阅读说明：本技术 包括多个冷却通道的涡轮机护罩 (Turbine shroud including multiple cooling channels ) 是由 特拉维斯·J·帕克 本杰明·保罗·拉西 ***·塞泽 扎卡里·约翰·斯奈德 布拉德·威尔逊· 于 2019-07-17 设计创作，主要内容包括：本发明公开了用于涡轮机系统的涡轮机护罩。所述涡轮机护罩可以包括整体主体,所述整体主体包括：前端和后端,面向在所述整体主体与所述涡轮机系统的涡轮机壳体之间形成的冷却室的外表面,以及面向热气体流动路径的内表面。所述护罩还可以包括在所述整体主体内延伸的第一冷却通道,以及通过所述整体主体的所述外表面形成以将所述第一冷却通道流体地联接到所述冷却室的多个冲击开口。附加地,所述护罩可以包括第二冷却通道和/或第三冷却通道。所述第二冷却通道可以邻近所述前端延伸,并且可以与所述第一冷却通道流体连通。所述第三冷却通道可以邻近所述后端延伸,并且可以与所述第一冷却通道流体连通。(The shroud may also include a cooling channel extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the cooling channel to the cooling chamber.)

1, a turbine shroud (100) coupled to a turbine housing (36) of a turbine system (10), the turbine shroud (100) comprising:

a unitary body (106) comprising:

a front end (108);

a rear end (110) located opposite the front end (108);

an outer surface (120) facing a cooling chamber (122) formed between the unitary body (106) and the turbine housing (36); and

an inner surface (124) facing a hot gas Flow Path (FP) for the turbine system (10);

an th cooling channel (130), the th cooling channel extending within the monolithic body (106), the th cooling channel (130) including a forward portion (134) positioned adjacent the forward end (108) of the monolithic body (106), an aft portion (136) positioned adjacent the aft end (110) of the monolithic body (106), and a central portion (132) positioned between the forward portion (134) and the aft portion (136);

a plurality of impingement openings (138) formed through the outer surface (120) of the monolithic body (106) to fluidly couple the -th cooling channel (130) to the cooling chamber (122), and

at least of the following:

a second cooling channel (142) extending within the monolithic body (106) adjacent the front end (108), the second cooling channel (142) in fluid communication with the -th cooling channel (130), or

A third cooling passage (152) extending within the monolithic body (106) adjacent the aft end (110), the third cooling passage (152) in fluid communication with the -th cooling passage (130).

2. The turbine shroud (100) of claim 1, wherein the unitary body (106) further includes a plurality of support pins (140) positioned within the -th cooling channel (130).

3. The turbine shroud (100) of claim 1, wherein the unitary body (106) further comprises at least of:

a th rib (144), the th rib formed adjacent to the front end (108), the th rib (144) positioned between the th cooling channel (130) and the second cooling channel (142) and separating the th cooling channel from the second cooling channel, or

A second rib (154) formed adjacent to the aft end (110), the second rib (154) positioned between the -th cooling channel (130) and the third cooling channel (152) and separating the -th cooling channel from the third cooling channel.

4. The turbine shroud (100) of claim 3, wherein the unitary body (106) further includes at least of:

a fourth plurality of impingement holes (146) , the fourth plurality of impingement holes formed through the third rib (144), the fourth plurality of impingement holes (146) fluidly coupling the third cooling channel (130) and the second cooling channel (142), or

A second plurality of impingement holes (156) formed through the second rib (154), the second plurality of impingement holes (156) fluidly coupling the -th cooling channel (130) and the third cooling channel (152).

5. The turbine shroud (100) of claim 1, wherein the unitary body (106) further comprises at least of:

an th plurality of support pins (148) positioned within the second cooling channel (142) or the th plurality of support pins

A second plurality of support pins (158) positioned within the third cooling channel (152).

6. The turbine shroud (100) of claim 1, wherein the -th cooling channel (130) further comprises:

a fourth cooling channel wall (162), the fourth cooling channel wall extending between two opposing sides (112,118) of the monolithic body (106), the fourth cooling channel wall (162) being positioned within the fourth cooling channel (130) and extending parallel to the front end (108) and the rear end (110).

7. The turbine shroud (100) of claim 6 wherein the -th cooling channel (130) includes:

a front section (164) formed between the front end (108) of the monolithic body (106) and the -th cooling channel wall (162), and

a rear section (166) formed between the rear end (110) of the monolithic body (106) and the cooling channel wall (162).

8. The turbine shroud (100) of claim 1, wherein the -th cooling channel (130) further comprises:

an th cooling channel wall (162), the th cooling channel wall extending between two opposing sides (112,118) of the monolithic body (106), the th cooling channel wall (162) being positioned within the th cooling channel (130) and extending parallel to the front end (108) and the rear end (110), and

a second cooling channel wall (168) extending parallel to the two opposing sides (112,118) of the monolithic body (106) between the front end (108) and the rear end (110), the second cooling channel wall (168) positioned within the -th cooling channel (130) and extending perpendicular to the -th cooling channel wall (162).

9. The turbine shroud (100) of claim 8, wherein the -th cooling channel (130) includes:

an th front section (170), the th front section being formed between the front end (108) and the th cooling channel wall (162), the th front section (170) being formed between the th side (112) of the two opposing sides of the monolithic body (106) and the second cooling channel wall (168);

a second forward section (172) formed between the forward end (108) and the second cooling channel wall (162), the second forward section (172) formed between the second of the two opposing sides (118) of the monolithic body (106) and the second cooling channel wall (168);

a th aft section (166) formed between the aft end (110) and the th cooling channel wall (162), the th aft section (166) formed between the nd side (112) of the two opposing sides and the second cooling channel wall (168), and

a second aft section (176) formed between the aft end (110) and the -th cooling channel wall (162), the second aft section (176) formed between the second of the two opposing sides (118) and the second cooling channel wall (168).

10. The turbine shroud (100) of claim 1, further comprising:

an th exhaust vent (150), the th exhaust vent in fluid communication with of the th cooling channel (130) or the second cooling channel (142),

wherein the th vent hole (150) extends through of:

the front end (108) of the unitary body (106), or

The inner surface (124) of the unitary body (106).

11. The turbine shroud (100) of claim 10, further comprising:

a second vent (160) in fluid communication with of the th cooling channel (130) or the third cooling channel (152),

wherein the second vent hole (160) extends through of:

the rear end (110) of the unitary body (106), or

The inner surface (124) of the unitary body (106).

12, a turbine system (10), comprising:

a turbine housing (36); and

an th stage, the th stage positioned within the turbine housing (36), the th stage comprising:

a plurality of turbine blades (38) positioned within the turbine housing (36) and circumferentially surrounding a rotor (30);

a plurality of stator vanes (40) positioned within the turbine housing (36) downstream of the plurality of turbine blades (38); and

a plurality of turbine shrouds (100) positioned radially adjacent to the plurality of turbine blades (38) and upstream of the plurality of stator vanes (40), each of the plurality of turbine shrouds (100) including:

a unitary body (106) comprising:

a front end (108);

a rear end (110) located opposite the front end (108);

an outer surface (120) facing a cooling chamber (122) formed between the unitary body (106) and the turbine housing (36); and

an inner surface (124) facing a hot gas Flow Path (FP) for the turbine system (10);

an th cooling channel (130), the th cooling channel extending within the monolithic body (106), the th cooling channel (130) including a forward portion (134) positioned adjacent the forward end (108) of the monolithic body (106), an aft portion (136) positioned adjacent the aft end (110) of the monolithic body (106), and a central portion (132) positioned between the forward portion (134) and the aft portion (136);

a plurality of impingement openings (138) formed through the outer surface (120) of the monolithic body (106) to fluidly couple the -th cooling channel (130) to the cooling chamber (122), and

at least of the following:

a second cooling channel (142) extending within the monolithic body (106) adjacent the front end (108), the second cooling channel (142) in fluid communication with the -th cooling channel (130), or

A third cooling passage (152) extending within the monolithic body (106) adjacent the aft end (110), the third cooling passage (152) in fluid communication with the -th cooling passage (130).

