EP3332097B1 - Ensemble d'alignement de structure de système de turbine - Google Patents

Ensemble d'alignement de structure de système de turbine Download PDF

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Publication number
EP3332097B1
EP3332097B1 EP15759959.8A EP15759959A EP3332097B1 EP 3332097 B1 EP3332097 B1 EP 3332097B1 EP 15759959 A EP15759959 A EP 15759959A EP 3332097 B1 EP3332097 B1 EP 3332097B1
Authority
EP
European Patent Office
Prior art keywords
support leg
base
turbine
assembly
jack assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15759959.8A
Other languages
German (de)
English (en)
Other versions
EP3332097A1 (fr
Inventor
Adrian Adam KLEJC
Thomas Michael MERLAU
Kenneth Damon Black
Stuart Craig Hanson
Sean Cornelius O'meara
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP3332097A1 publication Critical patent/EP3332097A1/fr
Application granted granted Critical
Publication of EP3332097B1 publication Critical patent/EP3332097B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding

Definitions

  • the subject matter disclosed herein relates to turbine systems and, more particularly, to an alignment assembly for turbine system structures, as well as a method of aligning turbine system structures.
  • a turbine such as an industrial gas turbine engine, is supported by a base or foundation that often includes beams that the turbine rests on.
  • one or more axial beams extending along a longitudinal direction of the turbine are included.
  • the turbine requires alignment while disposed on the base and the alignment assemblies and methods are designed based on the presence of axial beams and cross beams.
  • the axial beam(s) may be removed from certain base assemblies, such as those that support large gas turbine engines where external equipment limits the available space for such beams.
  • Bases that do not include axial beams impose challenges associated with alignment of the turbine. This is due to the introduction of twisting issues when the forward or aft end of the turbine is moved independently. Space for tooling that is required to perform alignment operations is limited, particularly in areas where leg supports at the forward and/or aft end of the turbine are present.
  • An example is shown in the patent application US-2010/218508 .
  • an alignment assembly includes a base and a support leg extending from the base, the leg configured to support a portion of a turbine system structure. Also included is a first support leg portion disposed on a surface of the base and coupleable thereto. Further included is a second support leg portion angularly oriented relative to the first support leg portion and coupleable to the turbine system structure. Yet further included is a jack assembly moveable on the surface of the base and configured to vertically and laterally adjust the turbine. The alignment further comprises at least one low friction plate disposed on the surface of the base to provide slideable adjustment of the jack assembly.
  • an alignment assembly includes a base and a support leg extending from the base, the support leg configured to support a portion of a turbine system structure. Also included is a jack assembly disposed in a recess defined by the support leg in a repeatedly removable manner, the jack assembly configured to engage the portion of the turbine for vertical and lateral adjustment thereof.
  • a method of aligning a turbine includes placing a portion of the turbine on at least one support leg extending from a base. The method also includes coupling the turbine to the at least one support leg. The method further includes disposing a jack assembly on the base. The method yet further includes laterally sliding the jack assembly to a position proximate the turbine with at least one low friction plate. The method also includes vertically adjusting the turbine with the jack assembly. The method further includes laterally adjusting the turbine with the jack assembly.
  • a portion of a turbine such as a gas turbine engine 10 is shown in a supported condition.
  • a gas turbine engine any type of turbomachine, such as a steam turbine, for example, may benefit from the embodiments described herein. Additionally, a generator may similarly benefit from the embodiments described herein.
  • a gas turbine engine will be referenced throughout.
  • the portion of the gas turbine engine 10 is an end portion of the turbine and the embodiments described herein are applicable to both the forward end region and the aft end region of the gas turbine engine 10.
  • the gas turbine engine is supported by a alignment assembly 12 that forms a portion of a foundation that is secured to the ground.
  • the alignment assembly 12 is configured to support and adjust the position of the gas turbine engine 10 in a reliable and convenient manner.
  • the alignment assembly 12 includes a base 14 that is part of a larger overall foundation that generally supports the entire gas turbine engine 10.
  • the base may be formed of any geometry and extends vertically from a ground surface.
  • the base includes a surface 16 that is suited to allow an operator to comfortably perform alignment operations at a suitable height. In one embodiment, the surface 16 is located at approximately a height that corresponds to an average human's waist.
