Separation tool for turbine system component segments

Abstract

This provides a separation tool for component segments of a turbine system. [Solution] A tool for separating adjacent component segments in a stage of a turbine section is disclosed. The tool includes a base, a first curved plate 180, and a second curved plate 182. The first plate includes a first end for engaging a portion of a component segment, and the second plate includes a first end for engaging a fixed element, such as the other component segment or a half-casing of the turbine section. A coupling connects the first plate to the base, and a linear actuator 250 is located between the base and the second plate. The linear actuator linearly moves the second plate between a first position in which the first end of the first plate and the first end of the second plate are retracted, and a second position in which the first end of the first plate and the first end of the second plate extend a certain distance from each other to force the adjacent component segments apart.

Description

Technical Field

[0001] The present disclosure relates generally to turbine systems and, more particularly, to a separation tool for separating adjacent component segments, such as nozzle segments, in preparation for removing those segments from the casing of a turbine section for repair or replacement.

Background Art

[0002] A turbine system extracts energy from a flow of a working fluid, such as hot combustion gas, steam, water, etc., to produce output power for an external load, such as a generator. In one example, a gas turbine (GT) system extracts energy from a flow of hot combustion gas. The GT system includes a compressor for compressing ambient air and a combustor for mixing the air flow with a fuel flow to produce hot combustion gas. A turbine section (e.g., an expansion turbine) receives the flow of hot combustion gas, extracts energy therefrom to power the compressor, and produces output power for an external load. High-temperature gas components, such as turbine nozzles and blades, positioned along the high-temperature gas path of the GT system are subjected to not only high temperatures and pressures but also different types of dynamic forces. Other turbine systems, such as steam or hydro turbines, experience similar environmental conditions with their working fluid components. Assuming such an environment, these components may be periodically replaced and / or refurbished to ensure the efficient and safe performance of the turbine system.

[0003] Removing components such as nozzles can be difficult and time-consuming. Each stage of a component in a turbine section may typically consist of segments mounted circumferentially from end to end, forming a continuous ring within the turbine section's half-casing. Extreme environments, such as high temperatures and pressures, can cause component segments to stick together and / or become fixed in their supporting structures. Small gaps in a turbine section, such as between the radially outer end of a nozzle segment and the insulating material within the turbine section's half-casing, provide little space to access the component segments or to apply any type of force to separate them before removal. One technique for separating component segments is to apply force to more easily accessible parts of the component segment, such as the airfoil. However, this technique increases the likelihood of damaging reusable and potentially more sensitive parts, such as the airfoil of a nozzle segment. Another method involves using a tool between the casing and one of the component segments to apply force to remove the component segments, but this method requires external access to the casing and two operators, one inside the casing and one outside, to be used properly. [Overview of the Initiative]

[0004] All aspects, examples, and features described below can be combined in any technically possible way.

[0005] One aspect of the present disclosure provides a tool for separating a first component segment from a second component segment adjacent to the first component segment in a stage of a turbine section, the tool comprising: a base; a first curved plate including a first end configured to engage with a portion of the first component segment; a second curved plate including a first end configured to engage with a fixing element, wherein the fixing element includes at least one portion of the second component segment or half-casing of the turbine section; and the first curved plate and The device comprises a coupling that connects one second end of the second curved plate to a base, and a linear actuator between the base and the other second end of the first curved plate and the second curved plate, the linear actuator moving the first curved plate and the second curved plate linearly relative to each other between a first position in which the first end of the first curved plate and the first end of the second curved plate are retracted, and a second position in which the first end of the first curved plate and the first end of the second curved plate extend a certain distance from each other, forcing the first component segment and the second component segment to separate.

[0006] Another aspect of the present disclosure includes any of the preceding aspects, wherein the first component segment and the second component segment each include a nozzle segment, and the first curved plate and the second curved plate have a radius of curvature that matches the radius of curvature of the space between the casing and the radial outer surface of the nozzle segment at the stage of the turbine section.

[0007] Another aspect of this disclosure includes any of the prior aspects, wherein the linear actuator includes a hydraulic ram.

[0008] Another aspect of the present disclosure includes any of the prior aspects, the tool further comprising an axial spacer member including a third curved plate having an axial width, configured to hold the first curved plate and the second curved plate in working positions at a step in the turbine section between a portion of a first component segment and a fixed element, with the first end of the first curved plate and the first end of the second curved plate being such that they are located between a portion of a first component segment and a fixed element.

[0009] Another aspect of the present disclosure includes any of the preceding aspects, wherein the other of the first curved plate and the second curved plate has a first circumferential portion including a second end, a second circumferential portion including the first end, and an axial extension portion connecting the first circumferential portion and the second circumferential portion.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, wherein each of the first curved plate and the second curved plate includes a circumferential extension and a vertical portion extending perpendicularly to the circumferential extension, and the first end of the first curved plate and the first end of the second curved plate are located on the vertical portion.

[0011] Another aspect of the present disclosure includes any of the preceding aspects, wherein the vertical portion extends axially with respect to the axis of the turbine section.

[0012] Another aspect of the present disclosure includes any of the preceding aspects, wherein the vertical portion extends radially inward with respect to the axis of the turbine section.

[0013] Another aspect of the present disclosure includes any of the preceding aspects, wherein the coupler includes a body, a first connector at a first end of the body for pivotally coupling the body to a base, and a second connector at a second opposing end of the body for pivotally coupling the body to a second end of one of a first curved plate and a second curved plate.

[0014] Another aspect of this disclosure includes any of the prior aspects, wherein the body is length-adjustable.

[0015] Another aspect of the present disclosure includes any of the preceding aspects, wherein the linear actuator includes at least one of a first connector at a first end for fixing and coupling the linear actuator to a base, or a second connector at a second opposing end for fixing and coupling the linear actuator to a second end of the first curved plate and the other of the second curved plate.

[0016] Another aspect of the present disclosure includes any of the preceding aspects, wherein the first curved plate and the second curved plate include a radially inward-facing surface and a radially outward-facing surface, and the tool further comprises at least one radial spacer on the radially outward-facing surface, configured to position each curved plate at a radial position where the first end is between a portion of the first component segment and a fixed element.

[0017] Another aspect of the present disclosure includes any of the prior aspects, wherein the tool further comprises a fixing member configured to lock the position of a second component segment relative to the casing.

[0018] Another aspect of the present disclosure includes any of the prior aspects, wherein the first curved plate and the second curved plate slide in contact with each other along at least a portion of their length when a linear actuator moves the first curved plate and the second curved plate relative to each other between a first position and a second position.

[0019] Another aspect of the present disclosure includes a tool for separating a first nozzle segment from a second nozzle segment adjacent to the first nozzle segment in a stage of a turbine section, the tool comprising a base and a first curved plate including a first end configured to engage with a portion of the first nozzle segment, and a second curved plate including a first end configured to engage with a fixing element, wherein the fixing element includes at least one portion of the second nozzle segment or half-casing of the turbine section, and the first curved plate and the second The device comprises a coupling that connects the second end of one of the curved plates to a base, and a linear actuator between the base and the other second end of the first curved plate and the second curved plate, the linear actuator moving the first curved plate and the second curved plate linearly relative to each other between a first position in which the first end of the first curved plate and the first end of the second curved plate are retracted, and a second position in which the first end of the first curved plate and the first end of the second curved plate extend a certain distance from each other, forcing the first nozzle segment and the second nozzle segment to separate.

[0020] Another aspect of the present disclosure includes any of the preceding aspects, wherein the first and second curved plates have a radius of curvature that matches the radius of curvature of the space between the casing and the radial outer surface of the nozzle segment at the stage of the turbine section.