13. The turbine system (10) of claim 12, wherein the cooling passages (130) of each turbine shrouds in the plurality of turbine shrouds (100) further include at least of:

a th cooling channel wall (162), the th cooling channel wall extending between two opposing sides of the monolithic body (106), the th cooling channel wall (162) being positioned within the th cooling channel (130) and extending parallel to the front end (108) and the rear end (110), or

A second cooling channel wall (168) extending parallel to the two opposing sides of the monolithic body (106) between the front end (108) and the rear end (110), the second cooling channel wall (168) positioned within the -th cooling channel (130) and extending perpendicular to the -th cooling channel wall (162).

14. The turbomachinery system (10) of claim 13, wherein each turbine shrouds (100) of the plurality further comprises at least of:

a third cooling channel wall (186) positioned within the second cooling channel (142) and extending parallel to the two opposing sides of the monolithic body (106), or

A fourth cooling channel wall (188) positioned within the third cooling channel (152) and extending parallel to the two opposing sides of the monolithic body (106).

15. The turbomachinery system (10) of claim 12, wherein said aft portion (136) of said cooling channel (130) formed in said monolithic body (106) comprises a substantially serpentine pattern (194).

Background

The present disclosure relates generally to turbine shrouds for turbine systems and, more particularly, to a unitary, body-style turbine shroud including a plurality of cooling passages formed therein.

denier compressed, the inlet air mixed with fuel to form combustion products that may 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 turbine shroud may be exposed to high temperature operating fluid flowing through the turbine components during operation.

To minimize thermal expansion, the turbine shroud is typically cooled. Conventional processes for cooling turbine shrouds include film cooling and impingement cooling. Film cooling involves the process of flowing cooling air over the surface of the turbine shroud during operation of the turbine components. Impingement cooling utilizes holes or apertures formed through the turbine shroud to provide cooling air to various portions of the turbine shroud during operation.

Additionally, to form impingement holes or orifices through various portions of the turbine shroud, the turbine shroud must be formed from multiple pieces that must be assembled and/or secured together at prior to installation into the turbine component.

Disclosure of Invention

A th aspect of the present disclosure provides a turbine shroud coupled to a turbine housing of a turbine system, the turbine shroud including a unitary body including a forward end, an aft end positioned opposite the forward end, an outer surface facing a cooling chamber formed between the unitary body and the turbine housing, and an inner surface facing a hot gas flow path for the turbine system, a cooling channel extending within the unitary body, the cooling channel including a forward portion positioned adjacent the forward end of the unitary body, an aft portion positioned adjacent the aft end of the unitary body, and a central portion positioned between the forward and aft portions, a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the cooling channel to the cooling chamber, and at least of a second cooling channel extending within the unitary body adjacent the forward end, the second cooling channel in fluid communication with the cooling channel, or a third cooling channel extending within the unitary body adjacent the aft end, the third cooling channel in fluid communication with .

A second aspect of the present disclosure provides a turbine system including a turbine housing, and a stage located within the turbine housing, the stage including a plurality of turbine blades located within the turbine housing and circumferentially surrounding a rotor, a plurality of stator blades located within the turbine housing downstream of the plurality of turbine blades, and a plurality of turbine shrouds located radially adjacent to the plurality of turbine blades and upstream of the plurality of stator blades, each of the plurality of turbine shrouds including a unitary body including a forward end, an aft end located opposite the forward end, an outer surface facing a cooling chamber formed between the unitary body and the turbine housing, and an inner surface facing a hot gas flow path for the turbine system, a cooling channel extending within the unitary body, the cooling channel including a forward portion located adjacent to the forward end of the unitary body, an aft portion located adjacent to the aft body, and a third portion located adjacent to the aft end, and a second portion located adjacent to the aft end, and a third portion located adjacent to the forward end, and a second portion located adjacent to the aft end, and a third portion located adjacent to the aft end, the second portion located adjacent to the second portion of the cooling channel .

Exemplary aspects of the present disclosure are designed to solve the problems herein described and/or other problems not discussed.

Drawings

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 depict various embodiments of the disclosure, in which:

FIG. 1 shows a schematic view of a gas turbine system according to an embodiment of the present disclosure.

FIG. 2 illustrates a side view of portion of a turbine of the gas turbine system of FIG. 1, the turbine including turbine blades, stator vanes, a rotor, a casing, and a turbine shroud, according to an embodiment of the present disclosure.

FIG. 3 illustrates an isometric view of the turbine shroud of FIG. 2, according to an embodiment of the present disclosure.

FIG. 4 illustrates a top view of the turbine shroud of FIG. 3, according to an embodiment of the present disclosure.

FIG. 5 illustrates a side view of the turbine shroud of FIG. 3, according to an embodiment of the present disclosure.

FIG. 6 illustrates a cross-sectional side view of the turbine shroud taken along line 6-6 in FIG. 4, according to an embodiment of the present disclosure.

FIG. 7 illustrates a top view of a turbine shroud including cooling passage walls according to additional embodiments of the present disclosure.

FIG. 8 illustrates a cross-sectional side view of the turbine shroud taken along line 8-8 in FIG. 7, according to additional embodiments of the present disclosure.

FIG. 9 illustrates a top view of a turbine shroud including two cooling passage walls according to further embodiments of the present disclosure.

FIG. 10 illustrates a cross-sectional side view of a turbine shroud taken along line 10-10 in FIG. 9, according to further embodiments of the present disclosure.

FIG. 11 shows a top view of a turbine shroud including two cooling passage walls according to another embodiments of the present disclosure.

FIG. 12 illustrates a top view of a turbine shroud including cooling passage walls according to further embodiments of the present disclosure.

FIG. 13 illustrates a cross-sectional side view of a turbine shroud taken along line 13-13 in FIG. 12, according to further embodiments of the present disclosure.

FIG. 14 illustrates a cross-sectional side view of the turbine shroud of FIG. 4, according to additional embodiments of the present disclosure.

FIG. 15 illustrates a cross-sectional side view of the turbine shroud of FIG. 4, according to further embodiments of the present disclosure.

FIG. 16 shows a cross-sectional side view of the turbine shroud of FIG. 4 in accordance with another embodiments of the present disclosure.

FIG. 17 illustrates a top view of a turbine shroud according to other embodiments of the present disclosure.

FIG. 18 illustrates a cross-sectional side view of a turbine shroud taken along line 18-18 in FIG. 17, according to other embodiments of the present disclosure.

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 disclosure, and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbering represents like elements between the drawings.

Detailed Description

As an initial matter, in order to clearly describe the present disclosure, it will be necessary to select certain terms when referring to and describing relevant machine components within the scope of the present disclosure, in doing so, common industry terms will be used and employed in a manner consistent with their accepted meaning .

As used herein, "downstream" and "upstream" refer to a direction opposite to flow, without any specificity of advancing , the terms "forward" and "aft" refer to directions where "forward" refers to a forward end or a compressor end of the engine, and "aft" refers to an aft end or a turbine end of the engine, additionally, the terms "forward" and "aft" may be used and/or understood, respectively, as describing similar to the terms "forward" and "aft" in a description, generally requiring that the terms "forward" and "aft" refer to a portion at different radial, axial, and/or radial positions, and that the terms "forward" and "aft" refer to a position in a direction (e.g., substantially perpendicular to the axial direction, such as along the axial direction, and/or radial axis, such as along the axial direction, such as about axis 631).

As described above, the present disclosure provides a turbine shroud for a turbine system, and more particularly, an integral, body-style turbine shroud including a plurality of cooling passages formed therein.

These and other embodiments are discussed below with reference to fig. 1-18. However, those skilled in the art will readily appreciate that the detailed description given herein with respect to these figures is for explanatory purposes only and should not be construed as limiting.

