Patent Description:
Turbomachines are utilized in a variety of industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and a fuel (e.g., natural gas) mix within the combustion section and burn in a combustion chamber to generate high pressure and high temperature combustion gases. The combustion gases flow from the combustion section into the turbine section where they expand to produce work. For example, expansion of the combustion gases in the turbine section may rotate a rotor shaft connected, e.g., to a generator to produce electricity. The combustion gases then exit the gas turbine via the exhaust section.

More specifically, the combustion section mixes large quantities of fuel and compressed air and burns the resulting mixture. The combustion section of a 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.

Combustion cans 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 one or more combustion cans, a significant amount of force may be required to properly lift, position and/or align each combustion can with respect to the gas turbine. <CIT> relates to an apparatus for disassembling and assembling a gas turbine combustor. <CIT> relates to a transition piece assembly jig including a transition piece carrier. <CIT> relates to a mounting/demounting device for combustor for use in a gas turbine. Accordingly, alternative systems and methods for installing and removing combustion cans would be welcome in the art.

Aspects and advantages of the systems and methods in accordance with the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology.

In accordance with one aspect of the invention, a system for installation or removal of one or more combustion cans from a combustion section of a turbomachine is provided. The system includes an annular track that surrounds the turbomachine. The annular track includes an upper rail portion and a lower rail portion removably coupled to one another. The system further includes a drive assembly operably coupled to the annular track. The drive assembly includes a drive chain that extends along the annular track. The system further includes a plurality of carts rotatably coupled to the annular track and connected to the drive chain such that operation of the drive assembly alters a circumferential position of the plurality of carts with respect to an axial centerline of the turbomachine. The system further includes a plurality of combustion can cradle assemblies each coupled to a respective cart of the plurality of carts. Each combustion can cradle assembly of the plurality of combustion can cradle assemblies is configured to removably couple to a combustion can of the one or more combustion cans.

In accordance with another aspect of the invention, a method for installation of one or more combustion cans from a combustion section of turbomachine is provided. The method includes positioning a lower rail portion of an annular track partially about a combustion section of a turbomachine. A second portion of a drive chain extends along the lower rail portion. The method further includes lifting an upper rail portion of the annular track. A first portion of the drive chain extends along the upper rail portion. A first plurality of carts movably coupled to the upper rail portion and coupled to the first portion of the drive chain. Each cart of the first plurality of carts coupled to a respective combustion can cradle assembly in a first plurality of combustion can cradle assemblies. Each combustion can cradle assembly in the first.

plurality of combustion can cradle assemblies is removably coupled to a combustion can in a first plurality of combustion cans. The method further includes coupling the upper rail portion to the lower rail portion. The method further includes coupling the first portion of the drive chain to the second portion of the drive chain. The method further includes operating a drive assembly to move the first plurality of carts from the upper rail portion of the annular track to the lower rail portion of the annular track. The method further includes installing the first plurality of combustion cans into a lower half of the combustion section of the turbomachine.

These and other features, aspects and advantages of the present systems and methods will become better understood with reference to the following description and appended claims.

A full and enabling disclosure of the present systems and methods, including the best mode of making and using the present systems and methods, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:.

Reference now will be made in detail to embodiments of the present systems and methods, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation, rather than limitation of, the technology. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention without departing from the scope of the claimed technology. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims.

The term "fluid" may be a gas or a liquid. The term "fluid communication" means that a fluid is capable of making the connection between the areas specified.

As used herein, the terms "upstream" (or "forward") and "downstream" (or "aft") refer to the relative direction with respect to fluid flow in a fluid pathway. However, the terms "upstream" and "downstream" as used herein may also refer to a flow of electricity. The term "radially" refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term "axially" refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component and the term "circumferentially" refers to the relative direction that extends around the axial centerline of a particular component.

Terms of approximation, such as "about," "approximately," "generally," and "substantially," are not to be limited to the precise value specified. For example, the approximating language may refer to being within a <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, or <NUM> percent margin in either individual values, range(s) of values and/or endpoints defining range(s) of values. When used in the context of an angle or direction, such terms include within ten degrees greater or less than the stated angle or direction. For example, "generally vertical" includes directions within ten degrees of vertical in any direction, e.g., clockwise or counter-clockwise.