[0021] Another aspect of the present disclosure includes any of the preceding aspects, wherein the other of the first curved plate and the second curved plate has a first circumferential portion including a second end, a second circumferential portion including the first end, and an axial extension portion connecting the first circumferential portion and the second circumferential portion.

[0022] Another aspect of the present disclosure includes any of the preceding aspects, wherein each of the first curved plate and the second curved plate includes a circumferential extension and a vertical portion extending perpendicular to the circumferential extension, the first end of the first curved plate and the first end of the second curved plate being located on the vertical portion, the vertical portion extending in one of the axial direction with respect to the axis of the turbine section and the radially inward direction with respect to the axis of the turbine section.

[0023] Another aspect of the present disclosure includes any of the preceding aspects, wherein the coupler includes a length-adjustable body, a first connector at a first end of the body for pivotally coupling the body to a base, and a second connector at a second opposing end of the body for pivotally coupling the body to a second end of one of a first curved plate and a second curved plate.

[0024] Another aspect of the present disclosure includes any of the preceding aspects, wherein the first curved plate and the second curved plate include a radially inward-facing surface and a radially outward-facing surface, and the tool further comprises at least one radial spacer on the radially outward-facing surface, configured to position each curved plate at a radial position where the first end is between a portion of the first nozzle segment and a fixed element.

[0025] Another aspect of the present disclosure includes any of the preceding aspects, and the first curved plate and the second curved plate slide in contact with each other along at least a portion of their lengths when the linear actuator moves the second curved plate relative to the first between a first position and a second position.

[0026] Another aspect of the present disclosure includes a method of separating first and second adjacent nozzle segments in a half casing of a turbine system, the method comprising circumferentially positioning a first curved plate and a second curved plate of a separation tool along the first and second adjacent nozzle segments, the first curved plate including a first end for engaging a portion of the first nozzle segment and a second end coupled to a base of the separation tool, the second curved plate including a first end for engaging a fixed element and a second end coupled to the base by a linear actuator; axially positioning the first end of the first curved plate and the first end of the second curved plate between a portion of the first nozzle segment and the fixed element; and actuating the linear actuator to move the first plate and the second plate relative to each other between a first position where the first end of the first curved plate and the first end of the second curved plate are retracted and a second position where the first end of the first curved plate and the first end of the second curved plate are spaced apart from each other to forcibly separate the first nozzle segment and the second nozzle segment.

[0027] Two or more aspects described in this summary section, including those described above, may be combined to form embodiments not specifically described herein. That is, all embodiments described herein may be combined with each other.

[0028] Details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.

[0029] These and other features of the Disclosure will be more readily apparent from the following detailed description of various embodiments of the Disclosure, in conjunction with the accompanying drawings illustrating various embodiments of the Disclosure. [Brief explanation of the drawing]

[0030] [Figure 1] This is a schematic diagram of a turbine system according to an embodiment of the present disclosure. [Figure 2] This is a cross-sectional view of the turbine section of a turbine system according to an embodiment of the present disclosure. [Figure 3] This is a perspective view of a tool positioned to separate a first component segment and a second component segment in a half-casing according to an embodiment of the present disclosure. [Figure 4] This is an enlarged perspective view of the component segments in the tool and half-casing according to embodiments of the present disclosure. [Figure 5] This is a radially inward perspective view of a tool and component segment according to an embodiment of the present disclosure. [Figure 6] This is a side perspective view of the tool according to an embodiment of the disclosure. [Figure 7] This is a top view of a tool according to an embodiment of the disclosure. [Figure 8] This is a side view of the tool according to an embodiment of the present disclosure. [Figure 9] This is a side view of a component segment within a tool and a half-casing according to an embodiment of the present disclosure. [Figure 10] This is a perspective view of another option for the vertical portions of the first and / or second curved plates of the tool, according to other embodiments of the present disclosure. [Figure 11] This is a bottom view of a tool according to another embodiment of the present disclosure. [Figure 12] This is a bottom view of a tool according to an additional embodiment of the present disclosure. [Figure 13] This is a bottom perspective view of a tool according to another embodiment of the present disclosure. [Figure 14]This is a bottom perspective view of a tool having an axial spacer member according to a further embodiment of the present disclosure. [Figure 15] This is a perspective view of a tool having an axial spacer member according to a further embodiment of the present disclosure. [Figure 16A] This is a bottom view of a tool before separating the first component segment and the second component segment according to an embodiment of the present disclosure. [Figure 16B] This is another bottom view of the tool before separating the first component segment and the second component segment according to an embodiment of the present disclosure. [Figure 16C] This is another bottom view of the tool before separating the first component segment and the second component segment according to an embodiment of the present disclosure. [Figure 16D] This is yet another bottom view of the tool before separating the first component segment and the second component segment according to an embodiment of the present disclosure. [Figure 17A] This is a bottom view of a tool having a linear actuator activated to isolate component segments according to an embodiment of the present disclosure. [Figure 17B] This is a bottom view of a tool having a linear actuator activated to isolate component segments according to an embodiment of the present disclosure. [Figure 17C] This is a perspective view of a tool having a linear actuator activated to isolate component segments, according to an embodiment of the present disclosure. [Figure 17D] This is a bottom view of a tool having a linear actuator activated to isolate component segments according to an embodiment of the present disclosure. [Modes for carrying out the invention]

[0031] Please note that the drawings in this disclosure are not necessarily to a uniform scale. The drawings are intended to illustrate only typical embodiments of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, the same reference numerals represent similar elements across drawings.

[0032] As a first issue, in order to clearly explain the subject matter of the current technology, it is necessary to select specific technical terms when referring to and describing relevant mechanical components within exemplary applications of turbine systems. In doing so, where possible, common industry jargon is used and adopted in accordance with its accepted meaning. Unless otherwise stated, such jargon should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that, in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single part may include multiple components and may be referred to in another context as consisting of multiple components. Or, what may be described herein as including multiple components may be referred to elsewhere as a single part.

[0033] In addition, this specification may use several descriptive terms, and it will be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise specified: As used herein, “downstream” and “upstream” are terms indicating direction relative to the flow of a fluid, such as the working fluid through a turbomachinery, or, for example, the flow of air through a combustor or the coolant through one of the turbomachinery's component systems. The term “downstream” corresponds to the direction of the fluid flow, and the term “upstream” refers to the direction opposite to the flow. The terms “forward” and “rear” refer to direction, unless further specified, with “forward” referring to the front end or compressor end of the turbomachinery, and “rear” referring to the rear end or turbine end of the turbomachinery.

[0034] In many cases, it is necessary to describe components that are located at different radial positions relative to a central axis. The term “axial” refers to movement or position parallel to an axis, e.g., the axis of a turbomachinery. The term “radial” refers to movement or position perpendicular to an axis, e.g., the axis of a turbomachinery. In such cases, if the first component is located closer to the axis than the second component, this specification states that the first component is “radially inward” or “inward” of the second component. On the other hand, if the first component is located further from the axis than the second component, this specification may state that the first component is “radially outward” or “outward” of the second component. Finally, the term “circumferential” refers to movement or position around an axis, e.g., around the circumferential inner surface of a half-casing extending around the axis of a turbomachinery. As indicated above, it will be understood that such terms may be applied with respect to the axis of a turbomachinery.

[0035] In addition, as described below, several descriptive terms may be used herein. The terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of any individual component.

[0036] The technical terms used herein are for the sole purpose of describing specific embodiments and are not intended to limit this disclosure. Where used herein, the singular forms “a,” “an,” and “the” are intended to also include the plural form unless the context otherwise explicitly indicates. Where used herein, the terms “comprises” and / or “comprising” express the presence of the described features, integers, steps, actions, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, actions, elements, components, and / or groups thereof. “Optional” or “optionally” means that the events described later may or may not occur, or the features described later may or may not exist, and that this description includes both cases in which the event occurs or the feature exists, and cases in which the event does not occur or the feature does not exist.