FIG. 1 illustrates a schematic view of an exemplary gas turbine system 10. The gas turbine system 10 may include a compressor 12. The compressor 12 compresses an incoming flow of air 18. The compressor 12 delivers a flow of compressed air 20 to a combustor 22. The combustor 22 mixes the compressed flow of air 20 with a flow of pressurized fuel 24 and ignites the mixture to generate a flow of combustion gases 26. Although only a single combustor 22 is shown, the gas turbine system 10 may include any number of combustors 22. The combustion gas stream 26 is, in turn, delivered to a turbine 28, which typically includes a plurality of turbine blades, including airfoils (see FIG. 2) and stator vanes (see FIG. 2). The flow of combustion gases 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 may be used to drive an external load 32 (such as an electrical generator or the like).

The gas turbine system 10 may 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 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, the portion (e.g., the outer casing) of the exhaust frame 34 may be coupled directly to the outer shell, casing, or casing 36 of the turbine 28.

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

Turning to fig. 2, portion of turbine 28 is shown, specifically, fig. 2 shows a side view of the portion of turbine 28, including the st stage of turbine blades 38( is shown), and the th stage of stator blades 40( is shown) coupled to the casing 36 of turbine 28 as discussed herein, each stage of turbine blades 38 (e.g., the st stage, the second stage (not shown), the third stage (not shown)) may include a plurality of turbine blades 38 that may be coupled to and positioned circumferentially around the rotor 30 and may be driven by combustion gases 26 to rotate the rotor 30. additionally, each stage of stator blades 40 (e.g., the 734 th stage, the second stage (not shown), the third stage (not shown)) may include a plurality of stator blades 38 that may be coupled to and positioned circumferentially around the casing 36 of turbine 28 and may include a plurality of stator vanes 42 that may be positioned adjacent to each other stage of turbine blades 38 in the axial direction of turbine blades 38. although not shown, the turbine blades 38 may include a plurality of turbine blades 38 positioned axially adjacent to each other stage of turbine blades 38 and vanes 40, the turbine blades 38 may include only a stator blades 38 positioned axially adjacent to the stator blades 38 and/or a stator blades 38. the turbine blades of turbine blades 38 may include only a stator blade 12, which are positioned adjacent to each other stage of turbine blades 30, and may be positioned within the turbine blades of turbine blades 30.

The turbine 28 (see FIG. 1) of the gas turbine system 10 may also include a plurality of turbine shrouds 100. for example, the turbine 28 may include the th stage of the turbine shroud 100( shown). The th stage of the turbine shroud 100 may correspond to the th stage of the turbine blades 38 and/or the th stage of the stator blades 40. that is, and as discussed herein, the th stage of the turbine shroud 100 may be positioned within the turbine 28 adjacent the th stage of the turbine blades 38 and/or the th stage of the stator blades 40 to interact with and provide a seal within the Flow Path (FP) of the combustion gases 26 flowing through the turbine 28. in the non-limiting example shown in FIG. 2, the th stage of the turbine shroud 100 may be positioned radially adjacent the th stage of the turbine blades 38 and/or may substantially surround or encircle the th stage.

Similar to the stator blades 40, the th stage of the turbine shroud 100 may include a plurality of turbine shrouds 100 that may be coupled to and positioned circumferentially around the casing 36 of the turbine 28. in the non-limiting example shown in FIG. 2, the turbine shroud 100 may be coupled to the casing 36 via coupling members 48 that extend radially inward from the casing 36 of the turbine 28. in the non-limiting example, the coupling members 48 may be configured to couple to and/or receive fasteners or hooks 102, 104 (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 another non-limiting example (not shown), the coupling members 48 may be formed with the casing 36 for coupling, positioning, and/or securing the turbine shroud 100 to the casing 36. similar to the turbine blades 38 and/or the stator blades 40, although only a portion of the th stage of the turbine shroud 100 of the turbine 28 is shown in FIG. 2, the turbine shroud 28 may include multiple stages of the turbine shroud 100 positioned axially over the entire turbine shroud 36.

Turning to fig. 3-6, various views of a turbine shroud 100 for a turbine 28 of the gas turbine system 10 of fig. 1 are illustrated. Specifically, fig. 3 illustrates an isometric view of the turbine shroud 100, fig. 4 illustrates a top view of the turbine shroud 100, fig. 5 illustrates a side view of the turbine shroud 100, and fig. 6 illustrates a cross-sectional side view of the turbine shroud 100.

3-6, because the turbine shroud 100 is formed from the unitary body 106, the turbine shroud 100 may not require the construction, engagement, coupling, and/or assembly of various parts to completely form the turbine shroud 100, and/or may not require the construction, engagement, coupling, and/or assembly of various parts (see FIG. 2) before the turbine shroud 100 may be installed and/or implemented within the turbine system 10 (as discussed herein). conversely, once the single, continuous, and/or non-disjointed unitary body 106 for the turbine shroud 100 is constructed, the turbine shroud 100 may be installed immediately within the turbine system 10 as .

The unitary body 106 of the turbine shroud 100, as well as various components and/or features of the turbine shroud 100, may be formed using any suitable additive manufacturing process and/or method. For example, the turbine shroud 100 including the unitary body 106 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 unitary body 106 of the turbine shroud 100 may be formed of any material that may be utilized by an additive manufacturing process to form the turbine shroud 100, and/or that is capable of withstanding the operational characteristics (e.g., exposure temperature, exposure pressure, etc.) experienced by the turbine shroud 100 within the gas turbine system 10 during operation.

For example, and as shown in FIGS. 3 and 4, the overall body 106 of the turbine shroud 100 may include a forward end 108 and an aft end 110 positioned opposite the forward end 108. the forward end 108 may be positioned upstream of the aft end 110 such that combustion gases 26 flowing through a Flow Path (FP) defined within the turbine 28 may flow through the adjacent forward end 108 before flowing through the adjacent aft end 110 of the overall body 106 of the turbine shroud 100. As shown in FIGS. 3 and 4, the forward end 108 may include a hook 102 configured to couple to and/or engage a coupling member 48 of the casing 36 of the turbine 28 to couple, position, and/or secure the turbine shroud 100 within the casing 36 (see FIG. 2). Inaddition, the aft end 110 may include a second hook 104 positioned opposite the hook 102 and/or formed on the overall body 106. similar to the second hook 102, the second hook 104 may be configured to couple to and/or engage the casing 36 of the turbine 28 to secure the shroud 100 within the casing 36 (see FIG. 2).

Additionally, the unitary body 106 of the turbine shroud 100 may also include a side 112 and a second side 118 located opposite the side 112 as shown in FIGS. 3 and 4, each of the side 112 and the second side 118 may extend and/or be formed between the forward end 108 and the aft end 110. turning briefly to FIG. 5, the side 112 and the second side 118 (not shown) of the unitary body 106 may be substantially closed and/or may include solid endwalls or caps. likewise, and as discussed herein, the solid endwalls of the side 112 and the second side 118 may substantially prevent fluids (e.g., combustion gases 26, cooling fluids) within the turbine 28 from entering the turbine shroud 100 and/or from exiting internal portions (e.g., passages) formed within the turbine shroud 100.

3-5, the unitary body 106 of the turbine shroud 100 may also include an outer surface 120. the outer surface 120 may face a cooling chamber 122 (see FIG. 2) formed between the unitary body 106 and the turbine casing 36. more specifically, the outer surface 120 may be positioned, formed, facing, and/or directly exposed in the cooling chamber 122 formed between the unitary body 106 of the turbine shroud 100 and the turbine casing 36 of the turbine 28. As discussed herein, the cooling chamber 122 formed between the unitary body 106 of the turbine shroud 100 and the turbine casing 36 may receive 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 unitary body 106 of the turbine shroud 100 may also be formed and/or positioned between the forward end 106 and the aft end 108, and the side 112 and the second side 118, respectively.

Returning briefly to FIG. 2, and with continued reference to FIGS. 3 and 5, the inner surface 124 may face a hot gas Flow Path (FP) (see FIG. 2) of the combustion gases 26 flowing through the turbine 28. more specifically, the inner surface 124 may be positioned, formed, facing, and/or directly exposed to a 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, as shown in FIG. 2, the inner surface 124 of the unitary body 106 of the turbine shroud 100 may be positioned radially adjacent to the hot gas Flow Path (FP) of the airfoil 42. in addition to facing the hot gas Flow Path (FP) of the combustion gases 26, and similar to the outer surface 120, the inner surface 124 of the unitary body 106 of the turbine shroud 100 may also be positioned between the forward end 106 and the aft end 108, and between the second side side and the second side 89112 and/or tip portion 118, respectively.

