EP3178771A1 - Brennkammerbaugruppenhebesysteme und verfahren zur verwendung davon zum montieren und demontieren von brennkammerbaugruppen - Google Patents

Brennkammerbaugruppenhebesysteme und verfahren zur verwendung davon zum montieren und demontieren von brennkammerbaugruppen Download PDF

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Publication number
EP3178771A1
EP3178771A1 EP16201231.4A EP16201231A EP3178771A1 EP 3178771 A1 EP3178771 A1 EP 3178771A1 EP 16201231 A EP16201231 A EP 16201231A EP 3178771 A1 EP3178771 A1 EP 3178771A1
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EP
European Patent Office
Prior art keywords
combustor assembly
lift arm
combustor
lift
engagement frame
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.)
Withdrawn
Application number
EP16201231.4A
Other languages
English (en)
French (fr)
Inventor
Sandra Beverly KOLVICK
Ansley Michelle HEARD
Thomas Alan MOGLE II
Michael Leon HELTON
SR Jason Dean LORGE
Lonnie Wood
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP3178771A1 publication Critical patent/EP3178771A1/de
Withdrawn legal-status Critical Current

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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
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
    • B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
    • B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
    • B66C1/62—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means comprising article-engaging members of a shape complementary to that of the articles to be handled
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts

Definitions

  • the subject matter disclosed herein relates to combustor assemblies and, more specifically, to apparatuses and methods for installing and removing combustor assemblies with respect to a gas turbine.
  • Gas turbines can include a compressor section, a combustion section, and a turbine section.
  • the compressor section pressurizes air flowing into the turbine.
  • the pressurized air discharged from the compressor section flows into the combustion section, which is generally characterized by a plurality of combustors.
  • Each of the plurality of combustors includes a combustion liner, which defines the combustion chamber of the combustor.
  • air entering each combustor is mixed with fuel and combusted within the combustion liner. Hot gases of combustion flow from the combustion liner through a transition piece to the turbine section of the gas turbine to drive the turbine and generate power
  • a gas turbine combustor mixes large quantities of fuel and compressed air and burns the resulting mixture.
  • Combustors for industrial gas turbines can include an annular array of cylindrical combustion "cans" in which air and fuel are mixed and combustion occurs. Compressed air from an axial compressor flows into the combustor. Fuel is injected through fuel nozzle assemblies that extend into each can. The mixture of fuel and air burns in a combustion chamber of each can. The combustion gases discharge from each can into a duct that leads to the turbine.
  • combustor assemblies designed for low emissions may include premix chambers and combustion chambers. Fuel nozzle assemblies in each combustor assembly inject fuel and air into the chambers of the can. A portion of the fuel from the nozzle assembly is discharged into the premix chamber of the can, where air is added to and premixed with the fuel. Premixing air and fuel in the premix chamber promotes rapid and efficient combustion in the combustion chamber of each can, and low emissions from the combustion. The mixture of air and fuel flows downstream from the premix chamber to the combustion chamber which supports combustion and under some conditions receives additional fuel discharged by the front of the fuel nozzle assembly. The additional fuel provides a means of stabilizing the flame for low power operation, and may be completely shut off at high power conditions.
  • Combustor assemblies need to be installed during the initial build of the gas turbine and may subsequently be removed during subsequent maintenance activities. However, to install, remove or re-install a combustor assembly, a significant amount of force may be required to properly lift, position, and/or align the combustor assembly with respect to the combustor assembly. Accordingly, alternative apparatuses and methods for installing and removing combustor assemblies with respect to a gas turbine would be welcome in the art.
  • a combustor assembly lift system comprises a lift arm comprising a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly.
  • a method for installing a combustor assembly on a turbomachine comprises disposing a combustor assembly lift system proximate the combustor assembly.
  • the combustor assembly lift system comprises a lift arm comprising a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly.
  • the method further comprises temporarily securing the combustor assembly engagement frame to the turbomachine, aligning and securing the combustor assembly with the turbomachine, and releasing the combustor assembly from the combustor assembly engagement frame.
  • a method for removing a combustor assembly from a turbomachine comprises disposing a combustor assembly lift system proximate the combustor assembly.
  • the combustor assembly lift system comprises a lift arm comprising a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly.
  • the method further comprises temporarily securing the combustor assembly engagement frame to the combustor assembly, and releasing the combustor assembly from the turbomachine and moving the combustor assembly lift system away from the turbomachine via one or more connections to the lift arm.
