JP2017106447A - Combustor assembly lift systems and methods for using the same to install and remove combustor assemblies - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide combustor assembly lift systems and methods for using the same to install and remove combustor assemblies.SOLUTION: A combustor assembly lift system 200 comprises a lift arm 220 comprising a first portion connected to a second portion, and a combustor assembly engagement frame 240 connected to the lift arm, where the combustor assembly engagement frame is configured to be temporarily secured to at least a portion of a combustor assembly 20. Also disclosed is a method for installing a combustor assembly on a turbomachine, the method comprising disposing a combustor assembly lift system proximately to the combustor assembly.SELECTED DRAWING: Figure 5

Description

  The subject matter disclosed herein relates to combustor assemblies and, more particularly, to an apparatus and method for installing and removing a combustor assembly from a gas turbine.

  The gas turbine may include a compressor section, a combustion section, and a turbine section. The compressor section pressurizes air flowing into the turbine. Pressurized air discharged from the compressor section flows into a combustion section generally characterized by a plurality of combustors. Each of the plurality of combustors includes a combustion liner that defines a combustion chamber of the combustor. Thus, the air entering each combustor is mixed with fuel and burned in the combustion liner. Hot combustion gases flow from the combustion liner through the transition piece to the turbine section of the gas turbine to drive the turbine and generate electricity.

  More specifically, the gas turbine combustor mixes a large amount of fuel and compressed air and burns the resulting mixture. A combustor for an industrial gas turbine can include an annular array of cylindrical combustion “cans” in which combustion occurs by mixing air and fuel. The compressed air from the axial compressor flows into the combustor. Fuel is injected through a fuel nozzle assembly that extends into each can. The fuel / air mixture burns in the combustion chamber of each can. Combustion gas is discharged from each can into a duct leading to the turbine.

  In some embodiments, a combustor assembly designed for low emissions may comprise a premix chamber and a combustion chamber. The fuel nozzle assembly in each combustor assembly injects fuel and air into the can chamber. A portion of the fuel from the nozzle assembly is discharged into the can premixing chamber where air is added to the fuel and premixed with the fuel. Premixing air and fuel in the premix chamber facilitates rapid and efficient combustion and low emissions due to combustion in the combustion chamber of each can. The air and fuel mixture flows downstream from the premix chamber to the combustion chamber, which supports combustion and receives additional fuel that is discharged from the front of the fuel nozzle assembly under some conditions. This additional fuel provides a means of stabilizing the flame for low power operation and can be completely shut off during high power conditions.

  The combustor assembly needs to be installed during the initial construction of the gas turbine and can subsequently be removed during subsequent maintenance activities. However, a significant amount of force can properly lift, position, and / or align the combustor assembly with respect to the combustor assembly to install, remove, or reinstall the combustor assembly. May be needed. Accordingly, alternative equipment and methods for installing and removing a combustor assembly from a gas turbine are welcome in the art.

US Patent No. 860340

  In one embodiment, a combustor assembly lift system includes a lift arm with a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm for combustion. The combustor assembly engagement frame is configured to be temporarily secured to at least a portion of the combustor assembly.

  In another embodiment, a method for installing a combustor assembly in a turbomachine is disclosed. The method includes disposing a combustor assembly lift system proximate to the combustor assembly. A combustor assembly lift system includes a lift arm having a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm. The frame is configured to be temporarily secured to at least a portion of the combustor assembly. The method includes temporarily securing a combustor assembly engagement frame to a turbomachine, aligning and securing the combustor assembly with the turbomachine, and engaging the combustor assembly with the combustor assembly. And removing from the frame.

  In yet another embodiment, a method for removing a combustor assembly from a turbomachine is disclosed. The method includes disposing a combustor assembly lift system proximate to the combustor assembly. A combustor assembly lift system includes a lift arm with a first portion connected to a second portion, and a combustor assembly engagement frame connected to the lift arm. The frame is configured to be temporarily secured to at least a portion of the combustor assembly. The method includes temporarily fixing a combustor assembly engagement frame to a combustor assembly, removing the combustor assembly from the turbomachine, and connecting the turbomachine via one or more connections to a lift arm. Moving the combustor assembly lift system away from the vehicle.

