator blade 200 via a plurality of leading end exhaust ducts 232 that are in fluid communication with the cooling passages 228 and formed or extend through the leading end 210 of the stator blade 200.

[0085] Furthermore, a portion of the cooling fluid (CF) that flows axially through the cooling passage 228 toward the aft end 212 may be distributed and / or discharged from the stator blade 200 via a plurality of aft end exhaust ducts 234 that are in fluid communication with the cooling passage 228 and that form or extend through the aft end 212 of the stator blade 200. Once discharged from the aft end exhaust ducts 234, the cooling fluid (e.g., cooled fluid) may flow toward the flange 226 of the stator blade 200, contact the flange of the stator blade, and / or may be redirected by the flange of the stator blade. That is, because the plurality of aft end exhaust ducts 234 extend upwardly through the aft end 212 from the cooling passage 228 / toward the flange 226 at a radial angle (α), the cooling fluid may also be discharged from the aft end exhaust ducts 234 directly toward the flange 226. The flange 226 may then direct the cooled fluid radially back toward the outer platform 202 and / or radially away from different portions of the retaining member 208 of the stator blade 200 / casing 36 (see Figure 2). Additionally, the flange 226 can prevent the cooling fluid exhausted from the aft exhaust duct 234 from flowing radially around the flange 226 and away from the outer platform 202. As discussed herein, redirecting the cooling fluid by the flange 226 can prevent the cooling fluid from flowing through and / or contacting components of the turbine 28 that are located radially adjacent to the flange 226 and radially opposite or outwardly from the outer platform 202 of the stator blade 200 (e.g., the casing 26) (see Figure 2 ). In addition, the flange 226 can also absorb and / or dissipate at least a portion of the heat transferred from the stator blade 200 to the cooling fluid as the cooling fluid flows through the cooling passage 228. The cooling fluid that may contact the flange 226 and / or be redirected by the flange 226 can continue to flow axially away from / downstream of the stator blade 200 toward downstream components of the turbine 28 (e.g., the turbine shroud 100). As discussed herein, the downstream components can utilize the cooling fluid from the stator blade 200 for additional processing (e.g., for cooling purposes).

[0086] Figure 16 Another non-limiting example of a stator blade 200 is shown. In a non-limiting example, the stator blade 200 may or may not include a retaining member 208 (shown in phantom as optional). In a non-limiting example, features for cooling the stator blade 200 may be formed and / or positioned directly within the outer platform 202 of the stator blade 200. That is, and as Figure 16 As shown in , the outer surface 218, the inner surface 222, the impingement portion 224, the cooling passages 228, and the openings 230 may all be formed in and / or integrally formed with the outer platform 202 of the stator blade 200. Figure 16 As shown in FIG, the flange 226 of the stator blade 200 may be integrally formed with the outer platform 202. More specifically, the flange 226 may be integrally formed within the outer platform 202 and radially formed above or adjacent a base portion 236 of the outer platform 202 that may be exposed to hot gases during operation of the turbine 28 (see FIG. Figure 2 ), as discussed in this article. In addition, Figure 16 As shown in FIG, the flange 226 may extend substantially axially from a cooling passage 228 formed in the outer platform 202 .

[0087] In addition, and as Figure 16As shown in FIG, exhaust ducts 232 and 234 may be formed within the outer platform 202 and may extend through the outer platform 202. More specifically, a plurality of forward exhaust ducts 232 may extend through the forward end 210 of the outer platform 202 to discharge cooling fluid from a cooling chamber 228 formed within the outer platform 202. Additionally, each of a plurality of aft exhaust ducts 234 may extend through the aft end 212 of the outer platform 202 of the stator blade 200. In a non-limiting example, the plurality of aft exhaust ducts 234 may extend radially between and / or through the aft end 212 of the outer platform 202 between a base portion 236 of the outer platform 202 and the flange 226; further, they may be integrally formed with the outer platform 202. As similarly discussed herein, the plurality of aft exhaust ducts 234 may extend upward through the aft end 212 of the outer platform 202 at a radial angle (α) toward the flange 226, such that cooling fluid may be discharged from the aft exhaust ducts 234 directly toward the flange 226.

[0088] Figure 17 An additional non-limiting example of a stator blade 200 is shown. In a non-limiting example, a cooling passage 228 formed in a portion of the outer platform 202 of the stator blade 200 can be fully exposed and / or open to a cooling chamber 220 of the stator blade 200. In one example, the cooling chamber 220 can be formed within the retaining member 208 (shown in phantom as optional). In another non-limiting example, the cooling chamber 220 can represent the space between the outer platform 202 of the stator blade 200 and the casing 36 of the turbine 28 (see FIG. 2 ). Figure 2 In this manner, cooling fluid (CF) used to cool the outer platform 202 of the stator blades 200 may flow directly from the cooling chamber 220 to the cooling passages 228 and subsequently be exhausted from the tubes 232 , 234 , as discussed herein.

