A separation tool and method for a shroud segment with insulation for a gas turbine

Abstract

A tool (100) and method for separating shield sections (402, 404) in a turbine. The tool (100) includes: a stabilizing member (202); a pair of arms (200A, 200B), each arm (200A, 200B) having a first end and a second end, wherein the first end of each arm (200A, 200B) is pivotally connected to the stabilizing member (202); a pivoting member (218A, 218B) extending from the second end of each arm (200A, 200B); a linear actuator pivotally connected at a central portion of each respective arm (200A, 200B) between the pair of arms (200A, 200B); and a pair of transfer plates (210A, 210B), each transfer plate (210A, 210B) pivotally connected to a corresponding pivoting member (218A, 218B).

Description

Technical Field

[0001] This disclosure relates generally to turbine systems. More specifically, this disclosure relates to a turbine shroud section separation device. Background Technology

[0002] Conventional turbines, such as those in gas turbine systems, are used to generate power for generators. Generally, a gas turbine system generates power by passing a fluid (e.g., hot gas) through a compressor and turbine components. More specifically, inlet air can be drawn into the compressor and compressed. Once compressed, the inlet air is mixed with fuel to form combustion products, which can be ignited by the gas turbine system's burner to form the working fluid (e.g., hot gas) of the gas turbine system. The fluid can then flow through fluid flow channels to rotate multiple rotating blades and a shaft in the turbine components to generate power. The fluid can be directed through the turbine components via multiple rotating blades and multiple fixed nozzles positioned between the blades. As the multiple rotating blades rotate the shaft of the gas turbine system, a generator coupled to the shaft can generate electricity from the rotation of the shaft.

[0003] Conventional gas turbine systems typically include multiple shroud stages positioned within the turbine housing. More specifically, multiple shroud stages may be coupled to the turbine housing and may be positioned adjacent to the tips of the rotating blades and / or between the stator nozzles of the gas turbine system. The shroud stages may surround the individual stages of the rotating blades and stator nozzles of the gas turbine system and may form the outer boundary of the working fluid flowing through the gas turbine system during operation.

[0004] The turbine shield stage can be removed when performing maintenance on the gas turbine system or when making adjustments to various components of the gas turbine system. For example, when maintaining or adjusting the rotating blades, stator nozzles, and / or the shield block itself, the shield stage can be removed to allow the turbine operator access to, maintain, and / or adjust specific components. Summary of the Invention

[0005] All aspects, examples, and features mentioned below can be combined in any technically possible way.

[0006] One aspect of this disclosure provides a tool for separating a shield section in a turbine, the tool comprising: a stabilizing member; a pair of arms, each arm having a first end and a second end, wherein the first end of each arm is pivotally connected to the stabilizing member; a pivoting member extending from the second end of each arm; a linear actuator pivotally coupled between the pair of arms at a central portion of each respective arm; and a pair of transfer plates, each transfer plate being pivotally coupled to a corresponding pivoting member.

[0007] Another aspect of this disclosure provides a method for separating shield sections in a turbine. The method includes providing a tool comprising: a stabilizing member; a pair of arms, each arm having a first end and a second end, wherein the first end of each arm is pivotally connected to the stabilizing member; a pivoting member extending from the second end of each arm; and a linear actuator pivotally coupled between the pair of arms at a central portion of each respective arm; a pair of transfer plates, each transfer plate pivotally coupled to a corresponding pivoting member; mounting the pair of transfer plates to two adjacent shield sections; coupling the pivoting member to the pair of transfer plates; and deploying the linear actuator to radially separate the pair of transfer plates and separate adjacent shield sections.

[0008] Another aspect of this disclosure includes any of the foregoing aspects, and wherein the pair of transfer plates are configured to releasably engage with adjacent shield sections.

[0009] Another aspect of this disclosure includes any of the foregoing aspects, and wherein the pair of transfer plates includes retaining pins for releasably engaging with retaining holes in adjacent shroud sections.

[0010] Another aspect of this disclosure includes any of the foregoing aspects, and wherein each pivot member includes a circular insert, and each transfer plate includes a complementary circular opening that engages with the circular insert of the corresponding pivot member, and wherein at least two retaining pins include a pair of retaining pins.

[0011] Another aspect of this disclosure includes any of the foregoing aspects, and wherein the circular insert and the pair of retaining pins each have a center point, wherein the center point of the circular insert is substantially linearly aligned with the center point of the pair of retaining pins.