Turning to FIG. 6, with continued reference to FIGS. 3-5, additional features of the turbine shroud 100 are now discussed.the turbine shroud 100 may include a base portion 126. As shown in FIG. 6, the base portion 126 may be formed as a body portion of the unitary body 106 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 unitary body 106 of the turbine shroud 100. additionally, the base portion 126 of the unitary body 106 of the turbine shroud 100 may be formed, positioned, and/or extended between the side 112 and the second side 118, respectively, the base portion 126 may be formed with solid sidewalls formed on the side 112 and the second side 118 of the unitary body 106. in a non-limiting example, the base portion 126 of the unitary body 106 of the turbine shroud 100 may have a thickness of between about 1.25 millimeters (mm) (0.05 inches (in)) and about 6.35mm (0.25 in.) As discussed herein, the shroud 100 may at least partially define a cooling channel for the turbine shroud 100 and/or the base portion.

The turbine shroud 100 may include an impingement portion 128 similar to the base portion 126, as shown in FIG. 6, the impingement portion 128 may be formed as an body portion of the unitary body 106 of the turbine shroud 100. the impingement portion 128 may include an outer surface 120, and/or the outer surface 120 may be formed on the impingement portion 128 of the unitary body 106 of the turbine shroud 100. the impingement portion 128 of the unitary body 106 of the turbine shroud 100 may be formed, positioned and/or extended between the forward end 106 and the aft end 108, and between the side 112 and the second side 118, respectively. additionally, and also similar to the base portion 126, the impingement portion 128 may be formed with solid sidewalls formed on the side 112 and the second side 118 of the unitary body 106. in the non-limiting example where the turbine shroud 100 is formed as a unitary body 106, the impingement portion 128 may have a thickness of between about 1.25mm (0.05in) and about 6.35mm (0.25 in.) As discussed herein, the impingement portion 128 of the turbine shroud 100 along with the base portion 126 may at least partially define at least one cooling channel within the turbine shroud 100.

The turbine shroud 100 may also include a plurality of cooling channels formed therein for cooling the turbine shroud 100 during operation of the turbine 28 of the gas turbine system 10, as shown in FIG. 6, the turbine shroud 100 may include a th cooling channel 130 formed, positioned and/or extending within the unitary body 106 of the turbine shroud 100. more specifically, and briefly returning to FIG. 4, a th cooling channel 130 (shown in phantom in FIG. 4) of the turbine shroud 100 may extend within the unitary body 106 between and/or adjacent the forward end 108, the aft end 110, the th side 112 and the second side 118, respectively.

For example, fourth cooling passage 130 may include a central portion 132 positioned and/or extending between forward portion 134 and aft portion 136. As shown in FIG. 6, central portion 132 of fourth cooling passage 130 may be formed and/or positioned centrally between forward end 108 and aft end 110 of overall body 106 of turbine shroud 100. forward portion 134 of fifth cooling passage 130 may be formed and/or positioned directly adjacent to forward end 108 of overall body 106 of turbine shroud 100 and axially adjacent to central portion 132 and/or axially upstream thereof. similarly, aft portion 136 of 4624 th cooling passage 130 may be formed and/or positioned directly adjacent to aft end 110 of overall body 106, opposite forward portion 134. additionally, aft portion 136 may be formed axially adjacent to central portion 132 and/or axially downstream thereof. in the non-limiting example shown in FIG. 6, portions 132, 134 of fifth cooling passage 130 may include a plurality of different sections, segments, and/or portions of radial openings 132, and/or radial openings 134 may include a radial height of a radial opening 134 of a second cooling passage 130, 134, a radial opening 134 may include a radial height of a radial opening 134, a radial opening 134 of a radial opening 134, or a radial opening 134 that may vary from a radial height of forward portion 134 to a radial opening 134 and/or radial opening 134 of a radial opening 134 that of shroud portion 134 that of overall body 106 and/or aft portion 134 that may include a radial opening 134 that varies from a radial height of a radial opening 134 that of turbine shroud 100 or that of a radial opening 134 that of a shroud 100 that is greater than a radial opening 134 that of shroud 100 or that of a radial opening 134 that of shroud 100 or that of a radial opening 134 that may include a radial opening 134 that of a radial opening 134 that is greater than that of shroud 100 and/or that of a radial opening 134 that of a radial portion 134 that is greater than that of a radial opening 134 that may include, or that is greater than that of a.

To provide cooling fluid to the -th cooling passage 130, the turbine shroud 100 may further include a plurality of impingement openings 138 formed therethrough. that is, and as shown in FIG. 6, the turbine shroud 100 may include a plurality of impingement openings 138 formed through the outer surface 120 (and more specifically the impingement portion 128) of the unitary body 106. the plurality of impingement openings 138 formed through the outer surface 120 and/or the impingement portion 128 may fluidly couple the cooling plenum 122 and the -th cooling passage 130. during operation of the gas turbine system 10 (see FIG. 1), as discussed herein, cooling fluid flowing through the cooling plenum 122 may pass through or flow through the plurality of impingement openings 138 to the -th cooling passage 130 to substantially cool the turbine shroud 100.

It should be appreciated that the size, shape, and/or number of impingement openings 138 formed through the outer surface 120 and/or the impingement portion 128, as shown in FIG. 6, is merely exemplary. As such, the turbine shroud 100 may include larger or smaller impingement openings 138, and/or may include more or fewer impingement openings 138 formed therein. additionally, although the size and/or shape of the plurality of impingement openings 138 is shown as substantially uniform, it should be understood that each of the plurality of impingement openings 138 formed on the turbine shroud 100 may include a different size and/or shape.

Additionally, as shown in FIG. 6, the monolithic body 106 of the turbine shroud 100 may further include a plurality of support pins 140. the plurality of support pins 140 may be positioned within the th cooling channel 130. more specifically, each of the plurality of support pins 140 may be positioned within the th cooling channel 130 and may extend between and/or form with the base portion 126 and the impingement portion of the monolithic body 106. in a non-limiting example, the plurality of support pins 140 may be formed and/or positioned within the central portion 132 of the th cooling channel 130. however, it should be understood that the plurality of support pins 140 may also be positioned within different portions (e.g., the forward portion 134, the aft portion 136) of the th cooling channel 130. the plurality of support pins 140 may be positioned throughout the th cooling channel 130 to provide support, structural and/or rigid support to both the base portion 126 and the impingement portion 128 when the turbine shroud portion 126 and the impingement portion 128 are positioned with a thickness of both about 1.25mm (0.in) and impingement portion 128, and/or may include additional cooling support pins 140, or impingement openings between the impingement portions of the impingement base portion 128 and/or impingement support pins 140, and/or impingement portions 128 when the impingement support pins 140 may be positioned with the turbine base portion 128 in a non-included in-cooling channel 100, or impingement-included in-a non-impingement-cooling channel-forming process such as discussed herein, and/or impingement-included-in-included-in-or-included-in-included-in-working.

As shown in FIG. 6, the size, shape, and/or number of support pins 140 positioned within the cooling channel 130 is merely exemplary.

In addition to the -th cooling channel 130, the turbine shroud 100 may also include a second cooling channel 142. the second cooling channel 142 may be formed, positioned, and/or extend within the unitary body 106 of the turbine shroud 100 adjacent the forward end 108. the second cooling channel 142 may also be formed and/or extend within the unitary body 106 adjacent the forward end 108 of the unitary body 106 between the -th side 112 and the second side 118, respectively.

The second cooling channel 142 may also be separated from the forward portion 134 of the cooling channel 130 by an th rib 144. that is, and as shown in FIG. 6, a 0 th rib 144 may be formed between the th and second cooling channels 130, 142 and may separate the th and second cooling channels th rib 144 may be formed with the unitary body 106 of the turbine shroud 100 and may be formed adjacent the forward end 108 of the turbine shroud 100. additionally, the th rib 144 may extend within the unitary body 106 between the th and second sides 112,118 and may be formed with the solid sidewalls formed on the th and second sides 112,118 of the unitary body 106.