[0089] The technical effect is to provide a hot gas path component (e.g., turbine shroud, stator blade) including a plurality of angled exhaust ducts and aft flanges. The hot gas path component including the angled exhaust ducts and aft flanges prevents the cooled fluid from being undesirably discharged directly toward and / or undesirably contacting the turbine housing or a coupling component of the turbine that holds the hot gas path component therein.

[0090] 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.

[0091] 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 is related. 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 the value unless otherwise dependent on the precision of the instrument used to measure the value.

[0092] 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) coupled to a casing (36) of a turbine (28) of a turbine system (10), the turbine shroud (100) comprising: a front end (102) including a first hook (106) coupled to the turbine (28) housing (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) housing (36); a base portion (126) extending between the forward end (102) and the aft 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 hot 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 the inner surface (124); and at least one rear exhaust pipe (138) in fluid communication with the cooling passage (132), the at least one rear exhaust pipe (138) extending radially through the rear end (104) between the base portion (126) and the flange (130), The at least one rear exhaust pipe (138) is angled radially outward from the cooling passage (132, 228) toward the flange (130, 226) such that cooling fluid in the cooling passage (132) is discharged directly from the rear exhaust pipe (138) toward the flange (130).

2. The turbine shroud (100) of claim 1, further comprising: a first side (110) formed proximal to the front end (102) and the rear end (104) and extending between the front end (102) and the rear end (104); and A second side (112) is positioned opposite the first side (110), the second side (112) being formed proximal to the front end (102) and the rear end (104) and extending between the front end (102) and the rear end (104).

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

4. The turbine shroud (100) of claim 1, wherein the flange (130) extends angularly from the aft end (104) and extends one of: radially outwardly towards the second hook (108), or Radially inwardly toward the base portion (126). The turbine shroud (100) of claim 1 , wherein the flange (130) extends axially beyond the base portion (126). The turbine shroud (100) of claim 1 , wherein the flange (130) is positioned radially between the cooling passage (132) and the turbine (28) casing (36).

7. A turbine system (10), comprising: a turbine (28) housing (36); and A first stage, the first stage being positioned within the turbine (28) housing (36), the first stage comprising: a plurality of turbine blades (38) positioned within the turbine (28) housing (36) and circumferentially around the rotor (30); a plurality of stator blades (40, 200) positioned within the turbine (28) housing (36) downstream of the plurality of turbine blades (38); and A plurality of turbine shrouds (100) are positioned radially adjacent the plurality of turbine (28) blades (38) and upstream of the plurality of stator vanes (40, 200), each turbine shroud of the plurality of turbine shrouds (100) being a turbine shroud (100) according to any one of the preceding claims.

8. The turbine system (10) of claim 7, further comprising: A seal (142) extending between the plurality of stator blades (40, 200) and each of the plurality of turbine shrouds (100), the seal (142) contacting: the base portion (126) of each of the plurality of turbine shrouds (100) adjacent the aft end (104); and An outer platform (42) of each of the plurality of stator blades (40, 200).

9. The turbine system (10) of claim 8, wherein the at least one aft exhaust pipe (138) of each of the plurality of turbine shrouds (100) is positioned radially between the flange (130) and the seal (142) contacting the base portion (126).

10. A stator blade (40, 200) positioned within a turbine (28) casing (36) of a turbine system (10), the stator blade (40, 200) comprising: frontend(210); a rear end (212), the rear end being positioned relative to the front end (210); a base portion (236) extending between the forward end (210) and the aft end (212) and positioned radially opposite the turbine (28) casing (36), the base portion (236) including an inner surface (222) facing a hot gas flow path for the turbine system (10); a flange (226) extending from the aft end (212) and positioned radially between the base portion (236) and the turbine (28) housing (36); a cooling channel (228) positioned adjacent the base portion (236) and the inner surface (222); and at least one rear exhaust pipe (234) in fluid communication with the cooling passage (228), the at least one rear exhaust pipe (234) extending radially through the rear end (212) between the base portion (236) and the flange (226), The at least one rear exhaust pipe (234) is angled radially outward from the cooling channel (228) toward the flange (226) such that cooling fluid in the cooling channel (228) is discharged directly from the rear exhaust pipe (234) toward the flange (226).

11. The stator blade (40, 200) according to claim 10, further comprising: An outer platform (42, 202) is positioned radially adjacent the turbine (28) casing (36), the outer platform (42, 202) including at least a portion of the base portion (236).

12. The stator blade (40, 200) of claim 11, wherein the stator blade extends from the rear end (212) of: The outer platform (42, 202), or A retaining member (208) is coupled to the turbine (28) casing (36), the retaining member (208) being positioned between the turbine (28) casing (36) and the outer platform (202).

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