  • a support leg 18 is disposed on the surface 16 and extends therefrom. In one embodiment, the support leg 18 is disposed directly on the surface 16, such that direct contact is made between the support leg 18 and the surface 16. In another embodiment, one or more intervening components may be disposed between the support leg 18 and the surface 16, thereby disposing the support leg 18 in indirect contact with the surface 16.
  • the support leg 18 includes a first support leg portion 20 and a second support leg portion 22.
  • the first support leg portion 20 is disposed on the surface 16 of the base 14 in the direct or indirect manner described above.
  • the first support leg portion 20 is configured to be coupled to the base 14 in any suitable manner.
  • one or more mechanical fasteners 21 are employed to couple the support leg 18 to the base 14.
  • the second support leg portion 22 is oriented at an angle to the first support leg portion 20 and is configured to at least partially support the end region of the gas turbine engine 10 in a coupled or uncoupled manner.
  • the support leg 18 comprises a substantially L-shaped geometric orientation based on a relative angle of about 90 degrees between the first support leg portion 20 and the second support leg portion 22.
  • a single leg portion is provided.
  • a jack assembly 24 is provided to vertically adjust the end region of the gas turbine engine 10.
  • the jack assembly 24 rests on the surface 16 of the base 14, however, it is to be appreciated that the jack assembly 24 may rest on another component that is disposed on the surface 16 of the base 14.
  • the jack assembly 24 is moveable on the surface 16 to facilitate convenient maneuvering of the jack assembly 24 to obtain desired position relative to the end region of the gas turbine engine 10.
  • one or more low friction plates 26 are disposed between the jack assembly 24 and the base 14. This allows the jack assembly 24 to be adjusted by simply sliding the jack assembly.
  • the support leg 18 is vertically adjusted by removing or inserting one or more shims 28 between the first support leg portion 20 and the surface 16 of the base 14.
  • the jack assembly 24, while supporting the gas turbine engine 10 is conveniently slid in a non-vertical manner via the low friction plate(s) 26. This allows the end region of the gas turbine engine to be adjusted in a horizontal plane to align the end region in a desirable orientation in all three axes. Lateral motion with the jack assembly 24 may be imparted by any suitable motion inducing assembly or system that is an external or internal assembly or system.
  • the jack assembly 24 may be removed.
  • lateral adjustment of the support leg 18 and the gas turbine engine 10 is permitted by the alignment assembly 12, as discussed above.
  • the support leg 18 is moveable relative to the base 14 for lateral adjustment that includes axial adjustment, transverse adjustment and combinations thereof.
  • the support leg 18 is coupled to the base 14 in a manner that allows a degree of lateral adjustment of the support leg 18, thereby allowing lateral adjustment of the gas turbine engine 10.
  • a final coupling of the support leg 18 to the base 14 is performed. In one embodiment, this includes positioning a brace 30 in abutment with the support leg 18 and coupling the brace 30 to both the support leg 18 and the base 14 with mechanical fasteners 31 or the like, as shown in the illustrated embodiment.
  • the turbine alignment assembly 40 includes a base 42 and a support leg 44 extending therefrom in a coupled manner. As with the embodiments described above, the support leg 44 is configured to support a portion of the turbine, such as the forward end region or the aft end region. However, it is to be appreciated that the alignment assembly 40 may be positioned in alternative locations depending upon the particular structure being adjusted (e.g., steam turbine, generator, etc.).
  • the support leg 44 defines a recess 46 that provides an access region for a jack assembly 48 to be repeatedly inserted and removed therein.
  • the jack assembly 48 and the recess 46 each include respective portions that are of a geometry which corresponds to the other component to provide at least partial insertion of the jack assembly 48 within the recess 46.
  • coupling of the jack assembly 48 to the base 42 is made to secure the position of the jack assembly 48.
  • the jack assembly 48 then vertically adjusts the gas turbine engine 10 in the manner described above in conjunction with the other embodiments.
  • the jack assembly 48 may be left in place to maintain the desired vertical position or may be removed subsequent to the insertion of shims or the like to maintain the vertical position.
  • the jack assembly 48 also includes one or more sliding plates 50 that facilitate lateral movement of the structure being aligned.
  • the sliding plate(s) 50 may be located on top of the jack assembly 48 to be in direct contact with an engagement surface of the structure to be adjusted or may be beneath the jack assembly 48. Regardless of the position of the sliding plate(s) 50, lateral adjustment of the structure is achieved in a convenient manner.
  • the sliding plate(s) 50 may be formed of a low friction material, such as Teflon or may be a ball bearing assembly. Alternative materials or assemblies are contemplated, such that friction is reduced or controlled if required, thereby rendering lateral movement of the structure convenient.