  • turbomachines such as gas turbines, aero-derivatives, or the like, burn a fuel and an air mixture during a combustion process to generate energy.
  • Figure 1 illustrates an example of a turbomachine 100.
  • the turbomachine 100 comprises an inlet plenum 105 that directs an airstream towards a compressor housed in a compressor casing 110.
  • the airstream is compressed and then discharged to a combustion system 115, where a fuel, such as natural gas, is burned to provide high-energy combustion gases, which drives the turbine section 120.
  • a fuel such as natural gas
  • the energy of the hot gases is converted into work, some of which is used to drive the compressor, with the remainder available for useful work to drive a load such as the generator, mechanical drive, or the like (none of which are illustrated).
  • an embodiment of the combustion system 115 may comprise at least one combustor assembly 20.
  • Some turbomachines 100 such as that illustrated in FIG. 2 , may comprise a plurality of combustor assemblies 20 disposed in an annular array around a central axis A.
  • combustor assemblies 20 can comprise one or more auxiliary systems 130 such as flame detection systems to monitor the flame burning in some of the combustor assemblies 20.
  • Such flame detection systems may be in the form of a flame scanner, a portion of which may be inserted within the combustor assembly 20.
  • Additional or alternative auxiliary systems 130 may similarly be incorporated into combustor assemblies 20 to monitor, control and/or impact one or more of the combustor assembly processes.
  • the combustor assembly 20 may generally include at least a combustion can 125 and potentially a substantially cylindrical combustion casing 22 secured to a portion of a gas turbine casing 24, such as a compressor discharge casing or a combustion wrapper casing.
  • a flange 26 may extend outwardly from an upstream end of the combustion casing 22.
  • the flange 26 may generally be configured such that an end cover assembly of a combustor assembly 20 may be secured to the combustion casing 22.
  • the flange 26 may define a plurality of flange holes 72 for attaching the end cover assembly to the combustion casing 22.
  • the combustor assembly 20 may also include an internal flow sleeve 28 and/or a combustion liner 30 substantially concentrically arranged within the flow sleeve 28.
  • the combustor assembly 20 may comprise a unibody combustor assembly 20 comprising the combustion can 125 and at least one of the flow sleeve 28 or combustion liner 30 connected to the combustion can 125 as a single pre-assembled structure, or the combustor assembly 20 may comprise an assembly where the combustion can 125, flow sleeve 28 and combustion liner 30 all connect directly to the turbomachine 100 such as to the turbine casing 24 (sometimes referred to as a combustion discharge casing or "CDC").
  • the flow sleeve 28 and the combustion liner 30 may extend, at their downstream ends, to a double walled transition duct, including an impingement sleeve 32 and a transition piece 34 disposed within the impingement sleeve 32.
  • the impingement sleeve 32 and the flow sleeve 28 may be provided with a plurality of air supply holes 36 over a portion of their surfaces, thereby permitting pressurized air from the compressor section 12 to enter the radial space between the combustion liner 30 and the flow sleeve 28.
  • the combustion liner 30 of the combustor assembly 20 may generally define a substantially cylindrical combustion chamber 38, wherein fuel and air are injected and combusted to produce hot gases of combustion. Additionally, the combustion liner 30 may be coupled at its downstream end to the transition piece 34 such that the combustion liner 30 and the transition piece 34 generally define a flow path for the hot gases of combustion flowing from each combustor assembly 20 to the turbine section 16 of the turbine assembly 10.
  • the transition piece 34 may be coupled to the downstream end of the combustion liner 30 with a seal 40 (e.g., a compression seal).
  • a seal 40 e.g., a compression seal
  • the seal 40 may be disposed at the overlapping ends of the transition piece 34 and combustion liner 30 to seal the interface between the two components.
  • a seal 40 may comprise a circumferential metal seal configured to be spring/compression loaded between inner and outer diameters of mating parts. It should be appreciated, however, that the interface between the combustion liner 30 and the transition piece 34 need not be sealed with a compression seal 40, but may generally be sealed by any suitable seal known in the art.
  • the combustion liner 30 may also include one or more male liner stops 42 that engage one or more female liner stops 44 secured to the flow sleeve 28 or, in combustor assemblies 20 without a flow sleeve 28, the combustion casing 22.
  • the male liner stops 42 may be adapted to slide into the female liner stops 44 as the combustion liner 30 is installed within the combustor assembly 20 to indicate the proper installation depth of the combustion liner 30 as well as to prevent rotation of the liner 30 during operation of the turbine assembly 10.