For example, a process, method, article, or apparatus that comprises a list of features is not necessarily limited only to those features but may include other features not expressly listed or inherent to such process, method, article, or apparatus. Further, unless expressly stated to the contrary, "or" refers to an inclusive- or and not to an exclusive- or.

Referring now to the drawings, <FIG> illustrates a schematic diagram of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine <NUM>. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to a land-based and/or industrial gas turbine unless otherwise specified in the claims. For example, the invention as described herein may be used in any type of turbomachine including but not limited to a steam turbine, an aircraft gas turbine, or a marine gas turbine.

As shown, gas turbine <NUM> generally includes an inlet section <NUM>, a compressor section <NUM> disposed downstream of the inlet section <NUM>, a plurality of combustors (not shown) within a combustion section <NUM> disposed downstream of the compressor section <NUM>, a turbine section <NUM> disposed downstream of the combustion section <NUM>, and an exhaust section <NUM> disposed downstream of the turbine section <NUM>. Additionally, the gas turbine <NUM> may include one or more shafts <NUM> coupled between the compressor section <NUM> and the turbine section <NUM>.

The compressor section <NUM> may generally include a plurality of rotor disks <NUM> (one of which is shown) and a plurality of rotor blades <NUM> extending radially outwardly from and connected to each rotor disk <NUM>. Each rotor disk <NUM> in turn may be coupled to or form a portion of the shaft <NUM> that extends through the compressor section <NUM>.

The turbine section <NUM> may generally include a plurality of rotor disks <NUM> (one of which is shown) and a plurality of rotor blades <NUM> extending radially outwardly from and being interconnected to each rotor disk <NUM>. Each rotor disk <NUM> in turn may be coupled to or form a portion of the shaft <NUM> that extends through the turbine section <NUM>. The turbine section <NUM> further includes an outer casing <NUM> that circumferentially surrounds the portion of the shaft <NUM> and the rotor blades <NUM>, thereby at least partially defining a hot gas path <NUM> through the turbine section <NUM>.

During operation, a working fluid such as air flows through the inlet section <NUM> and into the compressor section <NUM> where the air is progressively compressed, thus providing pressurized air to the combustors of the combustion section <NUM>. The pressurized air is mixed with fuel and burned within each combustor to produce combustion gases <NUM>. The combustion gases <NUM> flow through the hot gas path <NUM> from the combustion section <NUM> into the turbine section <NUM>, wherein energy (kinetic and/or thermal) is transferred from the combustion gases <NUM> to the rotor blades <NUM>, causing the shaft <NUM> to rotate. The mechanical rotational energy may then be used to power the compressor section <NUM> and/or to generate electricity. The combustion gases <NUM> exiting the turbine section <NUM> may then be exhausted from the gas turbine <NUM> via the exhaust section <NUM>.

Referring now to <FIG>, 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. <FIG> illustrates an example of a gas turbine <NUM>. Generally, the gas turbine <NUM> comprises an inlet section <NUM> that directs an airstream towards a compressor section <NUM> housed in a compressor casing <NUM>. The airstream is compressed and then discharged to a combustion section <NUM>, where a fuel, such as natural gas, is burned to provide high-energy combustion gases, which drives the turbine section <NUM>. In the turbine section <NUM>, 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).

As shown, the gas turbine <NUM> may define a cylindrical coordinate system having an axial direction Agt extending along the axial centerline <NUM>, a radial direction Rgt perpendicular to the axial centerline <NUM>, and a circumferential direction Cgt extending around the axial centerline <NUM>. The upper rail portion <NUM> may extend along the circumferential direction Cgt of the gas turbine <NUM>. The upper rail portion <NUM> may extend along the circumferential direction Cgt of the gas turbine <NUM> (See <FIG>).