  These and further features provided by the embodiments described herein will be more fully understood in view of the following detailed description in conjunction with the drawings.

  The embodiments depicted in the drawings are illustrative and exemplary in nature and are not intended to limit the invention as defined by the appended claims. The following detailed description of exemplary embodiments can be understood when read in conjunction with the following drawings. Here, the same structure is indicated by the same reference numeral.

1 is a side view of a turbomachine according to one or more embodiments shown or described herein. FIG. 1 is a side view of a combustion system according to one or more embodiments shown or described herein. FIG. 1 is a cross-sectional side view of a combustor assembly according to one or more embodiments shown or described herein. 1 is a perspective view of a combustor assembly lift system according to one or more embodiments shown or described herein. FIG. FIG. 5 is a perspective view of the combustor assembly lift system shown in FIG. 4 in different orientations according to one or more embodiments shown or described herein. 2 is a flow diagram of a method of installing a combustor assembly according to one or more embodiments shown or described herein. 2 is a flow diagram of a method of removing a combustor assembly according to one or more embodiments shown or described herein.

  One or more specific aspects / embodiments of the invention are described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. The development of any such actual implementation, such as in any engineering or design project, has a number of implementation-specific implementations to achieve the developer's specific goals, such as respecting system-related constraints and business-related constraints. It should be understood that a decision must be made and this may vary from implementation to implementation. Furthermore, it should be understood that such development efforts can be complex and time consuming, but nevertheless are routine tasks relating to design, fabrication, and manufacture for those skilled in the art having the benefit of this disclosure.

  When introducing elements of various embodiments of the present invention, the articles “a”, “an”, “the”, and “said” are intended to mean that there are one or more elements. . The terms “comprising”, “including” and “having” are inclusive and mean that there may be additional elements other than the listed elements. Intended.

  Referring now to FIG. 1, some turbomachines, such as gas turbines, aircraft diverters, etc., generate energy by burning a fuel / air mixture during the combustion process. FIG. 1 shows an example of a turbomachine 100. In general, turbomachine 100 includes an inlet plenum 105 that directs airflow toward a compressor contained within a compressor casing 110. The air stream is compressed and then discharged to the combustion system 115 where fuel, such as natural gas, is burned to provide a high energy combustion gas, thereby driving the turbine section 120. In the turbine section 120, the energy of the hot gas is converted into work, part of the work is used to drive the compressor, and the rest of the energy is used for generators, mechanical drives, etc. (all of which are illustrated). Not available for work to help drive loads).

  Still referring to FIG. 2, an embodiment of the combustion system 115 can comprise at least one combustor assembly 20. Some turbomachines 100 as shown in FIG. 2 may include a plurality of combustor assemblies 20 arranged in an annular array about a central axis A. Generally, within each combustor assembly 20, the above-described combustion process occurs. In some embodiments, the combustor assembly 20 may include one or more auxiliary systems 130 such as a flame detection system for monitoring a flame that burns in a portion of the combustor assembly 20. Such a flame detection system can be in the form of a flame detector, a portion of which can be inserted into the combustor assembly 20. Additional or alternative auxiliary systems 130 may be similarly incorporated into the combustor assembly 20 to monitor, control, and / or influence one or more of the combustor assembly processes.

  With reference additionally now to FIG. 3, a cross-sectional side view of an embodiment of a combustor assembly 20 of turbomachine 100 is shown. Generally, the combustor assembly 20 includes at least a combustion can 125 and a potentially 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. Can do. As shown, the flange 26 may extend outward from the upstream end of the combustion casing 22. In general, the flange 26 can be configured such that the end cover assembly of the combustor assembly 20 can be secured to the combustion casing 22. For example, the flange 26 may define a plurality of flange holes 72 for attaching the end cover assembly to the combustion casing 22.