[0012] Another aspect of this disclosure includes any of the foregoing aspects, and wherein each arm includes a first connecting element that pivotally connects a first end of the arm to an end of a stabilizing member.

[0013] Another aspect of this disclosure includes any of the foregoing aspects, and wherein each arm includes a second connecting element for pivotally connecting a central portion of the arm to an end of a linear actuator.

[0014] Another aspect of this disclosure includes any of the foregoing aspects, and also includes at least one gasket configured to retain the pair of transmission plates relative to the turbine housing ribs of the turbine.

[0015] Another aspect of this disclosure includes any of the foregoing aspects, wherein each transfer plate includes an outer edge extending beyond the second end of the corresponding arm.

[0016] Another aspect of this disclosure includes any of the foregoing aspects, wherein the linear actuator includes a hydraulic cylinder comprising a connector for receiving compressed fluid, wherein the compressed fluid causes the hydraulic cylinder to extend and radially move the pair of transfer plates to separate adjacent shield sections.

[0017] Two or more aspects described in this disclosure (including those described in this overview section) can be combined to form specific embodiments not specifically described herein. That is, all embodiments described herein can be combined with each other.

[0018] Details of one or more specific embodiments are set forth in the following figures and description. Other features, objects, and advantages will be apparent from the specification, figures, and claims. Attached Figure Description

[0019] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure, taken in conjunction with the accompanying drawings depicting various embodiments thereof, in which:

[0020] Figure 1 A turbine housing with a shield section separation tool according to an embodiment of the present disclosure is shown;

[0021] Figure 2 A top perspective view of a shield segment separation tool according to an embodiment of the present disclosure is shown;

[0022] Figure 3 A bottom perspective view of a shield segment separation tool according to an embodiment of the present disclosure is shown;

[0023] Figure 4 A top perspective view of a shield section separation tool connected to a shield section according to an embodiment of the present disclosure is shown;

[0024] Figure 5 A transfer plate installed in a turbine housing according to an embodiment of the present disclosure is shown;

[0025] Figure 6 A shield section separation tool installed in a turbine housing according to an embodiment of the present disclosure is shown;

[0026] Figure 7 The illustration shows a gasket installed in the turbine housing together with the shield section separation tool according to an embodiment of the present disclosure; and

[0027] Figure 8 It is a tool for separating the protective cover section.

[0028] It should be noted that the accompanying drawings of this disclosure are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and should therefore not be considered as limiting the scope of this disclosure. In the drawings, similar numbers denote similar elements between figures. Detailed Implementation

[0029] First, in order to clearly describe the subject matter of the present art, it will be necessary to select certain terms when referring to and describing relevant machine components in illustrative applications of turbine sections. In doing so, common industry terms will be used and adopted in a manner consistent with their accepted meanings, where possible. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that several different or overlapping terms may generally be used to refer to a particular component. An object that can be described herein as a single part may include multiple components and is referred to in another context as being composed of multiple components. Alternatively, an object that can be described herein as comprising multiple components may elsewhere be referred to as a single part.

[0030] Furthermore, several descriptive terms may be used regularly throughout this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as through the working fluid of a turbine, or, for example, through the airflow of a combustor or through the coolant of one of the turbine's component systems. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the direction opposite to the flow. Without any other particularity, the terms “front” and “rear” refer to directions, where “front” refers to the front end of the turbine or compressor end, and “rear” refers to the rear end of the turbine or turbine end.

[0031] It is often necessary to describe parts positioned radially relative to a central axis. The term "axial" refers to movement or positioning parallel to an axis (e.g., the axis of a micromixer tube). The term "radial" refers to movement or positioning perpendicular to an axis (e.g., the axis of a micromixer tube). In such cases, if a first part resides closer to the axis than a second part, this document will state that the first part is "radially inward" or "inner" of the second part. On the other hand, if the first part resides further away from the axis than the second part, this document may state that the first part is "radially outward" or "outer" of the second part. Finally, the term "circumferential" refers to movement or positioning about an axis (e.g., about the circumferential inner surface of a micromixer tube). As noted above, it should be understood that such terms can be applied relative to the axis of a turbine.

[0032] In addition, several descriptive terms may be used regularly in this document, as described below. 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 a single component.

[0033] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that, when used in the specification, the terms “comprising” and / or “including” specify the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or groups thereof. “Optional” or “optionally” means that the events subsequently described may or may not occur, or the features subsequently described may or may not be present, and the description includes instances where the events occur or the features are present and instances where the events do not occur or the features are not present.