Referring now additionally to <FIG>, an embodiment of the combustion section <NUM> may comprise at least one combustor assembly <NUM>. Some gas turbines <NUM>, such as that illustrated in <FIG>, may comprise a plurality of combustor assemblies <NUM> disposed in an annular array around a axial centerline <NUM>. Generally, within each combustor assembly <NUM> (and more specifically, the combustion can <NUM> of the combustor assembly <NUM>) the aforementioned combustion process occurs. In some embodiments, combustor assemblies <NUM> can comprise one or more auxiliary systems such as flame detection systems to monitor the flame burning in some of the combustor assemblies <NUM>. Such flame detection systems may be in the form of a flame scanner, a portion of which may be inserted within the combustor assembly <NUM>. Additional or alternative auxiliary systems <NUM> may similarly be incorporated into combustor assemblies <NUM> to monitor, control and/or impact one or more of the combustor assembly processes.

Referring additionally to <FIG>, a cross-sectional side view of an embodiment of a combustor assembly <NUM> of a gas turbine <NUM> is illustrated. The combustor assembly <NUM> may generally include at least a combustion can <NUM> and potentially a substantially cylindrical combustion casing <NUM> secured to a portion of a gas turbine casing <NUM>, such as a compressor discharge casing or a combustion wrapper casing. As shown, a flange <NUM> may extend outwardly from an upstream end of the combustion casing <NUM>. The flange <NUM> may generally be configured such that an end cover assembly <NUM> of a combustor assembly <NUM> may be secured to the combustion casing <NUM>. For example, the flange <NUM> may define a plurality of flange holes <NUM> for attaching the end cover assembly <NUM> to the combustion casing <NUM>.

In some embodiments, the combustor assembly <NUM> may also include an internal flow sleeve <NUM> and/or a combustion liner <NUM> substantially concentrically arranged within the flow sleeve <NUM>. The combustor assembly <NUM> may comprise a unibody combustor assembly <NUM> comprising the combustion can <NUM> and at least one of the flow sleeve <NUM> or combustion liner <NUM> connected to the combustion can <NUM> as a single pre-assembled structure, or the combustor assembly <NUM> may comprise an assembly where the combustion can <NUM>, flow sleeve <NUM> and combustion liner <NUM> all connect directly to the gas turbine <NUM> such as to the turbine casing <NUM> (sometimes referred to as a combustion discharge casing or "CDC"). For example, the flow sleeve <NUM> and the combustion liner <NUM> may extend, at their downstream ends, to a double walled transition duct, including an impingement sleeve <NUM> and a transition piece <NUM> disposed within the impingement sleeve <NUM>. It should be appreciated that in some embodiments the impingement sleeve <NUM> and the flow sleeve <NUM> may be provided with a plurality of air supply holes <NUM> over a portion of their surfaces, thereby permitting pressurized air from the compressor section <NUM> to enter the radial space between the combustion liner <NUM> and the flow sleeve <NUM>.

The combustion liner <NUM> of the combustor assembly <NUM> may generally define a substantially cylindrical combustion chamber <NUM>, wherein fuel and air are injected and combusted to produce hot gases of combustion. Additionally, the combustion liner <NUM> may be coupled at its downstream end to the transition piece <NUM> such that the combustion liner <NUM> and the transition piece <NUM> generally define a flow path for the hot gases of combustion flowing from each combustor assembly <NUM> to the turbine section <NUM> of the gas turbine <NUM>.

In some embodiments, such as that illustrated in <FIG>, the transition piece <NUM> may be coupled to the downstream end of the combustion liner <NUM> with a seal <NUM> (e.g., a compression seal). For example, the seal <NUM> may be disposed at the overlapping ends of the transition piece <NUM> and combustion liner <NUM> to seal the interface between the two components. For example, a seal <NUM> 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 <NUM> and the transition piece <NUM> need not be sealed with a compression seal <NUM>, but may generally be sealed by any suitable seal known in the art.