  • the embodiments of the turbine alignment assembly described herein advantageously provide convenient and reliable adjustment of a portion of the gas turbine engine 10 in both vertical and lateral directions. Such adjustment is otherwise cumbersome due to the lack of adequate space for necessary equipment. By essentially splitting the forward or aft leg, such space is provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Ensemble d'alignement comprenant :
    une base (14) ;
    une patte de support (18) s'étendant à partir de la base (14), la patte (18) étant conçue pour supporter une partie d'une structure de système de turbine ;
    une première partie de patte de support (20) disposée sur une surface de la base (14) et pouvant être couplée à celle-ci ;
    une deuxième partie de patte de support (22) orientée angulairement par rapport à la première partie de patte de support (20) et pouvant être couplée à la structure de système de turbine ; et
    un ensemble de vérin (24) mobile sur la surface de la base (14) et configuré pour ajuster verticalement et latéralement la structure de système de turbine,
    caractérisé en ce qu'il comprend au moins une plaque à faible frottement (26) disposée sur la surface de la base pour assurer un ajustement coulissant de l'ensemble de vérin (24).
  2. Ensemble d'alignement selon la revendication 1, dans lequel la patte de support est mobile par rapport à la base pendant l'ajustement latéral de la structure de système de turbine.
  3. Ensemble d'alignement selon la revendication 1, comprenant en outre au moins une cale (28) disposée entre la patte de support et la base.
  4. Ensemble d'alignement selon la revendication 1, comprenant en outre une entretoise (30) en butée avec la patte de support et couplée à celle-ci, l'entretoise étant également couplée à la base.
  5. Ensemble d'alignement selon la revendication 1, dans lequel la partie de la structure de système de turbine supportée par la patte de support comprend une région d'extrémité avant d'un moteur à turbine à gaz.
  6. Ensemble d'alignement selon la revendication 1, dans lequel la partie de la structure de système de turbine supportée par la patte de support comprend une région d'extrémité arrière d'un moteur à turbine à gaz.
  7. Ensemble d'alignement selon la revendication 1, comprenant en outre une pluralité de pattes de support.
  8. Ensemble d'alignement selon la revendication 1, dans lequel la structure de système de turbine comprend l'un d'un moteur à turbine à gaz, d'un moteur à turbine à vapeur et d'un générateur.
  9. Procédé d'alignement de turbine consistant à :
    fournir l'ensemble d'alignement selon l'une quelconque des revendications 1 à 8 ;
    placer une partie de la turbine sur au moins une patte de support s'étendant à partir d'une base ;
    coupler la turbine à l'au moins une patte de support ;
    disposer un ensemble de vérin sur la base ;
    faire coulisser latéralement l'ensemble de vérin vers une position proche de la turbine avec au moins une plaque à faible frottement ;
    ajuster verticalement la turbine avec l'ensemble de vérin ;
    ajuster latéralement la turbine avec l'ensemble de vérin.
  10. Procédé selon la revendication 9, consistant en outre à faire coulisser l'au moins une patte de support par rapport à la base pour ajuster latéralement la turbine.
  11. Procédé selon la revendication 9, consistant en outre à coupler l'au moins une patte de support à la base.
  12. Procédé selon la revendication 9, consistant en outre à placer l'ensemble de vérin sur la base et dans un évidement délimité par l'au moins une patte de support.
  13. Procédé selon la revendication 9, consistant en outre à placer au moins une cale entre l'au moins une patte de support et la base après l'ajustement vertical de la turbine à l'aide de l'ensemble de vérin.
EP15759959.8A 2015-08-06 2015-08-06 Ensemble d'alignement de structure de système de turbine Active EP3332097B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/PL2015/050032 WO2017023181A1 (fr) 2015-08-06 2015-08-06 Ensemble d'alignement de structure de système de turbine

Publications (2)

Publication Number Publication Date
EP3332097A1 EP3332097A1 (fr) 2018-06-13
EP3332097B1 true EP3332097B1 (fr) 2020-01-29

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Application Number Title Priority Date Filing Date
EP15759959.8A Active EP3332097B1 (fr) 2015-08-06 2015-08-06 Ensemble d'alignement de structure de système de turbine

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EP (1) EP3332097B1 (fr)
WO (1) WO2017023181A1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7779540B2 (en) * 2005-08-12 2010-08-24 United Technologies Corporation Apparatus and method for quadrail ergonomic assembly
US8590151B2 (en) * 2006-06-30 2013-11-26 Solar Turbines Inc. System for supporting and servicing a gas turbine engine
DK2434141T3 (en) * 2010-09-24 2016-02-01 Siemens Ag A device for handling a wind turbine component

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
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Also Published As

Publication number Publication date
WO2017023181A1 (fr) 2017-02-09
EP3332097A1 (fr) 2018-06-13

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