[0034] When an element or layer is referred to as “on another element or layer,” “joined to another element or layer,” “connected to another element or layer,” “linked to another element or layer,” or “mounted to another element or layer,” it may be directly on, joined to, connected to, linked to, or mounted to another element or layer, or an intermediary element or layer may be present. In contrast, when an element is referred to as “directly on another element or layer,” “directly joined to another element or layer,” “directly connected to another element or layer,” or “directly coupled to another element or layer,” no intermediary element or layer is present. Other terms used to describe the relationship between elements should be interpreted in a similar manner (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items. The verb forms “join” and “mount” are used interchangeably herein.

[0035] Embodiments of this disclosure provide a tool and associated method for separating a shield section in a turbine housing. Figure 1A turbine housing 110 with three shield stages is shown, including a first stage 102, a second stage 104, and a third stage 106. As shown, each stage includes a series of shield segments mounted along the curved inner surface of the housing 110. Removing the shield segments from the housing 110 can be challenging because the segments in each stage may become stuck together and / or melt into the housing 110 over time due to factors such as high operating temperatures. Significant forces must be applied to separate the individual shield segments, and care must be taken not to cause damage. Furthermore, because each shield segment has a curved profile to mate with the curved inner surface of the housing 110, additional friction is applied when attempting to remove the segments using lateral separation forces. To address this issue, a tool 100 is provided, which is configured to separate adjacent shield segments to facilitate their removal.

[0036] Figure 2 A detailed top perspective view of an exemplary tool 100 is shown, which typically includes: a pair of arms 200A, 200B, each arm having a first end pivotally connected to an opposing end of a stabilizing member 202 (e.g., a rigid rod, etc.) and a second end connected to (or having) pivoting members 218A, 218B; a linear actuator 206 (e.g., a hydraulic cylinder) pivotally coupled between the pair of arms 200A, 200B at the central portion of each respective arm; and a pair of transfer plates 210A, 210B, each transfer plate being rotatably coupled to a corresponding pivoting member 218A, 218B. In the illustrated exemplary embodiment, the pair of arms 200A, 200B are pivotally connected to the stabilizing member 202 using first connecting elements 212A and 212B (e.g., shafts, cotter pins, bushings, and / or other connecting mechanisms). Similarly, the linear actuator 206 includes opposing cylinder ends pivotally connected to arms 200A, 200B via second connecting elements 214A and 214B (e.g., shafts, cotter pins, bushings, and / or other connecting mechanisms). As shown, the linear actuator 206 (in this case, a hydraulic cylinder) includes a connector 204 for connection to a pressurized fluid source (not shown). As understood in the art, a hydraulic cylinder is a mechanical device that uses pressurized hydraulic fluid to generate linear motion, essentially by pushing or pulling a load within a cylinder barrel, thereby generating force along a straight line. In other embodiments, alternative devices performing similar functions (e.g., threaded rods, pneumatic cylinders, screw threads, etc.) may be used instead of hydraulic cylinders.

[0037] As described in further detail herein, the transfer plates 210A, 210B are configured to releasably engage with the turbine housing 110. Figure 1The adjacent shield sections (not shown) within the linear actuator 206. When the linear actuator 206 is deployed, the pair of arms 200A, 200B swing apart about the first connecting elements 212A, 212B, pushing the transfer plates 210A, 210B open. Each pivot member 218A, 218B includes a circular insert 216 that engages with a complementary circular opening 217 in the corresponding transfer plate 210A, 210B, allowing each transfer plate 210A, 210B to rotate, for example, about the circular insert 216 in a hinged manner. Thus, when the linear actuator 206 is linearly deployed, the transfer plates 210A, 210B rotate apart to substantially follow the curved profile of the inner surface of the shield section / housing 110.

[0038] A set of gaskets 208 is also shown, which can be placed on top of transfer plates 210A, 210B as needed to hold tool 100 within housing 110 during shield separation. This process will be referenced... Figure 7 and Figure 8 Further detailed description.