  In some embodiments, the combustor assembly 20 can also include an internal flow sleeve 28 and / or a combustion liner 30 disposed substantially concentrically within the flow sleeve 28. Combustor assembly 20 includes a single combustor assembly 20 comprising a combustion can 125 and at least one of a flow sleeve 28 or combustion liner 30 connected to the combustion can 125 as a single pre-assembled structure. Combustor assembly 20 may include a combustion can 125, a flow sleeve 28, and a combustion liner 30 all such as a turbine casing 24 (sometimes referred to as a combustion discharge casing or "CDC"). An assembly that connects directly to the turbomachine 100 may be provided. For example, the flow sleeve 28 and combustion liner 30 may extend at its downstream end to a double wall transition duct comprising an impingement sleeve 32 and a transition piece 34 disposed within the impingement sleeve 32. In some embodiments, the impingement sleeve 32 and the flow sleeve 28 can include a plurality of air supply holes 36 that cover portions of their surfaces so that the compressed air from the compressor section 12 is combusted. It should be understood that entry into the radial space between the liner 30 and the flow sleeve 28 is allowed.

  In general, the combustion liner 30 of the combustor assembly 20 can define a generally cylindrical combustion chamber 38 where fuel and air are injected and burned to generate hot combustion gases. In addition, the combustion liner 30 transitions at its downstream end so that the combustion liner 30 and transition piece 34 generally define a flow path for hot combustion gases from each combustor assembly 20 to the turbine section 16 of the turbine assembly 10. Can be coupled to piece 34.

  In some embodiments, like that shown in FIG. 32, the transition piece 34 can be coupled to the downstream end of the combustion liner 30 with a seal 40 (eg, a compression seal). For example, the seal 40 can be disposed at the overlapping end of the transition piece 34 and the combustion liner 30 to seal the boundary between the two components. For example, the seal 40 may comprise a circumferential metal seal configured to be a spring / compression that is loaded between the inner and outer diameters of the mating portions. However, it will be understood that the boundary between the combustion liner 30 and the transition piece 34 need not be sealed with a compression seal 40 and can be totally sealed by any suitable seal known in the art. I want.

  In some embodiments, the combustion liner 30 is attached to one or more female liner stops 44 that are fixed to the flow sleeve 28 or fixed to the combustion casing 22 in the combustor assembly 20 without the flow sleeve 28. One or more male liner stops 42 may also be provided. In particular, the male liner stop 42 is used by the combustion liner 30 to indicate proper installation depth of the combustion liner 30 and to prevent rotation of the liner 30 during operation of the turbine assembly 10. It can be adapted to slide into the female liner stop 44 when installed in 20. Additionally or alternatively, in some embodiments, the male liner stop 42 can be disposed on the flow sleeve 28 or the combustion casing, while the female liner stop 44 is disposed on the combustion liner 30. Please understand that you can.

  In some embodiments, first, the combustion liner 30 can be installed in the combustor assembly 20 by being pushed into the combustor assembly 20. For example, the combustion liner 30 can be pushed into the combustor assembly 20 until the force limits the further installation depth into the transition piece 34. With continued reference to FIG. 2, the combustion cans 125 can then be installed in each respective combustor assembly 20. Specifically, the combustion can 125 can be positioned, aligned and inserted so that its end cover assembly abuts the flange 26 of the combustor assembly 20.

  Although specific embodiments have been shown herein, for the individual connections made with turbomachine 100, combustor assembly 20 can comprise a variety of different components that are assembled in a variety of different orders. I want you to understand. For example, the combustor assembly 20 may be fully assembled prior to installation on the turbomachine 100 (eg, a single combustor assembly 20) or partially assembled prior to installation on the turbomachine 100. It may well be fully assembled while connected to the turbomachine 100, or a combination thereof.

  With further reference to FIGS. 4 and 5, the combustor assembly lift system 200 may be provided to assist in the installation, removal or re-installation of the combustor assembly 20 in the turbomachine 100. In particular, the combustor assembly lift system 200 may allow for the installation and removal of one or more combustor assemblies 20 while providing specific appropriate alignment for each component. The combustor assembly lift system 200 allows a continuous installation and / or removal process by allowing the combustor assembly 20 to be gripped while the combustor assembly 20 is in a shipping container. Move the combustor assembly 20 to the proper position and alignment within the turbomachine 100 and reverse the entire process without having to replace the combustor assembly 20 between multiple different lift assemblies You can also.