[0037] When an element or layer is referred to as "on top of," "engaged to," "connected to," "bonded to," or "attached to" another element or layer, that element or layer may be directly on top of, engaged to, connected to, bonded to, or attached to the other element or layer, or there may be an intervening element or layer. In contrast, when an element is referred to as "directly on top of," "directly engaged to," "directly connected to," or "directly bonded to" another element or layer, there is no intervening element or layer. Other words used to describe the relationship between elements should be interpreted similarly (e.g., "between" vs. "directly between," "adjacent" vs. "directly adjacent"). As used herein, the term "and / or" includes any combination of one or more of the related enumerated items. The verb forms "bond" and "attach" may be used interchangeably herein.

[0038] Embodiments of the present disclosure include a tool for separating a first component segment from a second component segment adjacent to the first component segment in a stage of a turbine section. For illustrative purposes, the tool according to embodiments of the present disclosure is described in relation to a component segment in the form of a nozzle segment. It is emphasized that the teachings of the present disclosure may be applied to other types of component segments in a turbine system, such as shroud segments or blade segments. The tool includes a base and a first curved plate including a first end configured to engage a portion of the first component segment, and a second curved plate including a first end configured to engage a fixing element. The fixing element may include at least one portion of the second component segment or half-casing of the turbine section. A coupling connects the first curved plate and the second end of one of the second curved plates to the base, and a linear actuator is located between the base and the other second end of the first curved plate and the second curved plate. The linear actuator moves the first and second curved plates linearly relative to each other between a first position in which the first ends of the first curved plate and the first end of the second curved plate are retracted, and a second position in which the first ends of the first curved plate and the first end of the second curved plate extend a certain distance from each other, forcing the first and second component segments to separate. The tool applies separation force in a safe manner away from any sensitive structures such as airfoils, reducing the required disassembly time. The tool requires only one user to operate and, in most cases, does not require external access to the casing for operation. Furthermore, the tool is highly customizable for applicability in various situations.

[0039] Figure 1 is a schematic diagram of an exemplary turbine system 100, such as a gas turbine (GT) system, using component segments 102A-B (Figures 2-4) according to embodiments of the present disclosure. It should be understood that the turbine system 100 of the present disclosure does not have to be a gas turbine system, but rather could be any suitable turbine system, such as a steam turbine system, a jet engine, or any other suitable system. The exemplary turbine system 100 may include a compressor section 112, a combustor section 114, and a turbine section 116. The compressor section 112 and the turbine section 116 may be connected by a shaft 118. The shaft 118 may be a single shaft or multiple shaft segments connected to each other to form the shaft 118. The shaft defines the X-axis of the turbine system 100 (labeled "TA" for the "turbine shaft" in Figure 2). As is commonly known in the art, air or another suitable working fluid flows through the compressor section 112 and is compressed in the compressor section 112. Next, the compressed working fluid is supplied to the combustor section 114, where it is combined with fuel and combusted to produce high-temperature combustion gases. After flowing through the combustor section 114, the high-temperature combustion gases can flow into the turbine section 116 and then flow through the turbine section 116.

[0040] Figure 2 shows an embodiment of a portion of a turbine section 116 according to the present disclosure. A high-temperature gas path 120 may be defined within the turbine section 116. Various high-temperature gas path component stages, such as shroud segments 122, fixed nozzle segments 124, and turbine rotor blade segments 126, may be at least partially located within the high-temperature gas path 120. For example, as shown, the turbine section 116 may include a plurality of shroud segments 122, a plurality of nozzle segments 124, and a plurality of turbine rotor blade segments 126 arranged in a plurality of turbine stages. More specifically, a stage includes a plurality of circumferentially adjacent component segments 102. That is, each stage of components in the turbine section 116 may typically be formed of component segments 102 that are circumferentially mounted from end to end to form a continuous ring or annular array within the turbine casing of the turbine section 116. For example, each stage may include a plurality of nozzle segments 124 arranged in an annular array and a plurality of turbine rotor blade segments 126 arranged in an annular array. Each stage may also include an annular array, i.e., a plurality of shroud segments 122 arranged radially outward from each plurality of turbine rotor blade segments 126. Each annular array may define a portion of the high-temperature gas path 120.

[0041] In one example, as shown in Figure 2, the turbine section 116 may have three stages. For example, the first stage of the turbine section 116 may include a first-stage nozzle assembly 128, a first-stage blade assembly 130, and a first-stage shroud assembly 131. The nozzle assembly 128 may include a plurality of nozzle segments 124 arranged and fixed circumferentially around the shaft 118. The blade assembly 130 may include a plurality of turbine rotor blade segments 126 arranged circumferentially around the shaft 118 and coupled to the shaft 118. The shroud assembly 131 may include, for example, a plurality of shroud segments 122 arranged circumferentially around the shaft 118 and fixed circumferentially around the shaft 118 within a fixed turbine casing 150. Similarly, the second stage of the turbine section 116 may include a second-stage nozzle assembly 132, a second-stage blade assembly 134, and a second-stage shroud assembly 135. The nozzle segment 124 included in the second-stage nozzle assembly 132 may be circumferentially positioned and fixed around the shaft 118. The turbine rotor blade segment 126 included in the second-stage blade assembly 134 may be circumferentially positioned around the shaft 118 and coupled to the shaft 118. The shroud segment 122 included in the second-stage shroud assembly 135 may be circumferentially positioned and fixed around the shaft 118. The second-stage nozzle assembly 132 is positioned along the hot gas path 120 between the first-stage blade assembly 130 and the second-stage blade assembly 134 (and the second-stage shroud assembly 135). Similarly, the third stage of the turbine section 116 may include a third-stage nozzle assembly 136, a third-stage blade assembly 138, and a third-stage shroud assembly 139. The nozzle segment 124 included in the nozzle assembly 136 may be circumferentially positioned and fixed around the shaft 118. The turbine rotor blade segments 126 included in the blade assembly 138 are circumferentially arranged around the shaft 118 and can be coupled to the shaft 118. The shroud segments 122 included in the shroud assembly 139 can be circumferentially arranged and fixed around the shaft 118.The third-stage nozzle assembly 136 is positioned along the high-temperature gas path 120 between the second-stage blade assembly 134 and the third-stage blade assembly 138 (and the third-stage shroud assembly 139).

[0042] It should be understood that the turbine section 116 is not limited to three stages, but rather any number of stages falls within the scope and intent of this disclosure. It should be understood that the teachings of this disclosure are not limited to component segments 102 in the turbine section 116, but could also be component segments 102 at least partially positioned in the flow path for the compressor section 112 or any other suitable section of the turbine system 100. Furthermore, it should be understood that the shroud segments 122 in the shroud assemblies 131, 135, and 139, and the nozzle segments 124 in the nozzle assemblies 128, 132, and 136, can be fixedly coupled to the turbine casing 150 surrounding the shaft 118 (Figure 1).

[0043] During the operation of the turbine system 100, high-temperature gas component segments 102, such as the nozzle segment 124, are positioned along the high-temperature gas path 120 of the turbine section 116 and are subjected not only to high temperature and high pressure but also to different types of dynamic forces. As described above, assuming such an environment, these component segments 102 may be periodically replaced and / or refurbished to ensure the efficient and safe performance of the turbine system 100. In particular, if extreme environments cause the component segments 102 to stick together and / or become fixed in the support structure, removal of the component segments 102 may be difficult and time-consuming.