In some embodiments, the combustion liner <NUM> may also include one or more male liner stops <NUM> that engage one or more female liner stops <NUM> secured to the flow sleeve <NUM> or, in combustor assemblies <NUM> without a flow sleeve <NUM>, the combustion casing <NUM>. In particular, the male liner stops <NUM> may be adapted to slide into the female liner stops <NUM> as the combustion liner <NUM> is installed within the combustor assembly <NUM> to indicate the proper installation depth of the combustion liner <NUM> as well as to prevent rotation of the liner <NUM> during operation of the gas turbine <NUM>. Moreover, it should be appreciated that, in some embodiments, male liner stops <NUM> may be additionally or alternatively disposed on the flow sleeve <NUM> or combustion casing while the female liner stops <NUM> are disposed on the combustion liner <NUM>.

In some embodiments, the combustion liner <NUM> may first be installed within a combustor assembly <NUM>, by being pushed into the combustor assembly <NUM>. For example, the combustion liner <NUM> can be pushed into the combustor assembly <NUM> until a force limits further installation depth into the transition piece <NUM>. With continued reference to <FIG>, a combustion can <NUM> can then be installed into each respective combustor assembly <NUM>. Specifically, the combustion can <NUM> can be positioned, aligned and inserted such that its end cover assembly <NUM> can then abut against the flange <NUM> of the combustor assembly <NUM>.

While specific embodiments have been presented herein, it should be appreciated that the combustor assembly <NUM> 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 gas turbine <NUM>. For example, the combustor assembly <NUM> may be completely assembled prior to installation onto the gas turbine <NUM> (e.g., a unibody combustor assembly <NUM>), may be partly assembled prior to installation on the gas turbine <NUM>, may be completely assembled while connected to the gas turbine <NUM>, or combinations thereof.

<FIG> illustrate various aspects or embodiments or a system <NUM> for installation or removal of one or more combustion cans <NUM> from a combustion section <NUM> of a turbomachine in accordance with the present disclosure. As will be discussed, the system <NUM> may facilitate the installation and/or removal of one or more combustion cans <NUM> from the combustor assemblies <NUM> of the gas turbine <NUM>. For example, the system <NUM> may advantageously be a compact design that allows for one or more combustion cans <NUM> to be installed, removed, or reinstalled without having to fully disassemble the gas turbine <NUM>. As may be appreciated by those of skill in the art, gas turbines (such as the gas turbine <NUM>) are often crowded with various pipings and external hardware that can make accessing the combustion section (e.g., for installation or removal of one or more combustion cans <NUM>) difficult. The compactness of the system <NUM> described herein may advantageously be used to install and/or remove combustion cans <NUM> into a combustor assembly <NUM> without having to remove external hardware and/or pipings.

<FIG> each illustrate a forward view of a combustion section <NUM> of a gas turbine <NUM>. More particularly, <FIG> illustrate the sequential steps of installing combustion cans <NUM> into the respective combustor assemblies <NUM> by using the system <NUM> described herein. For example, in <FIG>, the combustion section <NUM> does not have any combustion cans <NUM> installed into the combustor assemblies <NUM>, but a lower rail portion <NUM> of an annular track <NUM> may be positioned at least partially about the gas turbine <NUM>. For example, the lower rail portion <NUM> of the annular track may be initially assembled and may be supported by one or more vertical legs <NUM>. In <FIG>, an upper rail portion <NUM> of the annular track <NUM>, which may be carrying a first plurality <NUM> of combustion cans <NUM>, may be lifted and lowered onto the lower rail portion <NUM> of the annular track <NUM> (e.g., via a crane or other lifting means). As shown, a first portion <NUM> (or first half) of a drive chain <NUM> may extend along the upper rail portion <NUM> during the assembly of the annular track <NUM>, and a second portion <NUM> (or second half) of the drive chain <NUM> may extend along the lower rail portion <NUM> during assembly of the annular track <NUM>. In <FIG>, the upper rail portion <NUM> of the annular track <NUM> may be coupled to the lower rail portion <NUM>, and the first portion <NUM> of the drive chain <NUM> may be coupled to the second portion <NUM> of the drive chain <NUM>. Once coupled, both the drive chain <NUM> and the annular track <NUM> may extend along the circumferential direction Cgt of the gas turbine <NUM> entirely around the axial centerline <NUM> of the gas turbine <NUM>. Additionally, the drive chain <NUM> may be movable relative to the annular track <NUM> in the circumferential direction Cgt. In this way, as discussed in more detail below, the first plurality <NUM> of combustion cans <NUM> may be rotatably coupled to the annular track <NUM> via one or more carts <NUM>, with the one or more carts <NUM> being attached to the drive chain <NUM>.

