BACKGROUND OF THE INVENTION

(0001] The subject matter disclosed herein relates to combustor assembly lift arms and systems and, more specifically, to combustor assembly lift arms and systems for installing and removing combustor assemblies with respect to a turbomachine.

[0002] 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. As such, 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

[0003] More specifically, 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 mat extend into each can. The mixture of fuel and air bums in a combustion chamber of each can. The combustion gases discharge from each can into a duct that leads to the turbine.

[0004] In some embodiments, 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.

[0005] 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 systems for installing and removing combustor assemblies with respect to a turbomachine would be welcome in the art.

BRIEF DESCRIPTION OF THE INVENTION

[0006] In one embodiment, a combustor assembly lift arm is disclosed. The combustor assembly lift arm comprises a moveable support arm comprising a first end and a second end with a combustor assembly engagement frame connected to the first end of the moveable support arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly, and a connection fixture connected to the second end of the moveable support arm, wherein the connection support is configured to connect the combustor assembly lift arm to a base structure.

[0007] In another embodiment, a combustor assembly lift systems is disclosed. The combustor assembly lift system comprises a combustor assembly lift track comprising one or more rails comprising one or more portions that combine to extend in a non-linear path and a rail connector attached to at least one of the one or more portions of the one or more rails, wherein the rail connector is configured to connect the one or more rails to at least a portion of a turbomachine. The combustor assembly lift system further comprises a combustor assembly lift arm comprising a moveable support arm comprising a first end and a second end with a combustor assembly engagement frame connected to the first end of the moveable support arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly, and a connection fixture connected to the second end of the moveable support arm, wherein the connection fixture connects the combustor assembly lift arm to the one or more rails of the combustor assembly lift track.

[0008] In yet another embodiment, a turbomachine is disclosed. The turbomachine comprises a plurality of combustor assemblies disposed in an annular array around a central axis and one or more rails comprising one or more portions that combine to extend in a non-linear path around the central axis, wherein at least one of the one or more portions of the one or more rails is connected to a portion of the turbomachine. The turbomachine further comprises a combustor assembly lift arm comprising a moveable support arm comprising a first end and a second end, a combustor assembly engagement frame connected to the first end of the moveable support arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly, and a connection fixture connected to the second end of the moveable support arm, wherein the connection fixture connects the combustor assembly lift arm to the one or more rails.

[0009] These and additional features provided by the embodiments discussed herein will be more fully understood in view of the following detailed description, in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The embodiments set forth in the drawings are illustrative and exemplary in nature and not intended to limit the inventions defined by the claims. The following detailed description of the illustrative embodiments can be understood when read in conjunction with the following drawings, where like structure is indicated with like reference numerals and in which:

[0011] FIG. 1 is a side view of a turbomachine according to one or more embodiments shown or described herein;

[0012] FIG. 2 is a side view of a combustion system according to one or more embodiments shown or described herein;

[0013] FIG. 3 is a cross-sectional side view of a combustor assembly according to one or more embodiments shown or described herein;

[0014] FIG. 4 is a perspective view of a combustor assembly lift system according to one or more embodiments shown or described herein; and,

[0015] FIG. 5 is a perspective view of various combustor assembly lift track configurations according to one or more embodiments shown or described herein.

DETAILED DESCRIPTION OF THE INVENTION

[0016] One or more specific embodiments of the present invention will be 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. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.

[0017] 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 of the elements. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements.

[0018] Referring now to FIG. 1, some 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. Generally, the turbomachine 100 comprises an inlet plenum 10S that directs an airstream towards a compressor housed in a compressor casing 110. The airstream is compressed and then discharged to a combustion system I IS, where a fuel, such as natural gas, is burned to provide high-energy combustion gases, which drives the turbine section 120. In the turbine section 120, 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).

[0019] Referring now additionally to FIG. 2, 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. Generally, within each combustor assembly 20, and more specifically the combustion can 12S of the combustor assembly 20, the aforementioned combustion process occurs. In some embodiments, 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.

[0020] Referring additionally to FIG. 3, a cross-sectional side view of an embodiment of a combustor assembly 20 of a turbomachine 100 is illustrated. 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. As shown, 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. For example, the flange 26 may define a plurality of flange holes 72 for attaching the end cover assembly to the combustion casing 22.

[0021] In some embodiments, 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 12S 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 12S, 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"). For example, 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. It should be appreciated that in some embodiments 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.

[0022] 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. [0023] In some embodiments, such as that illustrated in FIG. 32, 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). For example, 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. For example, 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.

[0024] In some embodiments, 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. In particular, 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. Moreover, it should be appreciated that, in some embodiments, 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.