The second cooling channel 142 of the turbine shroud 100 may also be in fluid communication with and/or fluidly coupled to the -th cooling channel 130 of the turbine shroud 100. for example, the overall body 106 of the turbine shroud 100 may include a -th plurality of impingement holes 146 formed through a -th rib 144. the -th plurality of impingement holes 146 formed through a -th rib 144 may fluidly couple the -th cooling channel 130 (and more specifically the forward portion 134) and the second cooling channel 142. during operation of the gas turbine system 10 (see FIG. 1), cooling fluid flowing through the forward portion 134 of the -th cooling channel 130 may pass through or flow through the plurality of impingement holes 146 to the second cooling channel 142 to substantially cool the turbine shroud 100, as discussed herein.

As shown in FIG. 6, the size, shape, and/or number of impingement holes 146 formed by the -th rib 144 is merely exemplary, as such, the turbine shroud 100 may include larger or smaller impingement holes 146, different sized impingement holes 146, and/or may include more or fewer impingement holes 146 formed therein similar to the impingement openings 138 formed by the outer surface 120/impingement portion 128, the size, shape, and/or number of impingement holes 146 formed by the -th rib 144 may depend at least in part on the operational characteristics of the gas turbine system 10 during operation, and/or the characteristics of the turbine shroud 100/second cooling passage 142.

Similar to the cooling channel 130, the second cooling channel 142 may also include a th plurality of support pins 148. that is, the monolithic body 106 of the turbine shroud 100 may include a th plurality of support pins 148 positioned within the second cooling channel 142. the th plurality of support pins 148 may extend between and/or may be formed with the base portion 126 and the th rib 144 of the monolithic body 106 similar to the support pins 140 positioned within the th cooling channel 130, the th plurality of support pins 148 positioned within the second cooling channel 142 may provide support, structure, and/or rigidity to both the base portion 126 and the th ribs 144 of the monolithic body 106, and may also assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see illustrative 1.) also similar to 140, when using any suitable additive manufacturing process and/or method to form the monolithic body 106 of the turbine shroud 100, the th plurality of support pins 148 may be positioned with the base portion 126 and/or the th cooling channel 142, and the cooling channel 142 may be sized and/or the number of support pins 148 may be determined by the size of the cooling channel 142.

As also shown in FIG. 6, the turbine shroud 100 may include a th vent 150. the th vent 150 may be in fluid communication with the second cooling channel 142. more specifically, the th vent 150 may be in fluid communication with and may extend axially from the second cooling channel 142. in the non-limiting example shown in FIG. 6, the th vent 150 may extend from the second cooling channel 142 to the forward end 108 of the turbine shroud 100 through the monolithic body 106. in addition to being in fluid communication with the second cooling channel 142, the th vent 150 may be in fluid communication with a hot gas Flow Path (FP) for the turbine 28 (see FIG. 2.) as such, the th vent 150 may fluidly couple the second cooling channel 142 and the hot gas Flow Path (FP) for the turbine 28. during operation, and as discussed herein, the th vent 150 may be adjacent to the forward end 108 of the turbine shroud 100, vent cooling fluid from the second cooling channel 142 and vent its combustion gases 26 to the turbine 28 through the non-linear Flow Path (FP). although the second vent 150 may be shown and/or formed as a non-linear cooling channel, the second vent 150 may be formed in a non-linear cooling channel, a non-linear cooling channel may be formed with the non-linear cooling channel 100, a non-linear cooling channel may be understood, a non-linear cooling channel, a non-linear exhaust port, a cooling channel, including a non-linear exhaust port, a.

Also in the non-limiting example shown in FIG. 6, the turbine shroud 100 may further include a third cooling passage 152. the third cooling passage 152 may be formed, positioned, and/or extend within the unitary body 106 of the turbine shroud 100. that is, the third cooling passage 152 may extend within the unitary body 106 of the turbine shroud 100 adjacent the aft end 110. the third cooling passage 152 may also be formed and/or extend within the unitary body 106 adjacent the aft end 110 of the unitary body 106 between the side 112 and the second side 118, respectively.

The third cooling channel 152 may also be separated from the aft portion 136 of the th cooling channel 130 by a second rib 154. that is, and as shown in FIG. 6, the second rib 154 may be formed between the th and third cooling channels 130, 152 and may separate the th and third cooling channels. the second rib 154 may be formed with the unitary body 106 of the turbine shroud 100 and may be formed adjacent the aft end 110 of the turbine shroud 100. additionally, the second rib 154 may extend within the unitary body 106 between the th side 112 and the second side 118 and may be formed with the solid side walls formed on the th side 112 and the second side 118 of the unitary body 106.

The third cooling channel 152 of the turbine shroud 100 may also be in fluid communication with and/or fluidly coupled to the -th cooling channel 130 of the turbine shroud 100. for example, the unitary body 106 of the turbine shroud 100 may include a second plurality of impingement holes 156 formed through the second ribs 154. the second plurality of impingement holes 156 formed through the second ribs 154 may fluidly couple the -th cooling channel 130 (and more specifically the aft portion 136) and the third cooling channel 152. during operation of the gas turbine system 10 (see FIG. 1), as discussed herein, cooling fluid flowing through the aft portion 136 of the -th cooling channel 130 may pass through or flow through the second plurality of impingement holes 156 to the third cooling channel 152 to substantially cool the turbine shroud 100. similar to the -th plurality of impingement holes 146, as shown in FIG. 6, exemplary impingement holes 156 formed through the second ribs 154 are merely sized, shaped, and/or numbered, and may depend at least in part on operational characteristics of the gas turbine system 10 during operation and/or characteristics of the third cooling channel 100/152.

Similar to the third cooling channel 130, the third cooling channel 152 may also include a second plurality of support pins 158, that is, the monolithic body 106 of the turbine shroud 100 may include a second plurality of support pins 158 positioned within the third cooling channel 152. the second plurality of support pins 158 may extend between and/or may be formed with the base portion 126 and the second ribs , respectively, of the monolithic body 106 similar to the third plurality of support pins 148 positioned within the second cooling channel 142, the second plurality of support pins 158 positioned within the third cooling channel 152 may provide support, structure, and/or rigidity to both the base portion 126 and the second ribs 154 of the monolithic body 106, and may also assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see FIG. 1). also similar to the exemplary plurality of support pins 148, when any suitable additive manufacturing process and/or method is used to form the monolithic body 106 of the turbine shroud 100, the second plurality of support pins 158 and/or ribs 158 may be formed with the base portion 126 and/or second cooling channel 158 in the size of the turbine shroud 100 and/or the size of the cooling channel 158.

As also shown in FIG. 6, the turbine shroud 100 may include a second exhaust vent 160. the second exhaust vent 160 may be in fluid communication with the third cooling passage 152. more specifically, the second exhaust vent 160 may be in fluid communication with and may extend from the third cooling passage 152 of the turbine shroud 100. As shown in FIG. 6, the second exhaust vent 160 may extend axially from the third cooling passage 152 to the aft end 110 of the turbine shroud 100. similarly to the exhaust vent 150, the second exhaust vent 160 may also be in fluid communication with a hot gas Flow Path (FP) for the turbine 28 (see FIG. 2.) thus, the second exhaust vent 160 may fluidly couple the third cooling passage 152 and the hot gas Flow Path (FP) for the turbine 28. As discussed herein, the second exhaust vent 160 may be adjacent the aft end 110 of the turbine shroud 100, exhaust cooling fluid from the third cooling passage 152 and exhaust it into the hot gas Flow Path (FP) of the combustion gases 26 flowing through the turbine 28. although a single exhaust vent is shown in FIG. 6, it should be appreciated that the turbine shroud 106 may include multiple exhaust vents formed in substantially linear flow communication with the second exhaust vent 160 and/or non-linear cooling passages, and that the second exhaust vent 160 may be formed as non-linear cooling passages.