Subsequently, as illustrated in <FIG>, a drive assembly <NUM> coupled to drive chain <NUM> may be operated to adjust a circumferential position of the first plurality <NUM> of combustion cans <NUM> (e. g, operation of the drive assembly <NUM> moves the drive chain <NUM>, the carts <NUM>, and the first plurality <NUM> of combustion cans <NUM>). For example, the drive assembly <NUM> may include a motor <NUM> coupled to the drive chain <NUM>, such that operation of the motor <NUM> adjusts a circumferential position of the first plurality <NUM> of combustion cans <NUM>. In <FIG>, an operation of the drive assembly <NUM> may be halted once the first plurality <NUM> of combustion cans <NUM> are disposed below the horizontal plane <NUM> of the gas turbine <NUM> (e.g., each combustion can coupled to the lower rail portion <NUM> of the annular track <NUM>). At which point, the upper rail portion <NUM> may be decoupled from the lower rail portion <NUM>, and the first portion <NUM> of the drive chain <NUM> may be decoupled from the second portion <NUM> of the drive chain <NUM>. As shown in <FIG>, the upper rail portion <NUM> of the annular track <NUM> may be lowered, coupled to a second plurality <NUM> of combustion cans <NUM>, and subsequently re-lifted (e.g., by a crane or other lifting means). As shown in <FIG>, the upper rail portion <NUM> may be recoupled to the lower rail portion <NUM> of the annular track <NUM>, and the first plurality <NUM> of combustion cans <NUM> and the second plurality <NUM> of combustion cans <NUM> may be installed into the respective combustor assemblies <NUM> of the combustion section <NUM>. As a result of the system and method shown and described above with reference to <FIG>, the combustion section <NUM> shown in <FIG> may be yielded (e.g., having all the combustion cans <NUM> installed into the respective combustor assemblies <NUM> of the combustion section <NUM>).

<FIG> each illustrate one or more exemplary features or aspects that may be incorporated into the system <NUM> for installing and/or removing one or more combustion cans <NUM> discussed above with reference to <FIG>. As shown in collectively by <FIG>, the system <NUM> may include an annular track <NUM> surrounding the turbomachine (e.g., the gas turbine <NUM>). For example, the annular track <NUM> may extend <NUM>° around the axial centerline <NUM> of the gas turbine <NUM>. Particularly, the annular track <NUM> may be disposed around the combustion section <NUM> of the gas turbine, such that the annular track <NUM> surrounds the combustor assemblies <NUM> of the combustion section <NUM>. For example, the annular track <NUM> may extend along a circular path having a center point along the axial centerline <NUM> of the gas turbine <NUM>.

In exemplary embodiments, the annular track <NUM> may an upper rail portion <NUM> and a lower rail portion <NUM> removably coupled to one another. For example, the upper rail portion <NUM> may couple to the lower rail portion <NUM>, such that the lower rail portion <NUM> and the upper rail portion <NUM> collectively surround the axial centerline <NUM> of the gas turbine <NUM>. In many embodiments, the upper rail portion <NUM> and the lower rail portion <NUM> of the annular track <NUM> may collectively surround the gas turbine <NUM> radially outward from the combustor assemblies <NUM> with respect to the radial direction Rgt of the gas turbine <NUM>. In many embodiments, a horizontal plane <NUM> that is parallel to the ground may divides the combustion section <NUM> into an upper half and a lower half. For example, the lower rail portion <NUM> may extend around the lower half of the combustion section <NUM> (e.g., about <NUM>° below the horizontal plane), and the upper rail portion <NUM> may extend around the upper half of the combustion section (e.g., about <NUM>° above the horizontal plane <NUM>). In exemplary embodiments, the upper rail portion <NUM> may extend about the upper half of the combustion section <NUM>, such that combustion cans <NUM> coupled to the upper rail portion <NUM> may be installed into a combustor assembly <NUM> in the upper half of the combustion section <NUM>. Similarly, the lower rail portion <NUM> may extend about the lower half of the combustion section <NUM>, such that combustion cans <NUM> coupled to the lower rail <NUM> may be installed in a combustor assembly <NUM> in the lower half of the combustion section <NUM>.