[0039] Figure 3 A detailed bottom perspective view of tool 100 is shown. As shown, the underside of transfer plates 210A, 210B includes a pin 300 configured to engage (i.e., releasably connect) existing holes (i.e., retaining holes) in adjacent shroud sections. In some embodiments, each transfer plate includes a pair of retaining pins for engaging a pair of retaining holes. However, it should be understood that the number of pins and holes may vary depending on the specific shroud construction. In some aspects, on each transfer plate 210A, 210B, the circular insert 216 and the retaining pin 300 each have substantially aligned center points, which reduces torque on the retaining pin 300 when the shroud sections separate. Furthermore, it should be understood that transfer plates 210A, 210B can be configured for a specific shroud stage in a specific turbine. Thus, different transfer plate sizes and configurations can be provided for different shroud sizes and constructions. Therefore, transfer plates 210A, 210B are releasably connected to pivot members 218A, 218B, for example, by slidable engagement, snap-fit, etc.

[0040] Figure 4A tool 100 is shown attached to adjacent shield sections 402, 404. During operation, when the linear actuator 206 is deployed, its end abuts against second connecting elements 214A, 214B pivotally connected to the central portion of each arm 200A, 200B, causing the arms 200A, 200B to rotate outward about first connecting elements 212A, 212B. When the transfer plates 210A, 210B are forced apart, pivoting members 218A, 218B allow the transfer plates to rotate, simultaneously separating adjacent shield sections 402, 404. Thus, the separation force is essentially radial, substantially matching the curved profile 407 of the shield. The radial separation force more effectively separates adjacent shield sections 402, 404, thereby enabling these sections to also engage with the sealing plate 409 located below the shield sections (see [link to documentation]). Figure 5 It separates without causing undue damage.

[0041] Figures 5 to 8 An image is shown illustrating a method of separating the protective section within the housing 110 using tool 100. First, as... Figure 5 As shown, transfer plates 210A and 210B are inserted and connected to adjacent shield sections 402 and 404. Specifically, retaining pins 300 (not shown) located on the underside of transfer plates 210A and 210B are placed into existing retaining holes 406 on the top of adjacent shields 402 and 404 below housing rib 408. Next, as... Figure 6 As shown, the circular inserts 216 of the pivot elements 218A and 218B slide, insert, or snap into the complementary circular openings 217 of the transfer plates 210A and 210B (partially obstructed in this view—see example...) Figure 2 As shown in the figure, a small gap may exist between the top surface of the transfer plate 210A and the bottom of the housing rib 408, which could cause the tool 100 to detach from the guard section. To solve this problem, as... Figure 7 As shown, one or more gaskets 208 can be placed above the transfer plates 210A, 210B and below the housing ribs 408 to eliminate gaps. This ensures that the tool 100 will be held tightly in place during the separation operation, allowing for operation by a single operator. Figure 8 As shown, when tool 100 is unfolded, the protective sections 402 and 404 can be easily separated.

[0042] Tool 100 and the related methods of using Tool 100 offer numerous technical and commercial advantages. Notably, the scissor-like design of Tool 100 provides radial force that substantially matches the curved profile of the inner surface of the shield section / housing 110, thus providing a more effective force for separating the shield section. Furthermore, due to the location of the housing rib 408, there is little space to access the existing hole 406 on the shield section. This design solves this problem by providing transfer plates 210A, 210B extending beyond the ends of arms 200A, 200B, which allow the transfer plates 210A, 210B to slide into the gap formed by the housing rib 408; that is, Tool 100 can be installed in a very limited space. Additionally, different transfer plate configurations can be used for different shield designs. Moreover, because the linear actuator 206 is positioned between the central portions of arms 200A, 200B, a large stroke sufficient to completely separate the shields of different types of gas turbines is achieved.

[0043] As used throughout the specification and claims, approximate language can be used to modify any quantitative expression that may be varied without causing a change in its underlying function. Therefore, a value modified by one or more terms (such as “about,” “approximately,” and “substantially”) is not limited to the specified precise value. In at least some instances, approximate language may correspond to the precision of the instrument used to measure the value. Herein and throughout the specification and claims, range limitations may be combined and / or interchanged; unless the context or language otherwise indicates, these ranges are identified and include all subranges contained therein. The term “about” or “approximately” applied to a specific value within a range applies to both ends of the range and, unless otherwise dependent on the precision of the instrument used to measure the value, may indicate + / - 10% of the stated value.

[0044] All means or steps plus functional elements in the following claims are intended to include any structure, material, action, and equivalent for performing a function in conjunction with other claimed elements of a particular claim. This disclosure has been given for purposes of illustration and description, but it is 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. Various embodiments have been selected and described in order to best explain the principles and practical application of the principles and techniques of this disclosure, and to enable others skilled in the art to understand this disclosure in order to consider various modifications of the embodiments suitable for the particular purpose contemplated.