[0025] In some embodiments, the combustion liner 30 may first be installed within a 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 a force limits further installation depth into the transition piece 34. With continued reference to FIG. 2, a combustion can 12S can then be installed into each respective combustor assembly 20. Specifically, 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. [0026] While specific embodiments have been presented herein, it should be appreciated that 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. For example, 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.

10027] With additional reference to FIGS. 4 and 5, a combustor assembly lift system 200 can be provided to help install, remove or re-install the combustor assembly 20 onto the turbomachine 100. Specifically, 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 with the turbomachine 100, and reverse the entire process without the need to exchange the combustor assembly 20 between multiple different lift assemblies.

[0028] The combustor assembly lift system 200 can generally comprise a combustor assembly lift track 210 and a combustor assembly lift arm 220. The combustor assembly lift track 210 can generally comprise one or more rails 212 and a rail connector 218 that combine to provide a place for the combustor assembly lift arm 220 to connect to while providing a path for said connection to traverse. The combustor assembly lift arm 220 can generally comprise a combustor assembly engagement frame 240 and a connection fixture 222 that are respectively connected to a first end 236 and a second end 238 of the moveable support arm 230 and that combine to facilitate the overall lifting, transportation, rotation, alignment installation and/or removal of one or more combustor assemblies 20. The combustor assembly lift system 200 and its constituent elements will be discussed in more detail herein.

[0029] As best illustrated in FIG. 4, the combustor assembly lift arm 220 generally comprises a moveable support arm 230 comprising a first end 236 and a second end 238. The combustor assembly lift arm 220 can further comprise a combustor assembly engagement frame 240 connected to the first end 236 of the moveable support arm 230, wherein the combustor assembly engagement frame 240 is configured to temporarily secure to at least a portion of a combustor assembly 20. The combustor assembly lift arm 220 can also comprise a connection fixture 222 connected to the second end 238 of the moveable support arm 230, wherein the connection fixture 222 is configured to connect the combustor assembly lift arm 220 to a base structure (e.g., a portion of the turbomachine 100 such as a flange 26 or a combustor assembly lift track 210 connected to the turbomachine 100).

[0030] The moveable support arm 230 can generally comprise any support structure that can support the weight of a combustor assembly 20 and move it from a first location (e.g., the floor or a shipping container) and a second location (e.g., the turbomachine 100). The moveable support arm 230 may additionally be moveable such that it can rotate, articulate, extend, bend, telescope and/or otherwise transition between at least any two locations based on its specific configuration.

[0031] In some embodiments, the moveable support arm 230 may comprise a plurality of portions such as, for example, a first portion 231, a second portion 232 and potentially a third portion 233 in a variety of configurations such as illustrated in FIG. 4. For example, in some embodiments, the first portion 231, second portion 232 and third portion 233 may be connected to one another in sequence (e.g., the first portion 231 and the third portion 233 connected to opposite ends of the second portion 232). In such embodiments, the first portion 231, second portion 232 and third portion 233 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.

[0032] In some embodiments, the moveable support arm 230 may comprise a plurality of portions (e.g., the second portion 232 and the third portion 233) connected to a single portion (e.g., the first portion 231). For example, the second portion 232 and the third portion 233 may split away from the first portion 231 in a V-shaped configuration to assist with the connection to the combustor assembly 20 between the second portion 232 and the third portion 233. In even some embodiments, the second portion 232 and the third portion 233 may be connected to a single end of the first portion 231. Alternatively, the second portion 232 and the third portion 233 may be offset from one another with their respective connections to the first portion 231.

[0033] In some embodiments, the moveable support arm 230 can comprise one or more rotatable connections. For example, if the moveable support arm 230 comprises a first portion 231 and a second portion 232, the first portion 231 may be rotatably connected to the second portion 232. Likewise, one or both of the first portion 231 and the second portion 232 may be rotatably connected to one or more additional portions, such as a third portion 233, of the moveable support arm 230. Rotatable connections can comprise any connection that facilitates the changing of the angle between two components (e.g., first portion 231 and second portion 232). For example, in some embodiments, a rotatable connection may comprise a pin connection or a ball-and-socket connection that facilitates the relative rotation between the two components. Such embodiments may additionally or alternatively comprise a bolt, screw, tension device or any other suitable mechanism for temporarily adjusting and securing a given angle.

[0034] In some embodiments, the moveable support arm 230 may comprise a telescopic structure wherein part or all of the moveable support arm 230 can extend and contract via telescoping parts. For example, a first portion 231 may telescope away from and into a second portion 232 of the moveable support arm 230. In such embodiments, the entirety of the moveable support arm 230 may comprise a telescopic structure, or just a portion of the moveable support arm 230 may comprise a telescopic structure.