As shown best in <FIG> and <FIG>, in some embodiments, the annular track <NUM> (including the upper rail portion <NUM> and the lower rail portion <NUM>) may define an interior <NUM>. For example, the annular track <NUM> may include side walls <NUM> spaced apart from one another, a solid outer wall <NUM> (e.g., a radially outer wall with respect to the radial direction Rgt of the gas turbine <NUM>), and an open inner wall <NUM> (e.g., radially inner wall with respect to the radial direction Rgt of the gas turbine <NUM>). The side walls <NUM>, the solid outer wall <NUM>, and the open inner wall <NUM> may collectively define the interior <NUM>. In exemplary embodiments, the open inner wall <NUM> may define a circumferential gap that extends both axially and circumferentially with respect to the axial centerline <NUM> of the gas turbine <NUM>. Particularly, both the circumferential gap and the interior <NUM> may extend circumferentially through the entire annular track <NUM>. In various implementations, the plurality of carts <NUM> may be rotatably mounted to the annular track <NUM> (e.g., via one or more wheels <NUM> disposed in the interior <NUM>). For example, a portion of each cart <NUM> may extend through the circumferential gap and into the interior <NUM> of the annular track <NUM>, where one or more wheels <NUM> may provide each cart <NUM> with the ability to move circumferentially around the annular track <NUM> with respect to an axial centerline of the gas turbine <NUM>.

In exemplary embodiments, the system <NUM> may further include a drive assembly <NUM> operably coupled to the annular track <NUM>. The drive assembly <NUM> may include the drive chain <NUM> that extends along the annular track <NUM>. In exemplary embodiments, the drive chain <NUM> may be a metal roller chain (such as a steel bush roller chain) having a plurality of inner links, outer links, and rollers. In various implementations, the drive assembly <NUM> may include one or more sprockets <NUM> rotatably coupled to the drive chain <NUM>. Particularly, the one or more sprockets <NUM> may be coupled to the drive chain <NUM> such that a rotation of the sprocket <NUM> causes translational movement of the drive chain <NUM>.

In many embodiments, the drive assembly <NUM> may includes a motor <NUM> (such as an electric motor, a hydraulic motor, gas motor, or other suitable motor for powering the drive assembly <NUM>). The motor <NUM> may include an output shaft <NUM> to a gearbox <NUM>. The gearbox <NUM> may be connected to the motor <NUM> and connected to the one or more sprockets <NUM>. For example, the gearbox <NUM> may include an input shaft connected to an output shaft of the motor <NUM>. Additionally, the gearbox <NUM> may include an output shaft coupled to the sprocket <NUM>, and the sprocket <NUM> may be coupled to the drive chain <NUM> such that operation of the motor <NUM> alters a circumferential position of the plurality of carts <NUM> with respect to an axial centerline <NUM> of the turbomachine. For example, the output shaft of the gearbox <NUM> may be coupled (e.g., fixedly coupled via welding or brazing) to a sprocket <NUM> of the one or more sprockets <NUM>, such that the sprocket <NUM> of the one or more sprockets <NUM> rotates with the output shaft of the gearbox <NUM>. In this way, the rotational output of the motor <NUM> drives the gearbox <NUM>, which turns the sprocket <NUM> and causes a translational movement of the drive chain <NUM> in the circumferential direction Cgt of the gas turbine <NUM>.