  In general, the combustor assembly lift system 200 can include a lift arm 220 and a combustor assembly engagement frame 240. The lift arm 220 can include 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. Also, the first portion 222 and the second portion 224 connect at an angle to facilitate realignment of the combustor assembly 20 temporarily secured to the combustor assembly lift system 200. Can be connected by a rotatable connection. The combustor assembly engagement frame 240 may be configured to connect to the lift arm 220 and be temporarily secured to at least a portion of the combustor assembly 20. The combustor assembly engagement frame 240 also facilitates the overall lifting, transport, rotation, alignment, installation and / or removal of one or more combustor assemblies 20 with respect to individual slots of the turbomachine 100. It can be configured in a variety of configurations to help.

  With further reference to FIGS. 4-5, generally, the lift arm 220 can comprise at least a first portion 222 connected to a second portion 224. The first portion 222 and the second portion 224 are used to lift and move the combustor assembly lift system 200, including when the combustor assembly 20 is temporarily secured to the combustor assembly engagement frame 240. Can be connected in various potential configurations and / or at adjustable angles.

  Thereby, the lift arm 220 can comprise various configurations and materials suitable for supporting the combustor assembly 20 during movement. In some embodiments, like the one shown in FIGS. 4 and 5, the first portion 222 of the lift arm can be rotatably connected to the second portion 224 of the lift arm 220. The rotatable connection can include any connection that facilitates changing the angle between the first portion 222 and the second portion 224 of the lift arm 220. For example, in some embodiments, the rotatable connection can comprise a pin connection that facilitates its relative rotation between the first portion 222 and the second portion 224. Additionally or alternatively, such embodiments may be used for bolts, screws, tensioning devices, or for temporarily securing at a given angle to prevent continuous rotation (such as when installing the combustor assembly 20), or Any other suitable mechanism can be provided.

  In some embodiments, the rotatable connection can comprise a limited variety of pre-designed slot angles between which the first portion 222 and the second portion 224 can be adjusted. For example, the combustor assemblies 20 may be installed at one of a limited number of angles to their respective slots based on the location of the particular combustor assembly 20 around the turbomachine 100. it can. In such an embodiment, the rotatable connection between the first portion 222 and the second portion 224 of the lift arm 220 pre-facilitates one or more of these potential installation angles. Can include defined positions. Such embodiments may facilitate faster and / or more predictable installation or removal of the combustor assembly 20 by aiding the alignment of the combustor assembly 20 and its respective slots in the turbomachine 100. it can.

  Thereby, the rotational connection between the first portion 222 and the second portion 224 of the lift arm 220 is in a substantially vertical orientation (as seen when disposed in a shipping container) (in the turbomachine 100). Can help to rotate the temporarily fixed combustor assembly 20 between nearer horizontal orientations (as required for installation).

  Further, the lift arm 220 can include a first portion 222 and a second portion 224 in various configurations. For example, in some embodiments, the first portion 222 and the second portion 224 can be connected to each other about their respective ends (as shown). In some embodiments, one end of the first portion 222 or the second portion 224 may connect to the other portion at a non-end position (eg, offset from the end of the other portion). it can. In some embodiments, the first portion 222 and the second portion 224 can each comprise a substantially similar length. However, in some embodiments, either the first portion 222 or the second portion 224 can be longer than the other. For example, when the combustor assembly engagement frame 240 is connected to the second portion 224 of the lift arm 220, the second portion 224 can be longer than the first portion 222. Such embodiments help to balance the load of the combustor assembly lift system 200 when the combustor assembly 20 is temporarily secured thereto and moved for installation or removal. Can do.

  Further, in some embodiments, the lift arm 220 further increases the adjustable level to temporarily secure the combustor assembly 20 or move the entire combustor assembly lift system 200, and / or Additional portions can be provided to increase the position to withstand the load. For example, in some embodiments, the lift arm 220 can comprise a third portion connected to the second portion 224. In such an embodiment, the first portion 222, the second portion 224, and the third portion transition between a single linear configuration and a serpentine (eg, bent) configuration. Can be arranged in order so that they can be combined.

  In some embodiments, the lift arm 220 can comprise a third portion, and both the second portion 224 and the third portion are connected to the first portion 222. For example, the second portion 224 and the third portion can be connected to the combustor assembly 20 between the second portion 224 and the third portion to provide a first portion 222 in a V-shaped configuration. It is divided away from. Further, in some embodiments, the second portion 224 and the third portion can be connected to a single end of the unit end of the first portion 222. Alternatively, with their respective connections to the first portion 222, the second portion 224 and the third portion can be offset from each other.