[0044] Figure 3 shows a perspective view of a half-casing 150H (hereinafter referred to as "half-casing 150H" for brevity) of a turbine casing having a first component segment 102A adjacent (circumferentially) to a second component segment 102B, and Figure 4 shows a magnified perspective view of component segments 102A-B in half-casing 150H. Half-casing 150H is shown as the lower half-casing after the upper half-casing (not shown) has been removed and all component segments except the last two component segments 102A and 102B have been removed. Figures 3 and 4 also show a tool 170 for separating adjacent component segments 102A-B.

[0045] For illustrative purposes, tool 170 will be described with respect to component segments 102A-B in the form of nozzle segments 124A-B (Figure 2). Thus, Figures 3 and 4 also show the first nozzle segment 124A adjacent to the second nozzle segment 124B. Thus, both terms “component segment” and “nozzle segment” may be used herein and are generally interchangeable. As understood in the art, each stage of component segment 102 in turbine section 116 can typically be formed by placing the component segment 102 circumferentially from end to end to form a continuous ring or annular array within a set pair of half-casings 150H of turbine section 116 (Figure 1) (then assembling the two half-casings). More specifically, in Figures 3 and 4, nozzle segments 124A-B are shown together with spatially free outer end walls 154A-B (with the rotor already removed) and inner end walls 152A-B in a support structure 156 in the form of a slot in the half-casing 150H. It will be recognized that the support structure 156 can have various alternative forms and positions depending on the type of component segment 102 in which it is used. In any case, component segments 102A-B, e.g., nozzle segments 124A, 124B are slidably positioned end-to-end in the circumferentially extending support structure 156. In Figures 3 and 4, nozzle segments 124A-B each have four airfoil sections 158, but any number of airfoil sections 158, e.g., one, two, three, or four or more, may be used on each nozzle segment 124A-B. The number of airfoil sections 158 used can determine the circumferential range of each nozzle segment 124A-B. Other types of component segments 102 may have different circumferential ranges. As described, the tool 170 can be customized to handle component segments 102A-B having any circumferential range.

[0046] Component segments 102A-B, such as nozzle segments 124A-B, are typically removed by sliding them circumferentially along the support structure 156, for example, a slot, until their ends 159 exit the support structure 156. As described above, extreme environments in the turbine section 116, such as high temperature and high pressure, may cause component segments 102, such as nozzle segments 124A-B, to stick together and / or become fixed in the support structure 156. As shown in Figure 4, the space 160 between the radially outer ends 162 of nozzle segments 124A, 124B and the half-casing 150H is relatively small, making it extremely difficult to access the nozzle segments 124A-B for tools for separation and / or removal. In some cases, the space 160 is further reduced by the presence of an insulating layer 164 positioned between the radially outer ends 162 of nozzle segments 124A, 124B and the half-casing 150H. Similar challenges exist for other types of component segments 102 in the turbine section 116 (Figure 1), such as the shroud segment 122 (Figure 2) or the blade segment 126 (Figure 2), and for component segments 102 in other types of turbine systems.

[0047] Tool 170 is shown at a predetermined position in the half-casing 150H to separate the first component segment 102A from the second component segment 102B adjacent to the first component segment 102A, for example, in the second stage of the half-casing 150H of the turbine section 116 (Figures 1-2). That is, tool 170 is shown at a predetermined position in a specific stage 165 of the turbine section 116 (Figures 1-2) to separate the first nozzle segment 124A from the second nozzle segment 124B adjacent to the first nozzle segment 124A. Figure 5 shows a radially inward perspective view of tool 170 and nozzle segments 124A and 124B. As described, the first nozzle segment 124A may include a portion 166 that can be engaged by a part of the tool 170, and the second nozzle segment 124B may include a portion 168 that can be engaged by a part of the tool 170. In the example shown in Figure 5, portions 166 and 168 may be flanges or other structures extending radially outward from the outer end walls 154A and 154B, respectively. It will be recognized that portions 166 and 168 can take on a wide variety of other configurations depending on other factors, such as the type of component segment 102, the stage used, and the type of turbomachine.

[0048] Next, the structure of the tool 170 will be described with reference to Figures 6 to 15. According to embodiments of this disclosure, Figure 6 shows a side perspective view of the tool 170, Figure 7 shows a top view of the tool 170, and Figure 8 shows a side view of the tool 170. The tool 170 includes a base 172. The base 172 may include any structural elements through which other parts of the tool 170 can be coupled for operation, as described herein. The base 172 may also provide a structure through which the tool 170 can be positioned, for example, in a half-casing 150H and / or storage location when not in use. The base 172, and therefore the tool 170, can be positioned manually by the user or using any form of automatic lifting system, such as an overhead crane or gantry, a robotic arm, etc.

[0049] The tool 170 also includes a pair of curved plates 180, 182 configured to position within the space 160 to separate component segments 102A-B, such as nozzle segments 124A-B. More specifically, the tool 170 includes a first curved plate 180, which includes a first end 184 configured to engage with a nozzle segment, for example, a portion 166 of the first nozzle segment 124A. Similarly, the second curved plate 182 includes a first end 186 configured to engage with a fixing element 188. The fixing element 188 may include any currently known or hereafter developed structure that is accessible within the space 160 and can resist the separating force F (Figures 17A-17D) applied to it by the tool 170. In certain embodiments, the fixing element 188 may include at least one portion of the second nozzle segment 124B or the half-casing 150H of the turbine section 116 (Figures 1-2). In Figure 5, the fixing element 188 may include a portion 168 of the second nozzle segment 124B, as previously described. Since the second nozzle segment 124B is fixed in place, portion 168 is fixed in place. The second nozzle segment 124B can be fixed in place in several ways. For example, the second nozzle segment 124B can be fixed in place by simply being adjacent to and in contact with another nozzle segment (not shown, but located on the left side of Figure 5) that is not moved or separated from the support structure 156. Alternatively, the nozzle segment 124B can be fixed in place by movement in the turbine section 116 (Figure 1) via fixation in the support structure 156. Alternatively, or in addition to the previously described mechanism for fixing the second nozzle segment 124B in place as shown in Figure 5, the second nozzle segment 124B may optionally be fixed in place by a fixing member 192 configured to lock the position of the second nozzle segment 124B relative to the half-casing 150H, i.e., within the support structure 156.This latter option may be desired if the previously described option is insufficient to hold the second nozzle segment 124B in place, for example, if the second nozzle segment 124B is the second-to-last nozzle segment 124 remaining within the support structure 156. The fixing member 192 may include any structure that can fix the movement of the second nozzle segment 124B relative to the half-casing 150H, for example, a pin extending through the half-casing 150H (see Figure 5), a blocking element in the space 160, or other structures.

[0050] Figure 9 shows a side view of the tool 170 and nozzle segments 124A and 124B within the half-casing 150H. Figure 9 shows an example in which the fixing element 188 includes a portion 194 of the half-casing 150H. The portion 194 of the half-casing 150H may include, but is not limited to, a flange, an edge, or other structure that can engage with the first end 186 of the second curved plate 182. Less likely, the first end 186 of the second curved plate 182 can engage with both the portion 166 of the second curved plate 182 and the portion 194 of the half-casing 150H, for example, if they are aligned circumferentially. Also in Figure 9, the portion 194 of the half-casing 150H is axially positioned, for example, within and outside the page of Figure 9. Figure 9 shows a method, as further described herein, in which the tool 170, in particular the curved plates 180, 182, may be positioned circumferentially (along the Y direction, left to right on the page) within the space 160, and then axially (in the X direction, in or out of the page) to position the first ends 184, 186 of the curved plates between a portion 166 of the first component segment 102A and a fixed element 188, for example, a portion 194 of the half-casing 150H.

