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KR-20260064548-A - SEPARATION TOOL FOR COMPONENT SEGMENT OF TURBINE SYSTEM

KR20260064548AKR 20260064548 AKR20260064548 AKR 20260064548AKR-20260064548-A

Abstract

A tool (170) for separating adjacent component segments (102A, 102B) at the stage (165) of the turbine section (116) is disclosed. The tool (170) comprises a base (172) and first and second curved plates (180, 182). The first plate (180) comprises a first end (184) that engages with a portion (166) of the component segment (102A), and the second plate (182) comprises a first end (186) that engages with a fixed element (188), such as another component segment (102B) or a half casing (150H) of the turbine section (116). A coupler (220) couples the first plate (180) to the base (172), and a linear actuator (250) is located between the base (172) and the second plate (182). The linear actuator (250) moves the second plate (182) linearly between a first position in which the first end (184, 186) of the first and second plates (180, 182) is retracted and a second position in which the first end (184, 186) of the first and second plates (180, 182) is extended by a predetermined distance from each other so as to forcibly separate the adjacent component segment (102A, 102B).

Inventors

  • 마초우스키, 마렉
  • 사쟉, 루카즈
  • 코러스, 마테우즈

Assignees

  • 지이 버노바 테크놀로지 게엠베하

Dates

Publication Date
20260507
Application Date
20251023
Priority Date
20241031

Claims (15)

  1. As a tool (170) for separating a first component segment (102A) from a second component segment (102B) adjacent to the first component segment (102A) at a stage (165) of a turbine section (116), the tool (170) is, Base (172); 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) comprising a first end (186) configured to engage with a fixed element (188) - the fixed element (188) comprises at least one part (168) of the second component segment (102B) and the half casing (150H) of the turbine section (116) -; A coupler (220) coupling the second end (222) of one of the first and second curved plates (180, 182) to the base (172); and It includes a linear actuator (250) located between the base (172) and the other second end (222) of the first and second curved plates (180, 182), and The linear actuator (250) is a tool (170) that moves the first and second curved plates (180, 182) linearly relative to each other between a first position in which the first end (184, 186) of the first and second curved plates (180, 182) is retracted and a second position in which the first end (184, 186) of the first and second curved plates (180, 182) is extended by a predetermined distance from each other to forcibly separate the first and second component segments (102A, 102B).
  2. In claim 1, the first and second component segments (102A, 102B) each include a nozzle segment (124A, 124B), and the first and second curved plates (180, 182) have a radius of curvature that matches the radius of curvature of the space (160) between the casing (150) and the radially outer surface of the nozzle segments (124A, 124B) in the stage (165) of the turbine section (116), a tool (170).
  3. In claim 1, the linear actuator (250) comprises a hydraulic ram (254), a tool (170).
  4. A tool (170) according to claim 1, further comprising an axial spacer member (280) including a third curved plate (282), wherein the third curved plate has an axial width configured to maintain the first and second curved plates (180, 182) in an operating position within the stage (165) of the turbine section (116) such that the first end (184, 186) of the first and second curved plates (180, 182) is between the part (166) of the first component segment (102A) and the fixed element (188).
  5. In claim 1, the other of the first and second curved plates (180, 182) has a first circumferential portion (270) including its second end (252), a second circumferential portion (272) including its first end (186), and an axial extension portion (274) coupling the first and second circumferential portions (270, 272), a tool (170).
  6. In claim 1, each of the first and second curved plates (180, 182) comprises a circumferential extension portion (210) and a vertical portion (212) extending perpendicularly to the circumferential extension portion (210), and the first end portion (184, 186) of the first and second curved plates (180, 182) is positioned on the vertical portion (212), a tool (170).
  7. In paragraph 6, the vertical portion (212) is a tool (170) that extends axially with respect to the axis of the turbine section (116).
  8. In paragraph 6, the vertical portion (212) is a tool (170) that extends radially inward with respect to the axis of the turbine section (116).
  9. A tool (170) comprising, in claim 1, a coupler (220) comprising a main body (230), a first connector (232) pivotally coupling the main body (230) to the base (172) at a first end (234) of the main body (230), and a second connector (236) pivotally coupling the main body (230) to a second end (222) of one of the first and second curved plates (180, 182) at a second opposite end (238) of the main body (230).
  10. In paragraph 9, the above main body (230) is a length-adjustable tool (170).
  11. In claim 9, the tool (170) comprises at least one of a first connector (256) that fixedly couples the linear actuator (250) to the base (172) at its first end (234) and a second connector (258) that fixedly couples the linear actuator (250) to the other second end (222) of the first and second curved plates (180, 182) at its second opposite end (252).
  12. A tool (170), wherein the first and second curved plates (180, 182) comprise a surface (200) facing radially inward and a surface (202) facing radially outward, and further comprises at least one radial spacer (268) on the surface (202) facing radially outward, wherein the radial spacer is configured to position each of the curved plates (180, 182) in a radial position such that its first end (184, 186) is between the part (194) of the first component segment (102A) and the fixed element (188).
  13. A tool (170) further comprising a fixing member (192) configured to lock the position of the second component segment (102B) with respect to the casing (150) in the first paragraph.
  14. A tool (170) wherein, when the linear actuator (250) moves the first and second curved plates (180, 182) relative to each other between the first position and the second position, 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.
  15. As a tool (170) for separating a first nozzle segment (124A) from a second nozzle segment (124B) adjacent to the first nozzle segment (124A) at a stage (165) of a turbine section (116), the tool (170) is, Base (172); 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) comprising a first end (186) configured to engage with a fixed element (188) - the fixed element (188) comprises at least one part (168) of the second nozzle segment (124B) and the half casing (150H) of the turbine section (116) -; A coupler (220) for coupling the second end (22) of one of the first and second curved plates (180, 182) to the base (172); and It includes a linear actuator (250) located between the base (172) and the other second end (222) of the first and second curved plates (180, 182), and The linear actuator (250) is a tool (170) that moves the first and second curved plates (180, 182) linearly relative to each other between a first position in which the first end (184, 186) of the first and second curved plates (180, 182) is retracted and a second position in which the first end (184, 186) of the first and second curved plates (180, 182) is extended by a predetermined distance from each other to forcibly separate the first and second nozzle segments (124A, 124B).