  The lift arm 220 can further include one or more pick points that assist in lifting and moving the entire combustor assembly lift system 200. As used herein, a pick point is attached to one or more parts of a combustor assembly lift system to provide a kite, ring, handle, or other similar grabbing point, or Any feature integral therewith can be provided. Thereby, the pick point can be used to attach a chain 270 or other external lift mechanism to the combustor assembly lift system 200. For example, one or more pick points may be used when the chain at the end of the chain 270 grips one or more pick points when the chain is used to lift and move the combustor assembly lift system 200. A portion of the lift arm 220 can be provided with a bolted, welded, or pierced ring so that it can.

  The pick points can be disposed at various locations around the combustor assembly lift system 200, such as one or more locations along the lift arm 220. In some embodiments, the second portion 224 of the lift arm 220 can include at least one lower pick location 225, as shown. One or more lower pick locations 225 may be used to remove the fixed combustor assembly 20 from the shipping container prior to installation, or after removal from the shipping container. The vertical lift of the combustor assembly lift system 200 can be facilitated, such as when being lowered. As used herein, a shipping container may refer to any box, crate, etc. that contains a combustor assembly 20 during or to transportation from a turbomachine 100 location. it can. In an embodiment, when the first portion 222 and the second portion 224 of the lift arm 220 are free to rotate with respect to each other, the second is opposite the end to which the first portion 222 is connected. Lifting the combustor assembly lift system 200 singly or in large quantities by the lower pick point 225 disposed at the end of the portion 224 facilitates the lift arm 220 to include a more vertical linear orientation. can do.

  In some embodiments, additionally or alternatively, the first portion 222 of the lift arm 220 can include at least one upper pick location 223. The load can be at least partially converted to the upper pick location 223 (i.e., the chain 270 can be attached to the lower pick location 225 to support a portion of the load) and thereby a fixed combustor Facilitates rotation or alignment of the assembly 20. For example, as shown in FIGS. 5 and 6, the entire load of the combustor assembly lift system 200 having the combustor assembly 20 temporarily secured thereto may be shared between two or more pick points. To transfer the lift arm between a single linear configuration and a serpentine (eg, bent) configuration. These positions and intermediate positions help to achieve a good alignment between the combustor assemblies 20 and each combustor assembly by showing the combustor assemblies 20 at a plurality of different angles. be able to.

  With further reference to FIGS. 4 and 5, the combustor assembly lift system 200 includes a combustor assembly connected to a lift arm 220 configured to be temporarily secured to at least a portion of the combustor assembly 20. A solid engagement frame 240 is further provided.

  The combustor assembly engagement frame 240 can have a variety of configurations to facilitate temporary fixation to the combustor assembly 20. For example, in some embodiments, the combustor assembly engagement frame 240 allows a transition between an open state and a closed state to temporarily secure to the combustor assembly 20. A clamshell configuration can further be provided. More specifically, in such embodiments, the combustor assembly engagement frames 240 are spaced apart from each other to rotate open to receive at least a portion of the combustor assembly 20, or Alternatively, two or more portions can be provided that can be pivoted at least in part to separate completely away from each other. The combustor assembly engagement frame 240 can then be closed back together around the combustor assembly 20 to temporarily secure the combustor assembly 20.

  In some embodiments, the combustor assembly engagement frame 240 can be configured to be temporarily secured to at least a portion of the combustor assembly 20 by one or more bolts. For example, the combustor assembly engagement frame 240 can include a plurality of holes that can be aligned with corresponding holes in the combustor assembly 20. When aligned, bolts, pins, etc. can temporarily pass through the corresponding holes in both sets to temporarily secure the combustor assembly 20 to the combustor assembly engagement frame 240.

  Although specific embodiments of the combustor assembly engagement frame 240 have been disclosed herein to illustrate possible temporary securing configurations between the combustor assembly engagement frame 240 and the combustor assembly 20. It should be understood that these are exemplary only and are not intended to be limiting. Additionally or alternatively, the configuration temporarily moves 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, etc. It can also be understood that it is easy to fix to.