[0051] Referring to Figures 6 and 7, the first curved plate 180 and the second curved plate 182 include a radially inward-facing surface 200 and a radially outward-facing surface 202. The surfaces 200 and 202 are curved and have an axial width W1 such that the curved plates 180 and 182 can be axially positioned within the space 160, as will be further described. The first curved plate 180 and the second curved plate 182 also include a circumferential extension 210 and a vertical portion 212 extending perpendicularly to the circumferential extension 210. The first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are located on their respective vertical portions 212. The second curved plate 182 is L-shaped. In contrast, the first curved plate 180 may have a recess 214 that partially forms the vertical portion 212 by removing at least a portion of its circumferential extension 210. However, this arrangement for the first curved plate 180 is not necessary in all cases, meaning that the arrangement may also be L-shaped. In Figures 6-7, the vertical portions 212 of the first curved plate 180 and the second curved plate 182 extend axially, i.e., in the X direction, with respect to the axis of the turbine section 116 and their respective circumferential extension portions 210. Thus, the first curved plate 180 and the second curved plate 182 can be nested together in the axial direction. As will be explained, although not necessary in all cases, the first curved plate 180 and the second curved plate 182 may slide in contact with each other along at least a portion of their lengths (L1, L2) when the linear actuator 250 moves the first curved plate 180 and the second curved plate 182 relative to each other between the retracted position and the extended position (e.g., Figures 16B-16D and 17A-17D).

[0052] Figure 10 shows a perspective view of another option for the vertical portions 212 of the first curved plate 180 and / or the second curved plate 182. In this arrangement, the vertical portion 212 extends radially, i.e., in the Y direction, with respect to the axis of the turbine section 116 and its circumferential extension portion 210. The arrangement in Figure 10 may be advantageous if the space 160 has a sufficient radial range for the vertical portion 212 to extend radially, and if the portion 166 and the fixing element 188 (engaged by the first ends 184, 186 on the vertical portion 212) are not circumferentially engageable by the first ends 184, 186. For example, the portion 166 may be recessed in the first nozzle segment 124A, and / or the fixing element 188 may be recessed in the second nozzle segment 124B or the half-casing 150H. Although shown in Figure 10 as extending only in a specific radial direction (upwards the page), the vertical portion 212 may extend radially inward and / or radially outward, i.e., in either the Z direction, relative to the axis of the turbine section 116 and its circumferential extension portion 210. In any case, different embodiments of the vertical portion 212 described herein may be joined and aligned in any manner to provide the positions of the first end 184 of the curved plate 180 and the first end 186 of the curved plate 182, which are necessary to engage the portion 166 of the first nozzle segment 124A with the fixing element 188 of, for example, the portion 168 of the second nozzle segment 124B or the portion 194 of the half-casing 150H.

[0053] The tool 170 also includes a coupling 220 that connects a second end 222 of one of the first curved plate 180 (shown) and the second curved plate 182 to the base 172. The coupling 220 may include any currently known or hereafter developed mechanical connections. The coupling 220 may be coupled to the base 172 pivotally or non-pivotably using any solution, such as screw fasteners or welding. In the non-limiting example shown, the coupling 220 is pivotally coupled to the base 172. In certain embodiments, as shown in Figures 6-7, the coupler 220 includes a body 230, a first connector 232 at a first end 234 of the body 230 which pivotably connects the body 230 to a base 172, and a second connector 236 at a second opposing end 238 of the body 230 which pivotably connects the body 230 to a second end 222 of one of a first curved plate 180 (illustrated) and a second curved plate 182. More specifically, the coupler 220 is pivotably connected to the base 172 using the first connector 232 having a threaded eyelet 240. A threaded pin 242 of the base 172 (Figure 7) extends through an opening in the threaded eyelet 240 at the end of the coupler 220 into which a bolt (not labeled) is screwed. Similarly, the coupler 220 may be pivotably or non-pivotably coupled to the second end 222 of the curved plate 180 using any solution. In the non-limiting illustrated example, the coupler 220 is coupled to the curved plate 182 at the second end 238 of the body 230 by a second connector 236 including a threaded eyelet 244. The pin 246 connects the threaded eyelet 244 to the bifurcated end 248 of the second end 222 of the curved plate 180.

[0054] In certain embodiments, the body 230 of the coupling 220 may be length-adjustable, which may be provided in any currently known or future-developed manner. In the illustrated example, the length of the body 230 may be adjusted using a threaded connector 249 (e.g., a bolt) that screws into threaded eyelets 240 on opposing ends of the body 230. The coupling 220 may be length-adjustable for initial setup of the tool 170, but as will be further described, it will likely be recognized that it is not length-adjustable during use of the tool 170, in contrast to the linear actuator 250. That is, the coupling 220 may be length-adjustable, for example, to correspond to setting a desired position of the first curved plate 180 relative to the base 172, in which case the coupling 220 remains at its fixed length during use of the tool 170. While exemplary connectors for the coupling 220 have been described, it will be recognized that a wide variety of alternative connectors and body configurations for the coupling 220 are possible and are considered to be within the scope of this disclosure.

[0055] The tool 170 also includes a linear actuator 250 between the base 172 and the other second end 252 of the first curved plate 180 and the second curved plate 182 (shown). The linear actuator 250 may include any currently known or hereafter developed actuator for linearly moving the selected, mounted curved plate 182. In certain embodiments, as shown, the linear actuator 250 may include a hydraulic ram 254. The linear actuator 250 may alternatively include a pneumatic or electric ram or a length-adjustable mechanical structure, the latter of which are further described herein.

[0056] A linear actuator 250, for example, a hydraulic ram 254, may be fixedly or pivotally coupled to the base 172 using any solution, such as a screw fastener or welding. For example, in the non-limiting examples shown in Figures 5 to 7, the linear actuator 250 is fixedly coupled to the base 172 using a first connector 256 in the form of a screw fastener, such as a screw bolt threaded through the base 172 to the end of the linear actuator 250. Similarly, a linear actuator 250, for example, a hydraulic ram 254, may be fixedly coupled to the second end 252 of the second curved plate 182 using any solution. In the non-limiting examples shown, the linear actuator 250 is coupled to the second curved plate 182 using a second connector 258, for example, which includes a screw fastener threaded to the end of the linear actuator 250. Therefore, the linear actuator 250 includes at least one of a first connector 256 at a first end that fixes and connects the linear actuator 250 to the base 172, or a second connector 258 at a second opposing end that fixes and connects the linear actuator 250 to the second end 252 of the second curved plate 182. Other forms of connectors for the linear actuator 250 to the base 172 and the second curved plate 182 are possible.

[0057] Figure 11 shows a bottom view of the tool 170 according to another embodiment of the present disclosure. In Figure 11, the positions of the coupler 220 and the linear actuator 250 are reversed, with the coupler 220 coupled to the second end 252 of the second curved plate 182 and the linear actuator 250 coupled to the second end 222 of the first curved plate 180. In addition, in Figure 11, the coupler 220 is replaced by a non-pivot connection to the base 172 and the second curved plate 182. In a non-limiting example, the coupler 220 may include a bar or member 259 of non-adjustable length, welded at its end 238 to the second end 252 of the second curved plate 182 and at its end 234 to the base 172. Other non-adjustable length couplers 220 are also possible and are considered to be within the scope of the present disclosure. In Figure 11, the linear actuator 250 includes a turnbuckle 260 held by a connection portion 262 to the second end 222 and base 172 of the first curved plate 180. The connection portion 262 can take any form, including a threaded eyelet connection similar to that shown in Figure 7. Other forms of the linear actuator 250 are also possible and are considered to be within the scope of this disclosure.