[0035] While specific configurations of the moveable support arm 230 have been disclosed herein, 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 supporting the weight of a combustor assembly 20 and moving it between two more locations.

[0036] Still referring to FIG. 4, the combustor assembly lift arm 220 can further comprise a combustor assembly engagement frame 240 connected to an end of the moveable support arm 230 that is configured to temporarily secure to at least a portion of a combustor assembly 20.

[0037] The combustor assembly engagement frame 240 can comprise a variety of configurations to facilitate temporary securement to combustor assemblies 20. For example, in some embodiments, 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. More specifically, in such embodiments, the combustor assembly engagement frame 240 may comprise two or more portions mat 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.

[0038] In some embodiments, 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, clamps or the like. For example, the combustor assembly engagement frame 240 may comprise a plurality of holes that may be aligned with corresponding holes on the combustor assembty 20. Once aligned, bolts may be passed through both sets of corresponding holes to temporarily secure the combustor assembly 20 to the combustor assembly engagement frame 240.

[0039] 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 arm 220.

[0040] The combustor assembly engagement frame 240 may be connected to the moveable support arm 230 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 a turbomachine 100. For example, in some embodiments, the combustor assembly engagement frame 240 may be rotatably connected to the moveable support arm 230 such that the combustor assembly engagement frame 240 and the moveable support arm 230 may rotate with respect to one another. The rotational connection may help facilitate rotational orientation between the combustor assembly 20 and its respective slot in the turbomachine 100. The rotational connection 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 moveable support arm 230.

[0041] The combustor assembly engagement frame 240 may be connected to the moveable support arm 230 at a variety of locations. For example, when moveable support arm 230 comprises a first end 236 and a second end 238, the combustor assembly engagement frame 240 can be connected to the first end 236 of the moveable support arm 230 while the connection fixture 222 (that connects the moveable support arm 230 to a based structure such as the turbomachine 100) can be connected to the second end 238.

[0042] Still referring to FIG. 4, the combustor assembly lift arm 220 can further comprise a connection fixture 222. The connection fixture 222 can be connected to the moveable support arm 230 and be configured to connect the combustor assembly lift arm 220 to a base structure.

[0043] The connection fixture 222 can be disposed at a variety of locations on the moveable support arm 230 and comprise a variety of configurations. For example, when the moveable support arm 230 comprises a first end 236 and a second end 238, the combustor assembly engagement frame 240 can be connected to the first end 236 of the moveable support arm 230 while the connection fixture 222 can be connected to the second end 238. Moreover, the connection fixture 222 can comprise any configuration that suitably secures the moveable support arm to a base structure when a combustor assembly 20 is temporarily secured to the combustor assembly engagement frame 240. For example, the connection support 222 may comprise one or more plates, caps, clamps, grips, wheels, disks or combinations thereof.

[0044] The connection fixture 222 can facilitate the connection between the moveable support arm 230 (and the overall combustor assembly lift arm 220) to a variety of base structures (and locations on said base structures).

[0045] For example, the base structure may comprise the turbomachine 100 itself. In such embodiments, the connection fixture 222 may connect the moveable support arm 230 to one or more points on the turbomachine 100 such as one or more locations on its exterior structure. In some embodiments, the base structure may comprise a flange 26. For example, the connection fixture 222 may connect the moveable support arm 230 to a flange 26 that does not have a combustor assembly 20 attached thereto. The connection fixture 222 may comprise a plate, cap or the like secured to the flange 26 using one or more bolts passing through the flange holes 72 on the flange 26. The combustor assembly lift arm 220 may then be utilized to install or remove combustor assemblies 20 with respect to the other slots and flanges 72 on the turbomachine 100, such as combustor assemblies 20 directly adjacent the attached connection fixture 222 or elsewhere about the annular array.

[0046] In some embodiments, the base structure may comprise a combustor assembly lift track 210 secured to the turbomachine 100 such that the combustor assembly lift arm 220 may move along the combustor assembly lift track 210 to help transport, lift, align, install, and remove combustor assemblies 20 into their respective slots of the turbomachine 20.

[0047] With reference to FIGS. 4 and 5, a combustor assembly lift track 210 can generally comprise one or more rails 212 and a rail connector 218 configured to connect the one or more rails 212 to at least a portion of the turbomachine 100.

[0048] The one or more rails 212 can comprise one or more portions that combine to extend in a non-linear path that can support and direct the movement of a combustor assembly lift arm 220 with a combustor assembly 20 temporarily secured thereto. The non-linear path can comprise a variety of layouts that may facilitate the movement of the combustor assembly lift arm 220 and a secured combustor assembly 20 around all or part of the annular array of combustor assemblies 20 of the turbomachine 100.