  The combustor assembly engagement frame 240 facilitates lifting and movement of the fixed combustor assembly 20 such as for removal or installation of the combustor assembly 20 relative to the open slot of the turbomachine 100. Can be connected to the lift arm 220 in various configurations and at various positions. For example, in some embodiments, the combustor assembly engagement frame 240 is rotatable relative to the lift arm 220 so that the combustor assembly engagement frame 240 and the lift arm 220 can rotate relative to each other. A connection 230 can be provided. Rotational connection 230 allows rotation about any one or more axes to help facilitate the direction of rotation between combustor assembly 20 and its respective slot in turbomachine 100. Can be. The rotational connection 230 is facilitated by any suitable configuration such as, but not limited to, a rotatable pin, bolt, screw, or ball and socket that connects the combustor assembly engagement frame 240 to the lift arm 220. can do.

  In some embodiments, in addition to the combustor assembly engagement frame 240 being rotatably connected to the lift arm 220 (eg, either the first portion 222 or the second portion 224), the lift The first portion 222 of the arm 220 can be rotatably connected to the second portion 224 of the lift arm 220, whereby the first portion 222 of the lift arm 220 and 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 (eg, bent) configuration.

  The combustor assembly engagement frame 240 can be connected to the lift arm 220 at various positions. For example, the second portion 224 of the lift arm 220 has a first end connected to the first portion 222 of the lift arm 220 and a second end distal to 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 shown in FIGS. 4 and 5). In some of these embodiments, the second end of the second portion 224 of the lift arm 220 (eg, the end of the second portion 224 to which the combustor assembly engagement frame 240 is connected) is: At least one lower pick location 225 may be provided.

  With further reference to FIG. 6, a method 300 of installing the combustor assembly 20 in the turbomachine 100 is illustrated. In general, the method includes disposing a combustor assembly lift system 200 near the combustor assembly 20 at step 310. As described above, the combustor assembly lift system 200 is configured to be temporarily secured to at least a portion of the first portion 222 connected to the second portion 224 and the combustor assembly 20. A lift arm 220 comprising a combustor assembly engagement frame 240 connected to the lift arm 220.

  In some embodiments, disposing the combustor assembly lift system 200 near the combustor assembly 20 in step 310 may be performed while the combustor assembly 20 is disposed in a shipping container. Disposing the combustor assembly lift system 200 in vertical alignment on the combustor assembly 20. Such an embodiment removes the combustor assembly 20 from the shipping container, moves the combustor assembly 20 to the turbomachine 100, and finally the combustor using its respective slot into the turbomachine 100. A single combustor assembly lift system 200 can be facilitated to align and install the assembly 20.

  The method 300 may further comprise temporarily securing the combustor assembly engagement frame 240 to the combustor assembly 20 at step 320. As described herein, the combustor assembly engagement frame 240 may include a combustor with a clamshell configuration using one or more bolts or using any other suitable fastening system. Various configurations such as opening and closing the assembly engagement frame 240 can be used to temporarily fix the combustor assembly 20.

  The method 300 may then include aligning and securing the combustor assembly 20 with the turbomachine 100 at step 320. The alignment of the combustor assembly 20 can move the entire combustor assembly lift system 200 while the combustor assembly 20 is temporarily secured thereto by any suitable means. For example, in some embodiments, one or more chains can be connected to one or more pick points on the lift arm 220. In some particular embodiments, the first chain 270 can be connected to the lower pick point 225 to lift the combustor assembly 20 out of the shipping container in a vertical path. Subsequently, an additional chain 270 can be connected to the upper pick point 223, thereby assisting in load transfer and / or burning in a more horizontal orientation that better aligns with its corresponding slot in the turbomachine 100. Assists rotation of the vessel assembly 20. Securing the combustor assembly 20 to the turbomachine can also be accomplished by any suitable technique as would be understood by one skilled in the art. For example, the combustor assembly 20 can be secured by one or more bolts, clamps, and the like.

  Finally, the method 300 may include removing the burner assembly 20 from the combustor assembly engagement frame 240 at step 340. Removing the combustor assembly 20 may be dependent on the configuration of the combustor assembly engagement frame 240 (eg, not opening the combustor assembly engagement frame 240 and / or bolting the combustor assembly engagement frame 240). ) On the basis of any suitable method.