  • male liner stops 42 may be additionally or alternatively disposed on the flow sleeve 28 or combustion casing while the female liner stops 44 are disposed on the combustion liner 30.
  • the combustion liner 30 may first be installed within a combustor assembly 20, by being pushed into the combustor assembly 20.
  • the combustion liner 30 can be pushed into the combustor assembly 20 until a force limits further installation depth into the transition piece 34.
  • a combustion can 125 can then be installed into each respective combustor assembly 20.
  • the combustion can 125 can be positioned, aligned and inserted such that its end cover assembly abuts against the flange 26 of the combustor assembly 20.
  • the combustor assembly 20 may comprise a variety of different components that are assembled in a variety of different orders with respect to the individual connections made with the turbomachine 100.
  • the combustor assembly 20 may be completely assembled prior to installation onto the turbomachine 100 (e.g., a unibody combustor assembly 20), may be partly assembled prior to installation on the turbomachine 100, may be completely assembled while connected to the turbomachine 100, or combinations thereof.
  • a combustor assembly lift system 200 can be provided to help install, remove, or re-install the combustor assembly 20 onto the turbomachine 100.
  • the combustor assembly lift system 200 can enable the installation and removal of one or more combustor assemblies 20 while providing proper alignment specific to each component.
  • the combustor assembly lift system 200 can also enable a continuous installation and/or removal process by being able to grab the combustor assembly 20 while the combustor assembly 20 is in a shipping container, move the combustor assembly 20 into proper position and alignment within the turbomachine 100, and reverse the entire process without the need to exchange the combustor assembly 20 between multiple different lift assemblies.
  • the combustor assembly lift system 200 can generally comprise a lift arm 220 and a combustor assembly engagement frame 240.
  • the lift arm 220 can comprise a first portion 222 connected to a second portion 224 that helps facilitate the overall lifting and movement of the combustor assembly lift system 200.
  • the first portion 222 and the second portion 224 may be connected at an angle or may be connected via a rotatable connection to facilitate the re-alignment of a combustor assembly 20 temporarily secured to the combustor assembly lift system 200.
  • the combustor assembly engagement frame 240 can be connected to the lift arm 220 and be configured to temporarily secure to at least a portion of a combustor assembly 20.
  • the combustor assembly engagement frame 240 can be configured in a variety of configurations to help facilitate the overall lifting, transportation, rotation, alignment, installation and/or removal of one or more combustor assemblies 20 with respect to the individual slots of a turbomachine 100.
  • the lift arm 220 can generally comprise at least a first portion 222 connected to a second portion 224.
  • the first portion 222 and the second portion 224 can connect in a variety of potential configurations and/or adjustable angles to facilitate the overall lifting and movement of the combustor assembly lift system 200, including when a combustor assembly 20 is temporarily secured to combustor assembly engagement frame 240.
  • the lift arm 220 may thereby comprise a variety of configurations and materials suitable for supporting a combustor assembly 20 during movement.
  • the first portion 222 of the lift arm may be rotatably connected to the second portion 224 of the lift arm 220.
  • the rotatable connection may comprise any connection that facilitates the changing of the angle between the first portion 222 and second portion 224 of the lift arm 220.
  • the rotatable connection may comprise a pin connection that facilitates that relative rotation between the first portion 222 and second portion 224.
  • Such embodiments may additionally or alternatively comprise a bolt, screw, tension device or any other suitable mechanism for temporarily securing a given angle to prevent continuous rotation (such as when installing a combustor assembly 20).
  • the rotatable connection may comprise a limited variety of pre-designed slotted angles that the first portion 222 and the second portion 224 may be adjusted between.
  • the combustor assemblies 20 may be installed at one of a limited number of angles onto their respective slots based on the specific combustor assembly 20 location about the turbomachine 100.
  • the rotatable connection between the first portion 222 and the second portion 224 of the lift arm 220 may comprise predefined positions to facilitate one or more of those potential installation angles.
  • Such embodiments may promote faster and/or more predictable installation or removal of combustor assemblies 20 by assisting with the alignment the combustor assemblies 20 and their respective slots of the turbomachine 100.
  • the rotational connection between the first portion 222 and second portion 224 of the lift arm 220 may thereby help rotate a temporarily secured combustor assembly 20 between a near vertical orientation (as found when disposed in a shipping container) and a closer to horizontal orientation (as required for installation on the turbomachine 100).