[0049] For example, in some embodiments, the non-linear path may comprise a curved path such that it comprises a continuous curve around all or a portion of the annular array of combustor assemblies 20. In such embodiments, the one or more rails 212 may comprise one continuous portion or may comprise a plurality of portions that combine to form a continuous curved path.

[0050] In some embodiments, the non-linear path may comprise a bent or angled path. For example, in some embodiments the one or more rails 212 may comprise at least two portions connected to one another at an angle. Such embodiments may form a partial or complete path around the annular array of combustor assemblies 20 one or more distinct angles in the combustor assembly lift track 210.

[0051] The non-linear path may further extend for any portion of the annular array of combustor assemblies 20 of the turbomachine. For example, in some embodiments, the non-linear path of the combustor assembly lift track 210 may comprise a circle that covers the entire annular array of combustor assemblies 20. In some of these embodiments, the one or more rails 212 may comprise a single portion that forms the circle. In other embodiments, the one or more rails 212 may comprise a plurality of portions that combine to form the circle. Furthermore, in some embodiments, the one or more rails 212 may comprise a non-linear path that traverses only a portion of the circle of the annular array of combustor assemblies. For example, the one or more rails 212 may extend for only a few combustor assemblies such as for half, quarter or other finite amount of combustor assemblies 20.

[0052] The combustor assembly lift track 210 may comprise a variety of configurations of rails that form the non-linear path. For example, referring to FIG. 5, a first rail configuration 213 may comprise a single rail that is disposed over one or more combustor assemblies 20 of the turbomachine 100. In some embodiments, a second rail configuration 214 may comprise two or more parallel rails that are disposed over one or more combustor assemblies 20 of the turbomachinc 100. In some embodiments, a third rail configuration 2 IS may comprise a single rail that is disposed adjacent one or more combustor assemblies 20 (e.g., on the outer periphery of the one or more combustor assemblies 20 such as when the combustor assembly lift track 210 is not connected directly to the flanges 26 of the turbomachine 100).

[0053] While specific configurations of the one or more rails 212 of the combustor assembly lift track 210 have been disclosed herein, it should be appreciated that these are exemplary only and not intended to be limiting. Additional or alternative configurations may also be realized.

[0054] The rail connector 218 of the combustor assembly lift track 210 can be attached to at least one of the one or more portions of the one or more rails 212, wherein the rail connector 218 is configured to connect the one or more rails 212 to at least a portion of the turbomachine 100.

[0055] In some embodiments, the rail connector 218 may be configured to connect the one or more rails 212 to at least one flange 26 of the turbomachine 100 (such as illustrated by the first rail configuration 213 and second rail configuration 214 in FIG. 5.) Such embodiments may utilize open flange holes 72 in the flanges 26 of one or more combustor assemblies 20 such as by securing the one or more rails 212 by passing bolts through said flange holes 72.

[0056] In some embodiments, the rail connector 218 may be configured to connect the one or more rails 212 to at least one external mounting point on the turbomachine 100 (such as illustrated by the third rail configuration 215 in FIG. 5). External mounting points can comprise any exterior structure of the turbomachine 100 including those around the combustor assemblies 20 or elsewhere around the overall external casing of the turbomachine 100. Such embodiments may facilitate installing or removing combustor assemblies 20 without blocking access to any slots for other combustor assemblies 20.

[0057] The combustor assembly lift track 210 and the combustor assembly lift arm 220 may thereby be used along or in combination on a turbomachine 100 to facilitate the transportation, lifting, alignment, installation and/or removal of combustor assemblies 20 onto the turbomachine 100. For example, a turbomachine 100 may comprise the plurality of combustor assemblies 20 disposed in the annular array around a central axis A. The turbomachine may further comprise one or more rails 212 comprising one or more portions that combine to extend in a non-linear path around the central axis, wherein at least one of the one or more portions of the one or more rails 212 is connected to a portion of the turbomachine 100 (i.e., to form the combustor assembly lift track 210). In some embodiments, the turbomachine 100 may further comprise the combustor assembly lift arm 220 comprising the moveable support arm 230 comprising the first end 236 and second end 238, wherein the combustor assembly engagement frame 240 is connected to the first end 236, and wherein the connection fixture 222 is connected to the second end 238.

[0058] It should now be appreciated that combustor assembly lift arms, combustor assembly lift tracks, combustor assembly lift systems and turbomachines as disclosed herein can be provided to help transport, lift, align, install, and remove combustor assemblies into turbomachines. Such embodiments can facilitate proper alignment specific to each combustor assembly while enabling a continuous transportation, installation and/or removal process via a single combustor assembly lift system. These combustor assembly lift arms, combustor assembly lift tracks, combustor assembly lift systems and turbomachines may thereby provide for simpler and faster overall installation and removal activities.

[0059] While 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 can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects 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.