  With further reference to FIG. 7, a method 400 of removing the combustor assembly 20 from a turbomachine is shown. In general, the method includes disposing a combustor assembly lift system 200 near the combustor assembly 20 at step 410. As described above, the combustor assembly lift system 200 includes a first portion 222 and is temporarily secured to at least a portion of the combustor assembly 20 with a lift arm 220 that is connected to the second portion 224. And a combustor assembly engagement frame 240 connected to a lift arm 220 configured to be configured.

  The method 400 may further include temporarily securing the combustor assembly engagement frame 240 to the combustor assembly 20 at step 420. As described herein, the combustor assembly engagement frame 240 may include a combustor with a clamshell configuration using one or more bolts or using any other suitable fastening system. Various configurations such as opening and closing the assembly engagement frame 240 can be used to temporarily fix the combustor assembly 20.

  Finally, the method 400, in step 430, disconnects the combustor assembly lift system 200 from the turbomachine 100 by disconnecting the combustor assembly 20 from the turbomachine 100 and leaving the turbomachine 100 by one or more connections to the lift arm 220. It can further include moving. Removing the combustor assembly 20 from the turbomachine can be accomplished by any suitable means based on the respective configuration of the combustor assembly 20 and the turbomachine. For example, in some embodiments, removing the combustor assembly 20 can include removing one or more bolts that connect the combustor assembly 20 to the turbomachine. Also, moving the combustor assembly lift system 200 may be accomplished by any suitable means, such as one or more chains 270 connected to one or more pick locations on the lift arm 220. it can.

  In some embodiments, the method 400 transitions the combustor assembly lift system 200 in a generally vertical orientation while the combustor assembly 20 is still temporarily secured to the combustor assembly engagement frame 240. Can further include. Such embodiments may then further include lowering the combustor assembly 20 into a shipping container and removing the combustor assembly 20 from the combustor assembly engagement frame 240. Similar to the above-described method 300 of installation, such a removal method 400 uses a single combustor assembly lift system 200 to burn from its slot in the turbomachine 100 with subsequent replacement in a shipping container. It may be easier to remove the vessel assembly 20.

  It should be understood herein that a combustor assembly lift system as disclosed herein can provide assistance in installing, removing, or re-installing a combustor assembly in a turbomachine. Such a combustor assembly lift system facilitates proper alignment specific to each combustor assembly while allowing a continuous installation and / or removal process with a single combustor assembly lift system. Can be. Thereby, these combustor assembly lift systems and methods can achieve a simpler and faster overall installation and removal activity.

  Although the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention may be modified to incorporate any number of variations, alternatives, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Furthermore, while various embodiments of the invention have been described, it should be understood that each aspect of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

DESCRIPTION OF SYMBOLS 20 Combustor assembly 22 Combustion casing 24 Turbine casing 26 Flange 27 Rear side 28 Internal flow sleeve 30 Combustion liner 32 Impingement sleeve 34 Transition piece 36 Air supply hole 38 Combustion chamber 40 Seal 42 Male type liner stop 44 Female type liner stop 72 Flange hole 100 Turbomachine 105 Inlet plenum 110 Compressor casing 115 Combustion system 120 Turbine section 125 Combustion can 130 Auxiliary system 200 Combustor assembly lift system 220 Lift arm 222 First part 223 Upper pick point 224 Second part 225 Below Side pick location 230 Rotary connection 240 Combustor assembly engagement frame 242 Base 244 Arm 270 Chain 300 Installation method 310 Step 320 Step 330 Step 340 Step 400 410 Step 420 Step 430 Step A shaft method for removing

Claims (20)