  • the lift arm 220 may comprise a first portion 222 and a second portion 224 in a variety of configurations.
  • the first portion 222 and the second portion 224 may be connected to one another about their respective ends (as illustrated).
  • one end of either the first portion 222 or the second portion 224 may be connected to the other portion at a non-end location (e.g., offset from the end of the other portion).
  • the first portion 222 and the second portion 224 may each comprise a substantially similar length. However, in some embodiments, one of either the first portion 222 or the second portion 224 may be longer than the other.
  • the second portion 224 may be longer than the first portion 222.
  • Such embodiments may help balance the load of the combustor assembly lift system 200 when a combustor assembly 20 is temporarily secured thereto and being moved for installation or removal.
  • the lift arm 220 may comprise additional portions to provide even more levels of adjustability and/or provide more load bearing locations to temporarily secure to the combustor assembly 20 or move the overall combustor assembly lift system 200.
  • the lift arm 220 may comprise a third portion connected to the second portion 224.
  • the first portion 222, second portion 224 and third portion may be aligned in a sequence such that they can combine to transition between a single linear configuration and a serpentine (e.g., bent) configuration.
  • the lift arm 220 may comprise a third portion, wherein both the second portion 224 and the third portion are connected to the first portion 222.
  • the second portion 224 and third portion may split away from the first portion 222 in a V-shaped configuration to assist with the connection to the combustor assembly 20 between the second portion 224 and the third portion.
  • the second portion 224 and the third portion may be connected to a single end of the first portion 222.
  • the second portion 224 and the third portion may be offset from one another with their respective connections to the first portion 222.
  • the lift arm 220 may further comprise one or more pick points to assist in the lifting and movement of the overall combustor assembly lift system 200.
  • pick points may comprise any feature attached to or integral with one or more parts of the combustor assembly lift system to provide a hook, ring, handle or other similar grabbing point.
  • Pick points may thereby be used to attach chains 270 or other external lifting mechanisms to the combustor assembly lift system 200.
  • one or more pick points may comprise rings bolted, welded or staked to a portion of the lift arm 220 such that hooks on the end of chains 270 can grab the one or more pick points when the chains are used to lift and move the combustor assembly lift system 200.
  • Pick points may be disposed at a variety of locations around the combustor assembly lift system 200 such as at one or more locations along the lift arm 220.
  • the second portion 224 of the lift arm 220 may comprise at least one lower pick point 225 as illustrated.
  • the one or more lower pick points 225 may help facilitate the vertical lifting of the combustor assembly lift system 200, such as when removing a secured combustor assembly 20 from a shipping container prior to installation or when dropping a secured combustor assembly 20 into a shipping container after removal.
  • shipping container can refer to any box, crate or the like that houses the combustor assembly 20 during shipment to or from the location of a turbomachine 100.
  • first portion 222 and the second portion 224 of the lift arm 220 may freely rotate with respect to one another, lifting the combustor assembly lift system 200 solely or largely by a lower pick point 225 disposed at an end of the second portion 224 that is opposite the end that the first portion 222 is connected to, may facilitate the lift arm 220 to comprise a more vertically linear orientation.
  • the first portion 222 of the lift arm 220 may additionally or alternatively comprise at least one upper pick point 223.
  • a load may be at least partially transferred to the upper pick points 223 (i.e., a chain 270 may be attached to a lower pick point 225 to carry some of the load) to facilitate rotation or alignment of a secured combustor assembly 20.
  • the load of the overall combustor assembly lift system 200 with a combustor assembly 20 temporarily secured thereto may be shared and transferred between two or more pick points to transition the lift arm between a single linear configuration and a serpentine (e.g., bent) configuration. These and intermediate positions can assist in achieving successful alignment between the combustor assembly 20 and a respective combustor assembly by presenting the combustor assembly 20 at plurality of different angles.
  • the combustor assembly lift system 200 further comprises a combustor assembly engagement frame 240 connected to the lift arm 220 that is configured to temporarily secure to at least a portion of a combustor assembly 20.
  • the combustor assembly engagement frame 240 can comprise a variety of configurations to facilitate temporary securement to combustor assemblies 20.
  • the combustor assembly engagement frame 240 may comprise a clam shell configuration capable of transitioning between an open and a closed state to temporarily secure to the combustor assembly 20.
  • the combustor assembly engagement frame 240 may comprise two or more portions that can at least partially pivot away from one another to rotate open or, alternatively, completely separate away from one another, to accept at least a portion of the combustor assembly 20. The combustor assembly engagement frame 240 may then close back together around the combustor assembly 20 to provide temporary securement of the combustor assembly 20.