[0058] Figure 12 shows a bottom view of the tool 170 according to an additional embodiment of the present disclosure. In Figure 12, the positions of the coupler 220 and the linear actuator 250 are reversed, as in Figure 11, with the coupler 220 coupled to the second end 252 of the second curved plate 182 and the linear actuator 250 coupled to the second end 222 of the first curved plate 180. In addition, as in Figure 11, the coupler 220 is replaced at the non-pivot connection between the base 172 and the second curved plate 182 as a non-adjustable length bar or member 259, for example, welded at its end 238 to the second end 252 of the curved plate 182 and welded at its end 234 to the base 172. In Figure 12, the linear actuator 250 is held by a pin connection 265 to the second end 222 of the first curved plate 180 and includes a length-adjustable threaded member 264 extending through an opening 267 in the base 172, the head 269 of the threaded member 264 being rotatably adjusted, for example, using a screwdriver or hex head for rotational adjustment, to adjust the length of the linear actuator 250. The connection 265 to the second end 222 of the first curved plate 180 can take any form, including a pin connection similar to that shown in Figure 7. As described above, other forms of the linear actuator 250 are also possible and are considered to be within the scope of this disclosure.

[0059] In any of the embodiments described herein, the dimensions of the curved plates 180, 182 may be configured for use with any step 165 (Figures 3, 4, 9, 17C) of the turbine section 116 (Figures 1-2) in which the tool 170 is used. For example, as shown in Figures 6-9 and above, the first curved plate 180 and the second curved plate 182 include a radially inward-facing surface 200 and a radially outward-facing surface 202. The surfaces 200, 202 are curved and have an axial width W1 (Figures 6 and 8) such that the curved plates 180, 182 can be positioned axially (in / out of the page of Figure 9) within the space 160, as will be further described. Although the axial width W1 of the curved plates 180, 182 is shown as equal, this is not necessary in all cases, as long as the curved plates 180, 182 can be positioned axially within the space 160 in the manner described herein. The curved plates 180 and 182 also have a radial thickness R configured to allow positioning within space 160. T (Figure 8) is also included. As shown in Figure 6, the first curved plate 180 and the second curved plate 182 also have lengths L1 and L2, respectively, configured to allow positioning within the space 160 and engagement of portion 166 with the fixed element 188, as described herein. Lengths L1 and L2 are also configured to position the base 172 outside the nozzle segments 124A and B. The curved plates 180 and 182 also have a radius of curvature RC1 (Figures 8 and 9) that matches the radius of curvature RC2 (Figure 9) of the space 160 between the half-casing 150H and the radially outer ends 162 of the nozzle segments 124A and 124B in a particular stage 165 (Figures 3, 4, 9, and 17C) of the turbine section 116 (Figures 1 and 2). As used herein, "matching" or "match" when applied to radii of curvature RC1, RC2 indicates that the curved plates 180, 182 can move circumferentially within space 160 with a clearance sufficient to avoid snagging or obstruction until they are positioned where the tool 170 is required to operate.

[0060] The dimensions of the curved plates 180 and 182 can be customized or configured in several ways. More specifically, the axial width W1 (Figures 6 and 8) and radial thickness R of each curved plate 180 and 182. T The radius of curvature RC1, and / or the length L1, L2 of each curved plate 180, 182 may be sized to correspond to the configuration of any space 160 and / or section 166 and fixing element 188. In contrast to conventional separation tools, the axial width W1 (Figures 6 and 8) is the radial thickness R T Since it is larger than the radius of curvature RC1 (Figures 8 and 9) and the relatively thin radial thickness R T (Figure 8) allows the curved plates 180 and 182 to be positioned in a space 160 of substantially any size in different steps 165, regardless of whether or not the insulating layer 164 (Figure 4) is present. In addition, the radius of curvature RC1 and the relatively thin radial thickness R TTherefore, the lengths L1, L2 of the curved plates 180, 182 and the overall circumferential reach of the tool 170 can be set to any desired extent, which increases the applicability of the tool 170 to a wider variety of smaller spaces 160 in different stages 165. Thus, the tool 170 can be applied to a wider variety of component segments 102A, 102B of different sizes, such as nozzle segments 124A, 124B, which have different circumferential ranges, for example, more or fewer airfoil sections 158. Customization of the lengths L1, L2 of the curved plates 180, 182 also allows the tool 170 to provide more options regarding which part of the component segment 102 or half-casing 150H is used for engagement by the curved plates 180, 182. Tool 170 may also include, for example, different sets of curved plates 180, 182 having different dimensions to correspond to different arrangements of the portion 166 of the first component segment 102A and the fixing element 188 in a given stage 165, different stages 165 in a given turbine section 116 (Figures 1-2), different turbine sections 116 (Figures 1-2) in a given turbine system 100 (Figure 1), and / or different turbine systems 100 (Figure 1).

[0061] Figure 13 shows a bottom perspective view of the tool 170 according to another embodiment of the present disclosure. Figure 13 shows an example of changing the dimensions of the curved plates 180, 182. In this example, the fixed element 188 includes a second component segment 102B, e.g., a portion 168 of the second nozzle segment 124B, which is further circumferentially from the base 172 than in the other drawings. In this case, the second curved plate 182 may be configured to extend the first end 186 further circumferentially than in the other drawings. For this purpose, the second curved plate 182 may include a first circumferential portion 270 including a second end 252 (coupled to a linear actuator 250), a second circumferential portion 272 including the first end 186, and an axial extension portion 274 connecting the first circumferential portion 270 and the second circumferential portion 272. Here, the axial extension portion 274 positions the first end portion 186 axially, and the second circumferential portion 272 further extends the second curved plate 182 circumferentially to engage with the fixed element 188, i.e., portion 168 of the second component segment 102B. Otherwise, the second curved plate 182 in Figure 13 may be dimensioned as described herein. For example, the first curved plate 180 may be nested with the second curved plate 182 as previously described.

[0062] Figure 14 shows a bottom perspective view of tool 170 according to another embodiment of the present disclosure. Figure 14 shows another example of changing the dimensions of the curved plates 180, 182. In some cases, one or both of the curved plates 180, 182 may be out of their radial position or may be difficult to position radially within space 160, for example, between a portion 166 of the first component segment 102A and a fixing element 188 of the second component segment 102B or half-casing 150H. To address this situation, tool 170 may optionally further include at least one radial spacer 268 on the radially outward-facing surface 202 of one or both of the curved plates 180, 182. The radial spacers 268 are configured to position the respective curved plates 180, 182 in a radial position where their first ends 184, 186 are located between a portion 166 of the first component segment 102A and a fixing element 188 of the second component segment 102B or half-casing 150H. The radial spacers 268 may slidably engage with the surface of the half-casing 150H or the insulating layer 164 thereon (Figure 4) to radially position the curved plates 180, 182 as described above. The radial spacers 268 may be positioned and sized as needed, which may depend, for example, on the radial size or radius of curvature RC2 of the space 160 (Figure 9), the radial position of the portion 166 of the first component segment 102A and the fixing element 188 of the second component segment 102B or half-casing 150H, among other factors. Although not shown, the radial spacer 268 can also be positioned on the radially inward-facing surface 200 of one or both of the curved plates 180, 182, or on both the radially inward-facing surface 200 and the radially outward-facing surface 202 of the curved plates 180, 182.

