Search

EP-4737693-A1 - SEPARATION TOOL FOR COMPONENT SEGMENT OF TURBINE SYSTEM

EP4737693A1EP 4737693 A1EP4737693 A1EP 4737693A1EP-4737693-A1

Abstract

A tool (170) for separating adjacent component segments (102A, 102B) in a stage (165) of a turbine section (116) is disclosed. The tool (170) includes a base (172) and first and second curved plates (180, 182). The first plate (180) includes a first end (184) to engage a portion (166) of a component segment (102A), and the second plate (182) includes a first end (186) to engage a fixed element (188), such as the other 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 between the base (172) and the second plate (182). The linear actuator (250) linearly moves the second plate (182) between a first position in which the first ends (184, 186) of the first and second plates (180, 182) are retracted and a second position in which the first ends (184, 186) of the first and second plates (180, 182) are extended a distance from one another to force the adjacent component segments (102A, 102B) to separate.

Inventors

  • MACHOWSKI, Marek
  • SAJDAK, Lukasz
  • KORUS, MATEUSZ

Assignees

  • GE Vernova Technology GmbH

Dates

Publication Date
20260506
Application Date
20251007

Claims (15)

  1. A tool (170) for separating a first component segment (102A) from a second component segment (102B) adjacent the first component segment (102A) in a stage (165) of a turbine section (116), the tool (170) comprising: a base (172); a first curved plate (180) including a first end (184) configured to engage 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), the fixed element (188) including a portion (168) of at least one of the second component segment (102B) and a half casing (150H) of the turbine section (116); a coupler (220) coupling a second end (222) of one of the first and second curved plates (180, 182) to the base (172); and a linear actuator (250) between the base (172) and a second end (222) of the other one of the first and second curved plates (180, 182), wherein the linear actuator (250) linearly moves the first and second curved plates (180, 182) relative to one another between a first position in which the first ends (184, 186) of the first and second curved plates (180, 182) are retracted and a second position in which the first ends (184, 186) of the first and second curved plates (180, 182) are extended a distance from one another to force the first and second component segments (102A, 102B) to separate.
  2. The tool (170) of claim 1, wherein 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 matching a radius of curvature of a space (160) between the casing (150) and a radial outer surface of the nozzle segments (124A, 124B) at the stage (165) of the turbine section (116).
  3. The tool (170) of claim 1, wherein the linear actuator (250) includes a hydraulic ram (254).
  4. The tool (170) of claim 1, further comprising an axial spacer member (280) including a third curved plate (282) having an axial width configured to hold the first and second curved plates (180, 182) in an operative position in the stage (165) of the turbine section (116) with the first ends (184, 186) of the first and second curved plates (180, 182) between the portion (166) of the first component segment (102A) and the fixed element (188).
  5. The tool (170) of claim 1, wherein the other one of the first and second curved plates (180, 182) has a first circumferential portion (270) including the second end (252) thereof, a second circumferential portion (272) including the first end (186) thereof, and an axial-extending portion (274) coupling the first and second circumferential portions (270,272).
  6. The tool (170) of claim 1, wherein each of the first and second curved plates (180, 182) include a circumferential-extending portion (210) and a perpendicular portion (212) extending perpendicular to the circumferential-extending portion (210), wherein the first end (184, 186) of the first and second curved plates (180, 182) is located on the perpendicular portion (212) thereof.
  7. The tool (170) of claim 6, wherein the perpendicular portion (212) extends in an axial direction relative to an axis of the turbine section (116).
  8. The tool (170) of claim 6, wherein the perpendicular portion (212) extends in a radially inward direction relative to an axis of the turbine section (116).
  9. The tool (170) of claim 1, wherein the coupler (220) includes a body (230), a first connector (232) at a first end (234) of the body (230) pivotally coupling the body (230) to the base (172), and a second connector (236) at a second, opposite end (238) of the body (230) pivotally coupling the body (230) to the second end (222) of the one of the first and second curved plates (180, 182).
  10. The tool (170) of claim 9, wherein the body (230) is a length-adjustable.
  11. The tool (170) of claim 9, wherein the linear actuator (250) includes at least one of a first connector (256) at a first end (234) thereof fixedly coupling the linear actuator (250) to the base (172) and a second connector (258) at a second, opposite end (252) thereof fixedly coupling the linear actuator (250) to the second end (222) of the other one of the first and second curved plates (180, 182).
  12. The tool (170) of claim 1, wherein the first and second curved plates (180, 182) include a radially-inward facing surface (200) and a radially-outward facing surface (202), and further comprising at least one radial spacer (268) on the radially-outward facing surface (202) configured to position the respective curved plate (180, 182) in a radial position with the first end (184, 186) thereof between the portion (194) of the first component segment (102A) and the fixed element (188).
  13. The tool (170) of claim 1, further comprising a fixing member (192) configured to lock a position of the second component segment (102B) relative to the casing (150).
  14. The tool (170) of claim 1, wherein the first curved plate (180) and the second curved plate (182) slide in contact with one another along at least part of a length thereof as the linear actuator (250) moves the first and second curved plates (180, 182) relative to one another 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 the first nozzle segment (124A) in a stage (165) of a turbine section (116), the tool (170) comprising: a base (172); a first curved plate (180) including a first end (184) configured to engage 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), the fixed element (188) including a portion (168) of at least one of the second nozzle segment (124B) and a half casing (150H) of the turbine section (116); a coupler (220) coupling a second end (22) of one of the first and second curved plates (180, 182) to the base (172); and a linear actuator (250) between the base (172) and a second end (222) of the other one of the first and second curved plates (180, 182), wherein the linear actuator (250) linearly moves the first and second curved plates (180, 182) relative to one another between a first position in which the first ends (184, 186) of the first and second curved plates (180, 182) are retracted and a second position in which the first ends (184, 186) of the first and second curved plates (180, 182) are extended a distance from one another to force the first and second nozzle segments (124A, 124B) to separate.