During operation of the gas turbine system 10 (see FIG. 1), Cooling Fluid (CF) may flow through the monolithic body 106 to cool the turbine shroud 100. more specifically, as the turbine shroud 100 is exposed to combustion gases 26 (see FIG. 2) flowing through a hot gas flow path of the turbine 28 and increases in temperature during operation of the gas turbine system 10, the Cooling Fluid (CF) may be provided to and/or may flow through a plurality of cooling channels 130, 142, 152 formed and/or extending through the monolithic body 106 to cool the turbine shroud 100. with respect to FIG. 6, various arrows may represent and/or may show the flow path of the Cooling Fluid (CF) as it flows through the monolithic body 106 of the turbine shroud 100. in a non-limiting example, the Cooling Fluid (CF) may first flow from the cooling chamber 122 to the cooling channel 130 via a plurality of impingement openings 138 formed through the outer surface 120 and/or impingement portion 128 of the monolithic body 106. the cooling channel 130. the Cooling Fluid (CF) may initially enter the central portion 132 of the cooling channel 130 of the integral body 130 and/or the cooling channel 130 and/or may flow from the cooling channel 130 through the cooling channel 130 located at the axial ends of the cooling channel 130 and/or cooling channel 130 located at the aft portion of the cooling channel 130 and/or portion 130, preferably located at the cooling channel 130/or sink 130, preferably proximate to the cooling channel 130, 140.

Once the Cooling Fluid (CF) has flowed to the opposite portions 134, 136 of the cooling channel 130 and/or the ends 108, 110 of the turbine shroud 100, the Cooling Fluid (CF) may flow to different cooling channels 142, 152 formed and/or extending within the monolithic body 106 of the turbine shroud 100 to continue cooling the turbine shroud 100 and/or receive heat, for example, the portion of the Cooling Fluid (CF) flowing to the forward end 108 and/or the forward portion 134 of the cooling channel 130 may then flow to the second cooling channel 142. the Cooling Fluid (CF) may flow from the forward portion 134 of the cooling channel 130 to the second cooling channel 142 via a th plurality of impingement holes 146 formed through a th rib 144 of the monolithic body 106. once into the second cooling channel 142, the Cooling Fluid (CF) along with a th plurality of support pins 148 positioned within the second cooling channel 142 may continue to cool the turbine shroud 100 and/or receive/receive heat from the turbine shroud 100. from the second cooling channel 100, the Cooling Fluid (CF) may flow through the exhaust holes 142 adjacent to dissipate hot gas flow into the turbine shroud 108, 362, see FIG. hot gas flow path exhaust 362, exhaust holes 142.

Meanwhile, a different portion of the Cooling Fluid (CF) flowing to the aft end 110 and/or the aft portion 136 of the cooling channel 130 may then flow to the third cooling channel 152 the Cooling Fluid (CF) may flow from the aft portion 136 of the cooling channel 130 to the third cooling channel 152 via a second plurality of impingement holes 156 formed through the second ribs 154 of the unitary body 106, upon entering the third cooling channel 152, the Cooling Fluid (CF), along with a second plurality of support pins 158 positioned within the third cooling channel 152, may continue to cool the turbine shroud 100 and/or receive/dissipate heat from the turbine shroud 100. the Cooling Fluid (CF) may then flow through the second exhaust holes 160, exit adjacent the aft end 110, and ultimately flow into the hot gas flow path of the combustion gases 26 flowing through the turbine 28 (see FIG. 2).

FIGS. 7 and 8 show various views of another non-limiting examples of a turbine shroud 100 for a turbine 28 of the gas turbine system 10 of FIG. 1. specifically, FIG. 7 shows a top view of the turbine shroud 100 and FIG. 8 shows a cross-sectional side view of the turbine shroud 100.

In contrast to the non-limiting examples of fig. 3-6, the turbine shroud 100 shown in fig. 7 and 8 may include a fifth exhaust vent 150 and a second exhaust vent 160 formed through different portions of the unitary body 106 for example, and referring to fig. 8, the fifth exhaust vent 150 may be in fluid communication with and may extend from the second cooling channel 142 of the turbine shroud 100 and through the base portion 126. while still positioned substantially adjacent to the forward end 108, the fourth exhaust vent 150 may extend generally radially through the base portion 126 of the unitary body 106 and/or exhaust Cooling Fluid (CF) through the base portion additionally, and as shown in fig. 8, the second exhaust vent 160 may be in fluid communication with and may extend generally radially from the third cooling channel 152 and through the base portion 126. the second exhaust vent 160 may be positioned substantially adjacent to the aft end 110, but similar to the fifth exhaust vent 150, may extend through the base portion 126 of the unitary body 106 and/or through the base portion 152 of the unitary body may flow from the second exhaust vent 160 into a second cooling channel 26 (CF 2) through which the second cooling fluid (CF 2) flows out of the second cooling channel 26).

For example, the turbine shroud 100 may include a th cooling channel wall 162. the th cooling channel wall 162 (shown in phantom in FIG. 7) may include and/or be formed in the 0 th cooling channel 130 and may extend between the side 112 and the second side 118 of the overall body 106 of the turbine shroud 100. additionally, and as shown in FIG. 7, the th cooling channel wall 162 may extend substantially parallel to the forward end 108 and the aft end 110 within the th cooling channel 130. continuing with the non-limiting example shown in FIG. 8, the th cooling channel wall 162 may be formed in the central portion 132 of the th cooling channel 130 and may extend between and/or may be formed with the base portion 126 and the impingement portion , respectively, of the overall body 106. As the overall body 106 of the turbine shroud 100 is formed using any suitable additive manufacturing process and/or method, the th cooling channel wall 162 and the impingement portion 128 may be formed with the base portion 126 and the impingement portion .

As similarly discussed herein with respect to the plurality of support pins 140 positioned within the fourth cooling channel 130, cooling channel wall 162 may be formed in the 0 th cooling channel 130 to assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see FIG. 1). additionally or alternatively, the 1 st cooling channel wall 162 may be formed in the th cooling channel 130 to separate the th cooling channel 130 and/or to assist in directing Cooling Fluid (CF) to the respective portions 134, 136 of the th cooling channel 130 and/or to the ends 108, 110 of the turbine shroud 100 during the cooling processes discussed herein.i.e., the th cooling channel wall 162 may substantially divide the th cooling channel 130 into a forward section 164 and an aft section 166. the forward section 164 of th cooling channel 130 may be formed between the forward end 108 of the unitary body 106 and the th cooling channel wall 162, 638 th cooling channel wall 164 may also include a central portion of the fourth cooling channel 130, a central portion of the fifth cooling channel 130 may be formed between the forward section 108 and the central portion of the integral body 4618, a central portion of the integral cooling channel 130, a central cooling channel 162 may be formed through a central section of the cooling channel 162, a central section of the central cooling channel 130, a central section of the cooling channel 166 of the cooling channel 162 of the cooling channel 130, a central cooling channel 162 of the central cooling channel 130, a central section of the cooling channel 166 of the cooling channel 162 of the integral body 132, a central cooling channel 166, a central section of the integral body 132, a central section of the cooling channel 166, a central section of the integral body 132, a central.

FIGS. 9 and 10 illustrate various views of additional non-limiting examples of a turbine shroud 100 for a turbine 28 of the gas turbine system 10 of FIG. 1. Specifically, fig. 9 shows a top view of the turbine shroud 100, and fig. 10 shows a cross-sectional side view of the turbine shroud 100. It should be appreciated that similarly numbered and/or named components may function in a substantially similar manner. Redundant explanations of these components have been omitted for the sake of clarity.

In the non-limiting example shown in fig. 9 and 10, the turbine shroud 100 may further include a second cooling passage wall 168 (shown in phantom in fig. 9) that may include and/or be formed in the th cooling passage 130 and that may extend axially between the forward end 108 and the aft end 110 of the unitary body 106 of the turbine shroud 100, substantially parallel to the side 112 and the second side 118 additionally, the second cooling passage wall 168 may extend substantially perpendicular to the th cooling passage wall 162 within the th cooling passage 130 turning to fig. 10 and, similar to the th cooling passage wall 162, the second cooling passage wall 168 may extend between the base portion 126 and the impingement portion 128 of the unitary body 106 and/or may be formed with the base portion and the impingement portion , respectively, when the unitary body 106 of the turbine shroud 100 is formed using any suitable additive manufacturing process and/or method, the second cooling passage wall 168 may form the base portion 126 and the impingement portion and the second cooling passage wall 168 of fig. 10 may also extend through the forward portion and/or the aft portion 136 of the cooling passage wall 134.