[0063] Figure 14 also shows the tool 170 including the axial spacer member 280. Figure 15 shows a perspective view of the tool 170 having the axial spacer member 280. The axial spacer member 280 may be used in cases where additional axial positioning is required in the space 160, such as by other means, for example by manual operation by the user, so that the curved plates 180, 182 remain between portion 166 of the first component segment 102A (nozzle segment 124A) and the fixed element 188 (portion 168 of the second component segment 102B (nozzle segment 124B) or portion 194 of the half-casing 150H). The axial spacer member 280 may include a (third) curved plate 282 having an axial width W2, configured to axially position (hold) the first curved plate 180 and the second curved plate 182 at a working position on a step (165) (Figures 3, 4, 9, and 17C) of the turbine section 116 (Figures 1-2) located between a portion 166 of the first component segment 102A and a fixed element 188, with the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 being the working position. The third curved plate 282 may have the same or similar radius of curvature RC3 (Figure 14) as the curved plates 180 and 182. The axial spacer member 280 may optionally include a handle 284 for positioning the curved plate 282 in space 160 and / or manipulating it to axially position the curved plates 180 and 182. As shown in Figure 15, the third curved plate 282 may interact with one of the curved plates 180, 182 (182 is shown) on one of its axial sides 286. As shown in Figures 16D and 17D, the third curved plate 282 may interact with any other (possibly circumferentially extending) structure 290 in space 160 that can define a limiting restraint for axial movement on its opposing axial side 288. The structure 290 may include, for example, the circumferentially extended surface of an adjacent step 165 or its constituent segment 102.

[0064] Next, with reference to Figures 16A-16D and 17A-17D, a method for separating the first and second adjacent nozzle segments 124A-B (or component segments 102A-B) in the (half)casing 150 of the turbine system 100 will be described. Figures 16A-16D show various bottom views of the tool 170 before separating the first nozzle segment 124A and the second nozzle segment 124B, and Figures 17A-17D show various views of the tool 170 after separating the first nozzle segment 124A and the second nozzle segment 124B.

[0065] Figure 16A shows the circumferential positioning of the first curved plate 180 and the second curved plate 182 of the separation tool 170 along the first and second adjacent nozzle segments 124A-B. The first curved plate 180 and the second curved plate 182 are in the first retracted position in this setup, i.e., the linear actuator 250 brings the first ends 184 and 186 of the curved plates 180 and 182 close to each other when they are not in contact with each other. As described above, the first curved plate 180 includes a first end 184 for the engagement portion 166 of the first nozzle segment 124A and a second end 222 coupled to the base 172 of the separation tool 170, i.e., by the coupling 220. Furthermore, the second curved plate 182 includes a first end 186 for engaging with a fixing element 188 of the second nozzle segment 124B or half-casing 150H, and a second end 252 coupled to the base 172 by a linear actuator 250. For illustrative purposes, in Figures 16A–16D and 17A–17D, the fixing element 188 is shown as a portion 168 of the second nozzle segment 124B. In Figure 16A, the first curved plate 180 and the second curved plate 182 are positioned axially so as not to engage with the nozzle segments 124A, 124B, so as to be able to move circumferentially to desired positions within space 160.

[0066] Figures 16B to 16D show that the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are axially positioned between the portion 166 of the first nozzle segment 124A and the fixing element 188, regardless of the shape of the fixing element 188. In this configuration, the first curved plate 180 and the second curved plate 182 remain in their first retracted position. When the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 reach a circumferential position where they can be circumferentially positioned between the portion 166 of the first nozzle segment 124A and the fixing element 188, the curved plates 180 and 182 are moved axially so that the first ends 184 and 186 can be circumferentially positioned between the portion 166 of the first nozzle segment 124A and the fixing element 188. As shown in Figure 16D, the axial spacer member 280 can be optionally used in the space 160 such that the curved plates 180, 182 remain between portion 166 of the first component segment 102A (nozzle segment 124A) and the fixed element 188 (portion 168 of the second component segment 102B (nozzle segment 124B) (shown) or portion 194 of the half-casing 150H (Figure 9)) if additional axial positioning beyond what is available by other means, for example, manual operation by the user, may be required. The curved plate 282 of the axial spacer member 280 axially positions (holds) the first curved plate 180 and the second curved plate 182 in working positions at the step (165) of the turbine section 116 (Figures 1-2), where the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are located between the portion 166 of the first component segment 102A and the fixed element 188. As described herein, a single operator can perform the two positioning steps of the tool 170.

[0067] Figures 17A to 17D show that the linear actuator 250 is actuated to move the first plate 180 and the second plate 182 relative to each other between a first retracted position (Figures 16B to 16D) in which the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are retracted close to each other, for example, when they are not in contact, and a second extended position in which the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are separated from each other in such a way that the first nozzle segment 124A and the second nozzle segment 124B are forcibly separated (see force F). In the illustrated configuration, the first curved plate 180 functions as a tension member on the first component segment 102A (nozzle segment 124A) to separate the first component segment 102A (nozzle segment 124A) from the second component segment 102B (nozzle segment 124B), for example, the second component segment 102B and / or the support structure 156. Similarly, the second curved plate 182 functions as a pressing member on the fixed element 188 to separate the first component segment 102A, as described. Figures 17A to 17D show the nozzle segments 124A and 124B (component segments 102A and 124B) with a circumferential space 300 between them. In the illustrated configuration, the linear actuator 250 is extended to apply a force F to linearly move the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 away from each other. As described above, the first curved plate 180 and the second curved plate 182 can slide in contact with each other along at least a portion of their lengths (L1, L2 (Figure 6)) when the linear actuator 250 moves the first curved plate 180 and the second curved plate 182 relative to each other between the retracted position and the extended position. The linear actuator 250 can be extended in any manner depending on its configuration, for example, by operating a hydraulic ram, a pneumatic ram or an electric ram, or by lengthening a turnbuckle.When the axial spacer member 280 is used, as shown in Figure 17D, its curved plate 282 axially holds the first curved plate 180 and the second curved plate 182 in an operating position where the first end 184 of the first curved plate 180 and the first end 186 of the second curved plate 182 are between portion 166 of the first component segment 102A and the fixed element 188. Regardless of the form of the linear actuator 250 used, a single operator can actuate the linear actuator 250 of the tool 170 as described herein.

[0068] The first curved plate 180 has a first end 184 that engages with a portion 166 of the first component segment 102A, and the second curved plate 182 has a first end 186 that engages with a fixed element 188, and it will be recognized that the positions of the curved plates 180 and 182 can be switched. That is, as described with respect to Figures 11 and 12, the first curved plate 180 and the second curved plate 182 can be switched in position and function.

[0069] Embodiments of this disclosure offer various technical and commercial advantages, examples of which are discussed herein. For example, the tool applies separation force in a safe manner away from any sensitive structures such as airfoils. In addition, the tool reduces the required disassembly time by not requiring external access to the casing for operation and not requiring two or more operators. Furthermore, the tool is highly customizable for applicability in different situations.

[0070] Throughout this specification and the claims, the approximation language may be applied to modify any quantitative expression that may vary to a reasonable extent without altering the fundamental function of the expression. Thus, values ​​modified by terms such as “approximately,” “about,” and “substantially” are not limited to the exact values ​​specified. In at least some cases, the approximation language may correspond to the precision of the instrument used to measure the value. Here, and throughout this specification and the claims, range limitations may be combined and / or interchangeable, and unless the context or wording indicates otherwise, such ranges are identified and include all subranges encompassed therein. “Approximately” or “about” applied to specific values ​​within a range may indicate + / - 10% of the stated value, unless applied to the values ​​at both ends and particularly dependent on the precision of the instrument used to measure that value.