Description

TECHNICAL FIELD The disclosure relates generally to turbine systems and, more particularly, to a separation tool to separate adjacent component segments, such as nozzle segments, in preparation for removing the segments from the casing of the turbine section for repair or replacement. BACKGROUND A turbine system extracts energy from a flow of a working fluid, e.g., hot combustion gases, steam, water, etc., for producing output power for an external load such as an electrical generator and the like. In one example, a gas turbine (GT) system extracts energy from a flow of hot combustion gases. The GT system includes a compressor for compressing ambient air and a combustor for mixing the flow of air with a flow of fuel to generate hot combustion gases. A turbine section (e.g., an expansion turbine) receives the flow of hot combustion gases and extracts energy therefrom for powering the compressor and for producing output power for the external load. The hot gas components such as the turbine nozzles and blades positioned along the hot gas path of a GT system are subject to not only high temperatures and pressures but also different types of dynamic forces. Other turbine systems, e.g., steam or water turbines, experience similar environmental conditions on their working fluid components. Given such environments, these components may be replaced and/or refurbished on a periodic basis to ensure efficient and safe performance of the turbine system. Removal of a component such as a nozzle and the like may be difficult and time consuming. Each stage of the components in a turbine section typically may be formed in segments that are placed circumferentially end-to-end to form a continuous ring within a half casing of the turbine section. The extreme environments, such as high temperature and high-pressure, may cause the component segments to stick together and/or to be seized in the supporting structure. The small clearances in the turbine section, e.g., such as between a radial outer end of nozzle segments and insulation within a half casing of the turbine section, provide very little space to access the component segments or to apply any type of force to separate the component segments prior to removal. One approach to separate the component segments applies a force to the more readily accessible parts, such as airfoils, of the component segments. However, this approach increases the probability of damaging the reusable and perhaps more sensitive parts, such as airfoils of a nozzle segment. Another approach uses a tool between the casing and one of the component segments to apply a force to remove the component segments, but this approach requires access from outside the casing and two operators - one person in the casing and one outside the casing - to properly use. BRIEF DESCRIPTION All aspects, examples and features mentioned below can be combined in any technically possible way. An aspect of the disclosure provides a tool for separating a first component segment from a second component segment adjacent 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 a portion of the first component segment; a second curved plate including a first end configured to engage a fixed element, the fixed element including a portion of at least one of the second component segment or a 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 a second end of the other one of the first and second curved plates, wherein the linear actuator linearly moves the first and second curved plates relative to one another between a first position in which the first ends of the first and second curved plates are retracted and a second position in which the first ends of the first and second curved plates are extended a distance from one another to force the first and second component segments to separate. Another aspect of the disclosure includes any of the preceding aspects, and the first and second component segments each include a nozzle segment, and the first and second curved plates have a radius of curvature matching a radius of curvature of a space between the casing and a radial outer surface of the nozzle segments at the stage of the turbine section. Another aspect of the disclosure includes any of the preceding aspects, and the linear actuator includes a hydraulic ram. Another aspect of the disclosure includes any of the preceding aspects, and further comprising an axial spacer member including a third curved plate having an axial width configured to hold the first and second curved plates in an operative position in the stage of the turbine section with the first ends of the first and second curved plates between the portion of the first component segment and the fixed element. Another aspect of the disclosure includes any of