As similarly discussed herein with respect to a plurality of support pins 140 and/or second cooling passage walls 162 positioned within first cooling passage 130, second cooling passage wall 168 may also be formed in second 0 cooling passage 130 to facilitate heat transfer and/or cooling of turbine shroud 100 during operation of gas turbine system 10 (see FIG. 1). additionally or alternatively, second cooling passage wall 168 along with first 1 cooling passage wall 162 may be formed in second 2 cooling passage 130 to separate second 3 cooling passage 130, and/or to facilitate channeling Cooling Fluid (CF) within second 4 cooling passage 130, as similarly discussed herein with respect to FIGS. 7 and 8. for example, first cooling passage wall 162 and second cooling passage wall 168 may substantially divide first cooling passage 130 into first leading section 170, second leading section 172, second aft section 174, and second aft section 174 and second 369 aft section 176. second may be formed between second and second central cooling passage wall 168, and second section of second , and between front cooling passage wall portion of second and aft cooling passage wall 168, and second 3614 may be formed between second and second 3614, and a leading cooling passage wall portion of integral cooling passage wall 162, , 3614, and a leading cooling passage wall portion of integral cooling passage wall may be formed between second , 3614, a leading cooling passage wall portion of integral cooling passage wall 172, , 3614, a leading cooling passage wall 172, a leading cooling passage wall 108, a leading cooling passage wall, a leading cooling passage, a leading cooling.

FIG. 11 illustrates a top view of another non-limiting example of the turbine shroud 100. in the non-limiting example illustrated in FIG. 1, the turbine shroud 100 may include only the second cooling passage wall 168. that is, the turbine shroud 100 may include the second cooling passage wall 168, but not the -th cooling passage wall 162. As similarly discussed herein with respect to FIGS. 9 and 10, the second cooling passage wall 168 (shown in phantom in FIG. 11) may be included and/or formed in the -th cooling passage 130. the second cooling passage wall 168 may extend axially between the forward end 108 and the aft end 110 of the unitary body 106 of the turbine shroud 100 and substantially parallel to the -th side 112 and the second side 118. additionally, and as discussed herein, the second cooling passage wall 168 may extend between and/or may be formed with the base portion 126 and the impingement portion , respectively, and may extend in the central portion 132, the forward portion 134 and the aft portion 136 of the unitary body 106, or through these portions (see FIG. 10).

As discussed herein with respect to FIGS. 9 and 10, the second cooling passage wall 168 may be formed in the cooling passage 130 to assist with heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see FIG. 1), and/or to assist with directing Cooling Fluid (CF) within the cooling passage 130. for example, the second cooling passage wall 168 may substantially divide the 0 cooling passage 130 into a side section 178 and a second side section 180. the side section 178 of the cooling passage 130 may be formed between the forward end 108 and the aft end 110 of the unitary body 106, and between the side 112 and the second cooling passage wall 168. the second side section 180 of the cooling passage 130 may be formed between the forward end 108 and the aft end 110 of the unitary body 106, and between the second side 118 and the second cooling passage wall 168. the side section 178 and the second side section 180 may each include the central portion 132 of the cooling passage 130, the forward portion 134 and the aft portion 136 of the turbine shroud 130, and the different portions of the cooling passage wall 130 may be formed during operation of the cooling passage 130, like as discussed herein with respect to the cooling passage wall 130 (CF 23, the cooling passage wall 168).

FIGS. 12 and 13 show various views of another non-limiting example of a turbine shroud 100 for a turbine 28 of the gas turbine system 10 of FIG. 1. specifically, FIG. 12 shows a top view of the turbine shroud 100, and FIG. 13 shows a cross-sectional side view of the turbine shroud 100 shown in FIG. 12. similar to the non-limiting examples shown in FIGS. 7 and 8, the turbine shroud 100 of FIGS. 12 and 13 may include a first cooling passage wall 162, the first cooling passage wall being formed in a first 1 cooling passage 130, and extending between a first side 112 and a second side 118 of the unitary body 106. additionally, in the non-limiting example shown in FIGS. 12 and 13, the second cooling passage 142 may further include a third cooling passage wall 182. a second cooling passage wall 182 (shown in phantom in FIG. 12) may be included and/or formed in the second cooling passage 142, and may extend axially from a forward end 108 of the unitary body 106 of the turbine shroud 100. additionally, the third cooling passage wall 182 may be formed in the second cooling passage wall 142 and/or on the second cooling passage wall 142, and may extend axially from a second cooling passage wall 126 and a second cooling passage wall 142, and a second cooling rib base portion of the turbine shroud 100, a second cooling passage wall 126, a second cooling passage wall 144, a second cooling rib, a second cooling passage wall, or a second cooling passage wall, or a second cooling rib, a second cooling passage wall, 120, a second cooling passage wall, a second.

As similarly discussed herein with respect to the plurality of support pins 140, 148 positioned within the turbine shroud 100, a third cooling passage wall 182 may be formed in the second cooling passage 142 to assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see FIG. 1). additionally or alternatively, a third cooling passage wall 182 may be formed in the second cooling passage 142 to separate the second cooling passage 142 and/or to help direct a Cooling Fluid (CF) through the second cooling passage 142 during the cooling process discussed herein. that is, the third cooling passage wall 182 may substantially divide the second cooling passage 142 into a section 184 and a second section 186. the section 184 of the second cooling passage 142 may be formed between the side 112 and the third cooling passage wall 182 of the monolithic body 106. the second section 186 of the second cooling passage 142 may be formed between the second side 118 of the monolithic body 106 and the third cooling passage wall 182. as similarly discussed herein, the cooling passage wall 184 and the second cooling passage wall 142 may be ensured by operation of the gas turbine system 10 (CF 1) during operation of the second cooling passage 142.

Similar to the second cooling channels 142, the third cooling channels 152 may include fourth cooling channel walls 188, in the non-limiting example shown in FIGS. 12 and 13, the fourth cooling channel walls 188 (shown in phantom in FIG. 12) may be included and/or formed in the third cooling channels 152 and may extend axially from the aft end 110 of the unitary body 106 of the turbine shroud 100. additionally, the fourth cooling channel walls 188 may extend substantially parallel to the side 112 and the second side 118 of the unitary body 106 of the turbine shroud 100 within the third cooling channels 152. continuing with the non-limiting example shown in FIG. 13, the fourth cooling channel walls 188 may be formed and/or extend between and/or with the base portion 126 and the second ribs 154, respectively, of the unitary body 106. continuing with the non-limiting example shown in FIG. 13, the fourth cooling channel walls 188 may be formed with the base portion 126 and the second ribs when the unitary body 106 of the turbine shroud 100 is formed using any suitable additive manufacturing process and/or method.

As similarly discussed herein with respect to the plurality of support pins 140, 158 positioned within the turbine shroud 100, a fourth cooling passage wall 188 may be formed in the third cooling passage 152 to assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10 (see FIG. 1). additionally or alternatively, the fourth cooling passage wall 188 may be formed in the third cooling passage 152 to separate the third cooling passage 152 and/or to help direct Cooling Fluid (CF) through the third cooling passage 152 during the cooling process discussed herein. that is, the fourth cooling passage wall 188 may substantially divide the third cooling passage 152 into a th section 190 and a second section 192. the th section 190 of the third cooling passage 152 may be formed between the side 112 of the monolithic body 106 and the fourth cooling passage wall 188. the second section 192 of the third cooling passage 152 may be formed between the second side 118 of the monolithic body 106 and the fourth cooling passage wall 188. as similarly discussed herein, the separation of the cooling passage wall 188 may be ensured by forming the third cooling passage wall 152 and the second section in the gas turbine shroud 100 (see FIG. 10).