[0071] All means or step-plus-function elements in the following claims are intended to include any structures, materials, or actions for performing a function in combination with other claimed elements specifically claimed. The descriptions in this disclosure are presented for illustrative and explanatory purposes and are not intended to be exhaustive or to limit the disclosure to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. The embodiments have been selected and described to best illustrate the principles of this disclosure and the practical applications of the art, and to enable those skilled in the art to understand this disclosure in order to consider various modifications to these embodiments that may be suitable for the particular use under consideration. [Explanation of Symbols]

[0072] 100 Turbine System 102 Component Segments 102A First component segment 102B Second component segment 112 Compressor Section 114 Combustor Section 116 Turbine Section 118 shaft 120 High-temperature gas pathway 122 Shroud Segments 124 nozzle segments 124A First nozzle segment 124B Second nozzle segment 126 Turbine rotor blade segments 128 First Stage Nozzle Assembly 130 First Stage Blade Assembly 131 First Stage Shroud Assembly 132 Second Stage Nozzle Assembly 134 Second Stage Blade Assembly 135 Second Stage Shroud Assembly 136 Third Stage Nozzle Assembly 138 Third Stage Blade Assembly 139 Third Stage Shroud Assembly 150 Fixed Turbine Casing 150H Half Casing 152A Inside end wall 152B Inside end wall 154A Outer end wall 154B Outer end wall 156 Support structure 158 Airfoil 159 End 160 Space 162 Radial outer end 164 Insulator layer, insulating layer 165 steps 166 parts 168 parts 170 Tools 172 Base 180 First curved plate, first plate 182 Second curved plate, second plate 184 First end 186 First end 188 fixed elements 192 Fixing member 194 parts 200 Radially inward-facing surface 202 Radially outward-facing surface 210 Circumferential extension 212 Vertical section 214 recess 220 Combiner 222 Second end 230 Main Unit 232 First connector 234 First end 236 Second connector 238 Second opposing end, second end 240 Screw eyelets 242 Screw pins 244 Screw eyelets 246 pins 248 Bifurcated end 249 Screw connection part 250 Linear Actuators 252 Second end, second opposite end 254 Hydraulic Ram 256 First connector 258 Second connector 259 Bars or components that cannot be adjusted in length 260 Turnbuckle 262 Connection part 264 Adjustable length screw member 265-pin connector 267 Opening 268 Radial Spacer 269 ​​heads 270 First circumferential portion 272 Second circumferential portion 274 Axial extension 280 Axial spacer member 282 Third curved plate 284 Handle 286 Axial side 288 Opposing axial side 290 Structure 300 circumferential space W1 Axial width W2 Axial width R T Radial thickness RC1 radius of curvature RC2 radius of curvature RC3 radius of curvature F separation force

Claims

1. A tool (170) for separating a first component segment (102A) from a second component segment (102B) adjacent to the first component segment (102A) in a stage (165) of a turbine section (116), wherein the tool (170) Base (172) and, A first curved plate (180) including a first end (184) configured to engage with a portion (166) of the first component segment (102A), A second curved plate (182) including a first end (186) configured to engage a fixed element (188), wherein the fixed element (188) includes at least one portion (168) of the second component segment (102B) and the half-casing (150H) of the turbine section (116), A coupling device (220) that connects one of the first curved plate (180) and the second curved plate (182) to the base (172), A linear actuator (250) between the base (172) and the other second end (222) of the first curved plate (180) and the second curved plate (182) and A tool (170) comprising a linear actuator (250) that moves the first curved plate (180) and the second curved plate (182) linearly relative to each other between a first position in which the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182) are retracted, and a second position in which the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182) extend a certain distance from each other, forcibly separating the first component segment (102A) and the second component segment (102B).

2. The tool (170) according to claim 1, wherein the first component segment (102A) and the second component segment (102B) each include nozzle segments (124A, 124B), and the first curved plate (180) and the second curved plate (182) have a radius of curvature that matches the radius of curvature of the space (160) between the casing (150) and the radial outer surfaces of the nozzle segments (124A, 124B) in the stage (165) of the turbine section (116).

3. The tool (170) according to claim 1, wherein the linear actuator (250) includes a hydraulic ram (254).

4. The tool (170) according to claim 1, further comprising an axial spacer member (280) including a third curved plate (282) having an axial width, configured such that the first curved plate (180) and the second curved plate (182) are held in working positions in the stage (165) of the turbine section (116) between the portion (166) of the first component segment (102A) and the fixed element (188), with the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182).

5. The tool (170) according to claim 1, wherein the other of the first curved plate (180) and the second curved plate (182) has a first circumferential portion (270) including a second end (252), a second circumferential portion (272) including the first end (186), and an axial extension portion (274) connecting the first circumferential portion (270) and the second circumferential portion (272).

6. The tool (170) according to claim 1, wherein each of the first curved plate (180) and the second curved plate (182) includes a circumferential extension portion (210) and a vertical portion (212) extending perpendicularly to the circumferential extension portion (210), and the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182) are located on the vertical portion (212).

7. The tool (170) according to claim 6, wherein the vertical portion (212) extends axially with respect to the axis of the turbine section (116).

8. The tool (170) according to claim 6, wherein the vertical portion (212) extends radially inward with respect to the axis of the turbine section (116).

9. The tool (170) according to claim 1, wherein the coupling (220) includes a body (230), a first connector (232) at a first end (234) of the body (230) that pivotably connects the body (230) to the base (172), and a second connector (236) at a second opposing end (238) of the body (230) that pivotably connects the body (230) to one of the second ends (222) of the first curved plate (180) and the second curved plate (182).

10. The tool (170) according to claim 9, wherein the main body (230) is length-adjustable.

11. The tool (170) according to claim 9, wherein the linear actuator (250) includes at least one of a first connector (256) at a first end (234) for fixing and coupling the linear actuator (250) to the base (172), and a second connector (258) at a second opposing end (252) for fixing and coupling the linear actuator (250) to the other second end (222) of the first curved plate (180) and the second curved plate (182).

12. The tool (170) according to claim 1, wherein the first curved plate (180) and the second curved plate (182) include a radially inward-facing surface (200) and a radially outward-facing surface (202), and the tool (170) further comprises at least one radial spacer (268) on the radially outward-facing surface (202) configured to position each curved plate (180, 182) at a radial position where the first end (184, 186) is between a portion (194) of the first component segment (102A) and the fixing element (188).

13. The tool (170) according to claim 1 further comprises a fixing member (192) configured to lock the position of the second component segment (102B) relative to the casing (150).

14. The tool (170) according to claim 1, wherein the first curved plate (180) and the second curved plate (182) slide in contact with each other along at least a portion of their length when the linear actuator (250) moves the first curved plate (180) and the second curved plate (182) relative to each other between the first position and the second position.

15. A tool (170) for separating a first nozzle segment (124A) from a second nozzle segment (124B) adjacent to the first nozzle segment (124A) in a stage (165) of a turbine section (116), wherein the tool (170) Base (172) and, A first curved plate (180) including a first end (184) configured to engage with a portion (166) of the first nozzle segment (124A), A second curved plate (182) including a first end (186) configured to engage a fixed element (188), wherein the fixed element (188) includes at least one portion (168) of the second nozzle segment (124B) and the half-casing (150H) of the turbine section (116), A coupling device (220) that connects one of the first curved plate (180) and the second curved plate (182) to the base (172), A linear actuator (250) between the base (172) and the other second end (222) of the first curved plate (180) and the second curved plate (182) and A tool (170) comprising a linear actuator (250) that moves the first curved plate (180) and the second curved plate (182) linearly relative to each other between a first position in which the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182) are retracted, and a second position in which the first end (184) of the first curved plate (180) and the first end (186) of the second curved plate (182) extend a certain distance from each other, forcing the first nozzle segment (124A) and the second nozzle segment (124B) to separate.

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