  • the combustor assembly engagement frame 240 may be configured to temporarily secure to at least a portion of the combustor assembly 20 via one or more bolts.
  • the combustor assembly engagement frame 240 may comprise a plurality of holes that may be aligned with corresponding holes on the combustor assembly 20. Once aligned, bolts, pins or the like may be temporarily passed through both sets of corresponding holes to temporarily secure the combustor assembly 20 to the combustor assembly engagement frame 240.
  • While particular embodiments of the combustor assembly engagement frame 240 have been disclosed herein to illustrate possible temporary securement configurations between the combustor assembly engagement frame 240 and the combustor assembly 20, it should be appreciated that these are exemplary only and not intended to be limiting. Additional or alternative configurations may also be realized to facilitate the temporary securement of the combustor assembly 20 to the combustor assembly engagement frame 240 of the combustor assembly lift system 200 such as by utilizing one or more holes, pick points, or the like.
  • the combustor assembly engagement frame 240 may be connected to the lift arm 220 in a variety of configurations and at a variety of locations to facilitate the lifting and movement of a secured combustor assembly 20 such as for the removal or installation of said combustor assembly 20 with respect to an open slot of a turbomachine 100.
  • the combustor assembly engagement frame 240 may comprise a rotatable connection 230 to the lift arm 220 such that the combustor assembly engagement frame 240 and the lift arm 220 may rotate with respect to one another.
  • the rotational connection 230 may enable rotation about any axis or axes to help facilitate rotational orientation between the combustor assembly 20 and its respective slot in the turbomachine 100.
  • the rotational connection 230 can be facilitated through any suitable configuration such as, but not limited to, a rotatable pin, bolt, screw, or ball-and-socket connecting the combustor assembly engagement frame 240 to the lift arm 220.
  • the first portion 222 of the lift arm 220 may be rotatably connected to the second portion 224 of the lift arm 220 in addition to the combustor assembly engagement frame 240 being rotatably connected to the lift arm 220 (e.g., either the first portion 222 or the second portion 224), so that the first portion 222 of the lift arm 220, the second portion 224 of the lift arm 220, and the combustor assembly engagement frame 240 can all transition between a vertical configuration and a serpentine (e.g., bent) configuration.
  • a serpentine e.g., bent
  • the combustor assembly engagement frame 240 may be connected to the lift arm 220 at a variety of locations.
  • the second portion 224 of the lift arm 220 comprises a first end connected to the first portion 222 of the lift arm 220, and a second end distal the first portion 222 of the lift arm 224
  • the combustor assembly engagement frame 240 can be connected to the second end of the second portion 224 of the lift arm 220 (as illustrated in FIGS. 4 and 5 ).
  • the second end of the second portion 224 of the lift arm 220 e.g., the end of the second portion 224 that the combustor assembly engagement frame 240 is connected to
  • a method 300 is illustrated for installing a combustor assembly 20 on a turbomachine 100.
  • the method generally comprises disposing a combustor assembly lift system 200 proximate the combustor assembly 20 in step 310.
  • the combustor assembly lift system 200 can comprise a lift arm 220 comprising a first portion 222 and connected to a second portion 224, and a combustor assembly engagement frame 240 connected to the lift arm 220 configured to temporarily secure to at least a portion of a combustor assembly 20.
  • disposing the combustor assembly lift system 200 proximate the combustor assembly 20 in step 310 comprises disposing the combustor assembly lift system 200 in vertical alignment over the combustor assembly 20 while the combustor assembly 20 is disposed in a shipping container.
  • Such embodiments can facilitate using a single combustor assembly lift system 200 for removal of the combustor assembly 20 from the shipping container, movement of the combustor assembly 20 to the turbomachine 100, and finally alignment and installation of the combustor assembly 20 with its respective slot on the turbomachine 100.
  • the method 300 may further comprise temporarily securing the combustor assembly engagement frame 240 to the combustor assembly 20 in step 320.
  • the combustor assembly engagement frame 240 may be temporarily secured to the combustor assembly 20 using a variety of configurations such as opening and closing a combustor assembly engagement frame 240 comprising a clamshell configuration, using one or more bolts, or using any other suitable securement system.
  • the method 300 may then comprise aligning and securing the combustor assembly 20 with the turbomachine 100 in step 320.
