EP3332097A1 - Turbine system structure alignment assembly - Google Patents
Turbine system structure alignment assemblyInfo
- Publication number
- EP3332097A1 EP3332097A1 EP15759959.8A EP15759959A EP3332097A1 EP 3332097 A1 EP3332097 A1 EP 3332097A1 EP 15759959 A EP15759959 A EP 15759959A EP 3332097 A1 EP3332097 A1 EP 3332097A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- support leg
- base
- turbine
- assembly
- system structure
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 claims description 14
- 230000008878 coupling Effects 0.000 claims description 6
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 230000008901 benefit Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 3
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 TeflonĀ® Polymers 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000002783 friction material Substances 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000009877 rendering Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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.
- 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 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.
- 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.
- FIG. 1 is a side view of an alignment assembly according to a first embodiment of the invention, the turbine alignment assembly in a first operating condition;
- FIG. 1 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 may be 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.
- 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)
Abstract
Description
Claims
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/PL2015/050032 WO2017023181A1 (en) | 2015-08-06 | 2015-08-06 | Turbine system structure alignment assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3332097A1 true EP3332097A1 (en) | 2018-06-13 |
EP3332097B1 EP3332097B1 (en) | 2020-01-29 |
Family
ID=54064548
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15759959.8A Active EP3332097B1 (en) | 2015-08-06 | 2015-08-06 | Turbine system structure alignment assembly |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP3332097B1 (en) |
WO (1) | WO2017023181A1 (en) |
Family Cites Families (3)
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 |
-
2015
- 2015-08-06 EP EP15759959.8A patent/EP3332097B1/en active Active
- 2015-08-06 WO PCT/PL2015/050032 patent/WO2017023181A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
WO2017023181A1 (en) | 2017-02-09 |
EP3332097B1 (en) | 2020-01-29 |
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