Description

Separation Tool for Components of a Turbine System The present disclosure generally relates to a turbine system, and more specifically to a separation tool for separating adjacent component segments, such as a nozzle segment, during the process of removing a segment from the casing of a turbine section for repair or replacement. Turbine systems extract energy from the flow of a working fluid (e.g., hot combustion gases, steam, water, etc.) to produce output power for external loads, such as electric generators. In one example, a gas turbine (GT) system extracts energy from the flow of hot combustion gases. A GT system includes a compressor to compress ambient air and a combustor to mix the air flow with the fuel flow to produce hot combustion gases. A turbine section (e.g., an expansion turbine) receives the flow of hot combustion gases and extracts energy from it to power the compressor and produce output power for external loads. Hot gas components (e.g., turbine nozzles and blades) positioned along the hot gas path of a GT system are subjected to high temperatures and high pressures, as well as different types of dynamic forces. For example, other turbine systems, such as steam turbines or hydroelectric turbines, also experience similar environmental conditions in their working fluid components. In such environments, these components may be periodically replaced and/or modified to ensure the efficient and safe performance of the turbine system. Removing components such as nozzles can be difficult and time-consuming. Each stage of a component within a turbine section can typically be formed as segments arranged end-to-end circumferentially to form a continuous ring within the turbine section's half-casing. Due to extreme environments such as high temperature and high pressure, component segments may stick together or become trapped within the support structure. Small gaps within the turbine section (e.g., between the radially outer end of a nozzle segment and the insulation within the turbine section's half-casing) provide very narrow spaces to apply any type of force to access or separate the component segments before removal. One approach to separating component segments is to apply force to more accessible parts, such as the airfoil of the component segment. However, this approach increases the probability of damage to reusable and potentially more sensitive parts, such as the airfoil of the nozzle segment. Another approach is to apply force to remove a component segment using a tool between the casing and one of the component segments, but this approach requires access from outside the casing and requires two operators (one inside the casing and one outside the casing) to use properly. All modes, examples, and features mentioned below may be combined in any technically possible manner. 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 having a first end configured to engage with a portion of the first component segment; a second curved plate having a first end configured to engage with a fixed element, wherein the fixed element comprises at least one portion of the second component segment or the half casing of the turbine section; a coupler coupling a second end of one of the first and second curved plates to the base; and a linear actuator between the base and the other second end of the first and second curved plates, wherein the linear actuator moves the first and second curved plates linearly relative to each other between a first position in which the first end of the first and second curved plates is retracted and a second position in which the first end of the first and second curved plates is extended by a predetermined distance from each other to forcibly separate the first and second component segments. Another aspect of the present disclosure includes any of the preceding aspects, wherein the first and second component segments each include a nozzle segment, and the first and second curved plates have a radius of curvature that corresponds to the radius of curvature of the space between the casing and the radially outer surface of the nozzle segment in the stage of the turbine section. Other embodiments of the present disclosure include any of the prior embodiments, and the linear actuator includes a hydraulic ram. Another aspect of the present disclosure comprises any of the preceding aspects and further comprises an axial spacer member comprising a third curved plate, wherein the third curved plate has an axial width configured to maintain the first and second curved plates in an operating position within a stage of a turbine section with the first end of the first and second curved plates being between a portion of the first component segment and a fixed element. Another aspect of the presen