  • Aligning the combustor assembly 20 may comprise moving the overall combustor assembly lift system 200 while the combustor assembly 20 is temporarily secured thereto by any suitable means.
  • one or more chains may be connected to one or more pick points on the lift arm 220.
  • a first chain 270 may be connected to a lower pick point 225 for lifting the combustor assembly 20 out of the shipping container in a vertical path.
  • additional chains 270 may be connected to an upper pick point 223 to help transfer the load and/or rotate the combustor assembly 20 towards a more horizontal orientation that better aligns with its corresponding slot in the turbomachine 100.
  • Securing the combustor assembly 20 to the turbomachine may also be achieved through any suitable technique as should be appreciated to those skilled in the arts.
  • the combustor assembly 20 may be secured via one or more bolts, clamps, or the like.
  • method 300 may comprise releasing the combustor assembly 20 from the combustor assembly engagement frame 240 in step 340.
  • Releasing the combustor assembly 20 can comprise any suitable method based on the configuration of the combustor assembly engagement frame 240 (e.g., opening the combustor assembly engagement frame 240 and/or unbolting the combustor assembly engagement frame 240).
  • a method 400 is illustrated for removing a combustor assembly 20 from a turbomachine.
  • the method generally comprises disposing a combustor assembly lift system 200 proximate the combustor assembly 20 in step 410.
  • the combustor assembly lift system 200 can comprise a lift arm 220 comprising a first portion 222 and connected to a second portion 224, and a combustor assembly engagement frame 240 connected to the lift arm 220 configured to temporarily secure to at least a portion of a combustor assembly 20.
  • the method 400 may further comprise temporarily securing the combustor assembly engagement frame 240 to the combustor assembly 20 in step 420.
  • the combustor assembly engagement frame 240 may be temporarily secured to the combustor assembly 20 using a variety of configurations such as opening and closing a combustor assembly engagement frame 240 comprising a clamshell configuration, using one or more bolts, or using any other suitable securement system.
  • the method 400 may further comprise releasing the combustor assembly 20 from the turbomachine 100 and moving the combustor assembly lift system 200 away from the turbomachine 100 via one or more connections to the lift arm 220 in step 430.
  • Releasing the combustor assembly 20 from the turbomachine may be achieved through any suitable means based on the respective configuration of the combustor assembly 20 and the turbomachine.
  • releasing the combustor assembly 20 may comprise removing one or more bolts connecting the combustor assembly 20 to the turbomachine.
  • moving the combustor assembly lift system 200 may be achieved through any suitable means such as one or more chains 270 connected to one or more pick points on the lift arm 220.
  • method 400 may further comprise transitioning the combustor assembly lift system 200 to a substantially vertical orientation while the combustor assembly 20 is still temporarily secured to the combustor assembly engagement frame 240. Such embodiments may then further comprise lowering the combustor assembly 20 into a shipping container and releasing the combustor assembly 20 from the combustor assembly engagement frame 240. Similar to the installation method 300 discussed above, such removal methods 400 may facilitate the removal of the combustor assembly 20 from its slot in the turbomachine 100 along with its subsequent placement in a shipping container using a single combustor assembly lift system 200.
  • combustor assembly lift systems as disclosed herein can be provided to help install, remove, or re-install combustor assemblies into turbomachines.
  • Such combustor assembly lift systems can facilitate proper alignment specific to each combustor assembly while enabling a continuous installation and/or removal process via a single combustor assembly lift system.
  • These combustor assembly lift systems and methods may thereby provide for simpler and faster overall installation and removal activities.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Load-Engaging Elements For Cranes (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16201231.4A 2015-12-10 2016-11-29 Brennkammerbaugruppenhebesysteme und verfahren zur verwendung davon zum montieren und demontieren von brennkammerbaugruppen Withdrawn EP3178771A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/964,792 US20170167298A1 (en) 2015-12-10 2015-12-10 Combustor assembly lift systems and methods for using the same to install and remove combustor assemblies

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EP3178771A1 true EP3178771A1 (de) 2017-06-14

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US (1) US20170167298A1 (de)
EP (1) EP3178771A1 (de)
JP (1) JP2017106447A (de)
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US11492929B1 (en) 2021-07-19 2022-11-08 General Electric Company Combustion can lift assembly
US11773772B2 (en) 2021-07-19 2023-10-03 General Electric Company System and method for installation or removal of one or more combustion cans

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JP2017106447A (ja) 2017-06-15
US20170167298A1 (en) 2017-06-15

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