A lift arm (220) comprising a first part (222) connected to a second part (224);
A combustor assembly lift system (200) comprising a combustor assembly engagement frame (240) connected to the lift arm (220);
A combustor assembly lift system (200), wherein the combustor assembly engagement frame (240) is configured to be temporarily secured to at least a portion of the combustor assembly (20). The combustor assembly lift of claim 1, wherein the first portion (222) of the lift arm (220) is rotatably connected to the second portion (224) of the lift arm (220). System (200). The combustor assembly lift system (200) of any preceding claim, wherein the combustor assembly engagement frame (240) is rotatably connected to the lift arm (220). The first portion (222) of the lift arm (220) is rotatably connected to the second portion (224) of the lift arm (220), and the combustor assembly engagement frame (240). ) Rotatably connected to the lift arm (220), the first portion (222) of the lift arm (220), the second portion (224) of the lift arm (220), and the combustion The combustor assembly lift system (200) of any preceding claim, wherein the combustor assembly engagement frame (240) is adapted to transition between a vertical configuration and a serpentine configuration. The second portion (224) of the lift arm (220) includes a first end connected to the first portion (222) of the lift arm (220) and the lift arm (220). A second end distal to the first portion (222), and the combustor assembly engagement frame (240) includes the second portion (224) of the lift arm (220). The combustor assembly lift system (200) of any preceding claim, connected to the second end of the combustor assembly. The combustor assembly lift system (200) of claim 5, wherein the second portion (224) of the lift arm (220) is longer than the first portion (222) of the lift arm (220). . The combustor assembly lift system (200) of claim 5, wherein the second end of the second portion (224) of the lift arm (220) comprises at least one lower pick point (225). ). The combustor assembly lift system (200) of any preceding claim, wherein the lift arm (220) further comprises a third portion connected to the second portion (224). The combustor assembly lift system (200) of claim 8, wherein the combustor assembly engagement frame (240) is connected to the third portion of the lift arm (220). The combustor assembly lift system (200) of claim 8, wherein both the second portion (224) and the third portion are connected to the first portion (222). The combustor assembly lift system (200) of claim 10, wherein both the second portion (224) and the third portion are connected to a single end of the first portion (222). ). The combustor assembly lift system (200) of any preceding claim, wherein the first portion (222) of the lift arm (220) comprises at least one upper pick location (223). The combustor assembly lift system (200) of claim 12, wherein the second portion (224) of the lift arm (220) comprises at least one lower pick point (225). The combustor assembly (20) comprises a single combustor assembly (20) comprising a combustion can (125) and at least one of a flow sleeve or combustion liner (30) connected to the combustion can (125). The combustor assembly lift system (200) of any preceding claim. The combustor assembly lift system (200) of any preceding claim, wherein the combustor assembly (20) is a combustion can (125). In a method (300) of installing a combustor assembly (20) in a turbomachine (100),
Disposing a combustor assembly lift system (200) proximate to the combustor assembly (20), the combustor assembly lift system (200) comprising:
A lift arm (220) comprising a first part (222) connected to a second part (224);
A combustor assembly engagement frame (240) connected to the lift arm (220), the combustor assembly engagement frame (240) being temporarily attached to at least a portion of the combustor assembly (20). Disposing to be configured to be fixed
Temporarily securing the combustor assembly engagement frame (240) to the turbomachine (100);
Aligning and securing the combustor assembly (20) with the turbomachine (100);
Disengaging the combustor assembly (20) from the combustor assembly engagement frame (240). Disposing the combustor assembly lift system (200) proximate to the combustor assembly (20) includes: while the combustor assembly (20) is disposed within a shipping container. The method of claim 16, comprising disposing the combustor assembly lift system (200) in vertical alignment on the combustor assembly (20). In a method (400) of removing a combustor assembly (20) from a turbomachine (100):
Disposing a combustor assembly lift system (200) proximate to the combustor assembly (20), the combustor assembly lift system (200) comprising:
A lift arm (220) comprising a first part (222) connected to a second part (224);
A combustor assembly engagement frame (240) connected to the lift arm (220), the combustor assembly engagement frame (240) being temporarily attached to at least a portion of the combustor assembly (20). Disposing to be configured to be fixed
Temporarily securing the combustor assembly engagement frame (240) to the combustor assembly (20);
The combustor assembly (20) is disconnected from the turbomachine (100) and away from the turbomachine (100) via one or more connections to the lift arm (220). Moving the lift system (200). The combustor assembly (20) moves the combustor assembly lift system (200) in a substantially vertical orientation while still being temporarily secured to the combustor assembly engagement frame (240). The method of claim 18, further comprising a step. The method of claim 19, further comprising lowering the combustor assembly (20) into a shipping container and disengaging the combustor assembly (20) from the combustor assembly engaging frame (240). .