While shown as being formed in the second and third cooling passages 142, 152, it should be understood that the cooling passage walls 182, 188 may be formed in only of the second or third cooling passages 142, 152-that is, in an additional non-limiting example, only the second cooling passage 142 may include the third cooling passage wall 182, or alternatively, the third cooling passage 152 may include the fourth cooling passage wall 188-additionally, although shown in fig. 12 and 13 as being formed in a turbine shroud 100 that includes only the cooling passage wall 162, the cooling passage walls 182, 188 may also be formed in a turbine shroud 100 that includes both the cooling passage wall 162 and the second cooling passage wall 168 (see fig. 9 and 10), or alternatively, only the second cooling passage wall 168 (see fig. 11).

14-18 illustrate various views of a non-limiting example of a turbine shroud 100 for a turbine 28 of the gas turbine system 10 of FIG. 1. It should be appreciated that similarly numbered and/or named components may function in a substantially similar manner. Redundant explanations of these components have been omitted for the sake of clarity.

Turning to FIG. 14, a non-limiting example of the monolithic body 106 of the turbine shroud 100 may include only the th and third cooling channels 130, 152. that is, the turbine shroud 100 may not include the second cooling channel 142 (see FIG. 6.) the monolithic body 106 of the turbine shroud 100 that does not include the second cooling channel 142 may also not include the th rib 144, the th plurality of impingement holes 146, and the th plurality of support pins 148, respectively, instead, and as shown in FIG. 14, the forward portion 134 of the th cooling channel 130 may extend substantially between the base portion 126 and the impingement portion 128. additionally, in the non-limiting example shown in FIG. 14, the th exhaust hole 150 may be in fluid communication with the th cooling channel 130 (and more specifically, the forward portion 134 of the th cooling channel 130) and may extend from the th cooling channel 130 to the forward end 108 of the turbine shroud 100 through the monolithic body 106.

As similarly discussed herein with respect to the central portion 132 of the cooling channel 130, the portion of the plurality of support pins 140 may be positioned within the forward portion 134, and/or may extend between the base portion 126 and the impingement portion 128 in the forward portion 134 of the cooling channel 130 the plurality of support pins 140 positioned within the forward portion 134 may be formed with the base portion 126 and the impingement portion 128 of the monolithic body 106 to provide support, structure, and/or rigidity, as well as to assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10.

In a non-limiting example shown in FIG. 15, the unitary body 106 of the turbine shroud 100 may include only the -th cooling channel 130 and the second cooling channel 142. that is, the turbine shroud 100 may not include the third cooling channel 152 (see FIG. 6.) As a result of not including the third cooling channel 152, the unitary body 106 of the turbine shroud 100 may also not include the second ribs 154, the second plurality of impingement holes 156, and the second plurality of support pins 158, respectively. As shown in FIG. 15, the aft portion 136 of the -th cooling channel 130 may extend substantially between the base portion 126 and the impingement portion 128. the second exhaust holes 160 may be in fluid communication with the -th cooling channel 130 (and, more specifically, the aft portion 136 of the -th cooling channel 130) and may extend through the unitary body 106 from the -th cooling channel 130 to the aft end 110 of the turbine shroud 100.

The portion of the plurality of support pins 140 formed and/or positioned within the cooling channel 130 may also be positioned within the aft portion 136 and/or may extend between the base portion 126 and the impingement portion 128 in the aft portion 136 of the cooling channel 130 the plurality of support pins 140 positioned within the aft portion 136 may be formed with the base portion 126 and the impingement portion 128 of the unitary body 106 to provide support, structure, and/or rigidity, as well as to assist in heat transfer and/or cooling of the turbine shroud 100 during operation of the gas turbine system 10.

Similar to FIG. 15, the non-limiting example of the turbine shroud 100 shown in FIG. 16 may also include only the th cooling channel 130 and the second cooling channel 142. however, and in comparison to the non-limiting example shown in FIG. 15, the th cooling channel 130 of the turbine shroud 100 shown in FIG. 16 may include different features. for example, the aft portion 136 of the th cooling channel 130 may include a substantially serpentine pattern 194. that is, and as shown in FIG. 16, the aft portion 136 of the th cooling channel 130 may be formed to include a serpentine pattern 194 that may extend, serpentine and/or include a plurality of turns spanning between the base portion 126 and the impingement portion 128. in the non-limiting example, the serpentine pattern 194 formed in the aft portion 136 of the th cooling channel 130 may be in fluid communication with the second serpentine exhaust hole 160 extending through the aft end 110 of the monolithic body 106 of the turbine 100. in the operation of the gas turbine system 10, the number of turns formed in the aft portion 136 of the 2 nd cooling channel 130 may be more than the serpentine pattern formed in the aft portion 136 of the cooling channel 130, or the serpentine pattern 194 included in addition to the cooling channel 134, as shown in the example of the cooling channel 130, or in addition to the serpentine pattern 136.

FIGS. 17 and 18 show various views of additional non-limiting examples of turbine shrouds 100 for the turbines 28 of the gas turbine system 10 of FIG. 1. specifically, FIG. 17 shows a top view of the turbine shroud 100, and FIG. 18 shows a cross-sectional side view of the turbine shroud 100. the turbine shroud 100 shown in FIGS. 17 and 18 may include another non-limiting examples of serpentine patterns 194 formed in the aft portion 136 of the cooling channel 130. that is, and as shown in FIGS. 17 and 18, the aft portion 136 of the cooling channel 130 may be formed to include a serpentine pattern 194 that may extend, serpentine run and/or include a plurality of turns spanning between the end 112 and the second end 118 of the overall body 106. each portion of the opening of the serpentine pattern 194 of the cooling channel 130 may also extend radially between the base portion 126 and the impingement portion 128 of the overall serpentine body 106 of the turbine shroud 100. in the non-limiting example, the turns formed in the aft portion 136 of the cooling channel 130 may extend through the second serpentine pattern 136 of the cooling channel 130 as shown in the aft portion of the cooling channel 130 or after the cooling channel 130, such as may be understood by the cooling fluid flow pattern 194 that the second cooling channel 130 may extend from the aft portion of the cooling channel 130 and/or through the aft cooling channel 130 and/or through the second end of the cooling channel 136 as illustrated in the cooling channel 130, the cooling channel 18, the cooling channel 130 may extend through the cooling fluid flow pattern 26, the cooling channel 18, the aft portion of the cooling channel 130, and/or through the cooling end 18, and/or through the cooling fluid exhaust outlet port 18, the cooling fluid exhaust outlet port 134, and/or through the cooling channel 134, such as illustrated in the cooling fluid exhaust outlet port 134, and/or through the cooling fluid exhaust port 134.

While shown and described herein with respect to various embodiments, it should be understood that the turbine shroud 100 may include any combination of the configurations shown in the non-limiting examples of FIGS. 3-18. for example, the turbine shroud 100 may include only the -th cooling channel 130, the -th cooling channel including a front portion 134 similar to that shown in the non-limiting example of FIG. 14, and an aft portion 136 similar to that shown in the non-limiting example of FIG. 15. in another non-limiting examples, a turbine shroud 100 including only the -th cooling channel 130 may include a front portion 134 similar to that shown in the non-limiting example of FIG. 14, and an aft portion 136 similar to that shown in the non-limiting example of FIG. 18 that includes a serpentine pattern 194.

The technical effect is to provide a unitary body turbine shroud that includes a plurality of cooling channels formed therein. The unitary body of the turbine shroud allows for more complex cooling channel configurations and/or thinner walls for the turbine shroud, which in turn improves cooling of the turbine shroud.

As used herein, the singular forms "," "," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, it will be understood at the step that, when used in this specification, the terms "comprises" and/or "comprising" specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of or more other features, integers, steps, operations, elements, components, and/or groups thereof.

Thus, a value modified by or terms (such as "about," "about," and "substantially") may not be limited to the precise value specified.

The corresponding structures, materials, acts, and equivalents of all means or step plus function elements in the claims below 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, but is not intended to be exhaustive or limited to the disclosure in the form 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 disclosure. The embodiments were chosen and described in order to best explain the principles of the disclosure and the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.