Claims

1. A tool (100) for separating shield sections (402, 404) in a turbine, said tool (100) comprising: Stabilizing component (202); A pair of arms (200A, 200B), each arm (200A, 200B) having a first end and a second end, wherein the first end of each arm (200A, 200B) is pivotally connected to the stabilizing member (202). Pivoting members (218A, 218B) extending from the second end of each arm (200A, 200B); A linear actuator (206) is pivotally connected between the pair of arms (200A, 200B) at the central portion of each respective arm (200A, 200B); and A pair of transfer plates (210A, 210B), each transfer plate (210A, 210B) being pivotally connected to a corresponding pivot member (218A, 218B).

2. The tool (100) according to claim 1, wherein the pair of transfer plates (210A, 210B) are configured to releasably engage adjacent shield sections (402, 404).

3. The tool (100) of claim 2, wherein each transfer plate (210A, 210B) includes at least two retaining pins (300) for releasably engaging with at least two retaining holes (406) in a corresponding one of the adjacent shield sections (402, 404).

4. The tool (100) according to claim 3, wherein each pivot member (218A, 218B) comprises a circular insert (216), and each transfer plate (210A, 210B) comprises: A complementary circular opening (217) is connected to the circular insert (216) of the corresponding pivot member (218A, 218B), and wherein the at least two retaining pins (300) include a pair of retaining pins (300).

5. The tool (100) according to claim 4, wherein the circular insert (216) and the pair of retaining pins (300) each have a center point, wherein the center point of the circular insert (216) and the center point of the pair of retaining pins (300) are substantially linearly aligned.

6. The tool (100) of claim 1, wherein each arm (200A, 200B) includes a first connecting element that pivotally connects the first end of the arm (200A, 200B) to the end of the stabilizing member (202).

7. The tool (100) of claim 1, wherein each arm (200A, 200B) includes a second connecting element for pivotally connecting the central portion of the arm (200A, 200B) to an end of the linear actuator (206).

8. The tool (100) according to claim 1, the tool further comprising at least one gasket configured to retain the pair of transmission plates (210A, 210B) relative to the ribs of the turbine housing (110) of the turbine.

9. The tool (100) of claim 1, wherein each transfer plate (210A, 210B) includes an outer edge extending beyond the second end of the corresponding arm (200A, 200B).

10. The tool (100) of claim 1, wherein the linear actuator (206) includes a hydraulic cylinder including a connector (204) for receiving compressed fluid, wherein the compressed fluid causes the hydraulic cylinder to extend and radially move the pair of transfer plates (210A, 210B) to separate adjacent shield sections (402, 404).

11. A method for separating shroud sections (402, 404) in a turbine, the method comprising: Provide tools (100), said tools comprising: Stabilizing component (202); A pair of arms (200A, 200B), each arm (200A, 200B) having a first end and a second end, wherein the first end of each arm (200A, 200B) is pivotally connected to the stabilizing member (202). Pivoting members (218A, 218B) extending from the second end of each arm (200A, 200B); A linear actuator (206) is pivotally connected at the central portion of each respective arm (200A, 200B) between the pair of arms (200A, 200B); and A pair of transfer plates (210A, 210B), each transfer plate (210A, 210B) being pivotally connected to a corresponding pivot member (218A, 218B). The pair of transfer plates (210A, 210B) are installed onto two adjacent shield sections (402, 404); Connect the pivoting members (218A, 218B) to the pair of transfer plates (210A, 210B); and The linear actuator (206) is deployed to radially separate the pair of transfer plates (210A, 210B) and the adjacent shield sections (402, 404).

12. The method of claim 11, wherein the outer edges of the pair of transfer plates (210A, 210B) are mounted between the surfaces of the two adjacent shield sections (402, 404) and the ribs of the turbine housing (110).

13. The method of claim 12, further comprising inserting at least one gasket between the pair of transfer plates (210A, 210B) and the rib.

14. The method of claim 11, wherein the pair of transfer plates (210A, 210B) includes at least two retaining pins (300) for releasably engaging with corresponding retaining holes (406) in the adjacent shield sections (402, 404).

15. The method of claim 14, wherein Each pivot member (218A, 218B) includes a circular insert (216); Each transfer plate (210A, 210B) includes a complementary circular opening (217) which is connected to the circular insert (216) of the corresponding pivot member (218A, 218B). The at least two retaining pins (300) include a pair of retaining pins (300); and The circular insert (216) and the pair of pins (300) each have substantially aligned center points.

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