In many embodiments, the system <NUM> may further include a plurality of carts <NUM> rotatably coupled to the annular track <NUM> and connected to the drive chain <NUM> such that operation of the drive assembly <NUM> alters a circumferential position of the plurality of carts <NUM> with respect to an axial centerline of the turbomachine (e.g., the gas turbine <NUM>). In many embodiments, each cart <NUM> of the plurality of carts <NUM> may include a main body <NUM> and a track member <NUM> extending from the main body <NUM> and into the annular track <NUM>. For example, the track member <NUM> may extend from the main body <NUM> of the cart <NUM>, through the circumferential gap, and into the interior <NUM> of the annular track <NUM>. In many embodiments, each cart <NUM> of the plurality of carts <NUM> may include one or more wheels <NUM> rotatably coupled to the cart <NUM> (e.g., via one or more pins or bearings). Particularly, the one or more wheels <NUM> may be coupled to the track member <NUM> of each cart <NUM>, such that the wheels <NUM> are disposed within the interior <NUM> of the annular track <NUM> and in rotatable contact with the annular track <NUM>.

In many embodiments, as shown best in <FIG>, the cart <NUM> may include a tab portion <NUM> extending from the main body <NUM> (e.g., first axially from the main body <NUM> then radially with respect to an axial centerline <NUM> of the combustion can cradle assembly <NUM>). Additionally, a jacking bolt <NUM> may extends through the tab portion <NUM> and into the combustion can cradle assembly <NUM>, such that rotation of the jacking bolt <NUM> adjusts an axial position of the combustion can cradle assembly <NUM> (e.g., along the axial direction ACA). For example, the jacking bolt <NUM> may be threadably received by the lower pressure plate <NUM> of the combustion can cradle assembly <NUM>, such that rotation of the jacking bolt <NUM> alters an axial position of the combustion can cradle assembly <NUM> relative to the cart <NUM>.

In exemplary embodiments, as shown throughout <FIG>, the system <NUM> may further include a plurality of combustion can cradle assemblies <NUM> each coupled to a respective cart <NUM> of the plurality of carts <NUM>. each combustion can cradle assembly <NUM> of the plurality of combustion can cradle assemblies <NUM> may be configured to removably couple to a combustion can <NUM>. For example, each combustion can cradle assembly <NUM> may removably couple to and securely hold a combustion can <NUM>. Particularly, <FIG> illustrates a perspective view of a combustion can cradle assembly <NUM> coupled to a cart <NUM>, <FIG> illustrates an exploded view of a combustion can cradle assembly <NUM> decoupled from the cart <NUM>.

Additionally, each of the combustion can cradle assemblies <NUM> may be configured to move in any direction relative to the cart <NUM>, in order to adjust a position of the combustion can to which it is attached for alignment with the respective combustor assembly <NUM>. For example, the annular track <NUM>, the carts <NUM>, and the drive assembly <NUM> may be operable to adjust a circumferential position of the combustion can cradle assemblies <NUM> along the circumferential direction Cgt of the gas turbine <NUM>, in order to circumferentially align each combustion can <NUM> with a respective combustor assembly <NUM> for installation therein. Once the combustion can cradle assemblies <NUM> have each been aligned with a respective combustor assembly <NUM> (e.g., by movement of the carts <NUM> along the annular track <NUM>), each combustion can may still require finite adjustments to be fully aligned with the respective combustor assembly <NUM> to which it will be attached. The combustor cradle assembly <NUM> described herein advantageously allows for the finite movements to be made without excessive force on the operator.

<FIG> illustrates a cross-sectional enlarged view of the system <NUM> from along the circumferential direction Cgt of the gas turbine <NUM>. As shown, each combustion can cradle assembly <NUM> of the plurality of combustion can cradle assemblies <NUM> defines a cylindrical coordinate system <NUM> having an axial direction ACA extending along an axial centerline <NUM> of the combustion can cradle assembly <NUM>, a radial direction RCA extending perpendicularly to the axial centerline <NUM> of the combustion can cradle assembly <NUM>, and a circumferential direction CCA extending around the axial centerline <NUM> of the combustion can cradle assembly <NUM>. When the combustion can cradle assembly <NUM> is coupled to a combustion can <NUM>, the axial centerline <NUM> of the combustion can cradle assembly <NUM> may coincide with an axial centerline of the combustion can <NUM> (such that they share a common axial centerline). Each combustion can cradle assembly <NUM> of the plurality of combustion can cradle assemblies <NUM> may be configured to move the along any of the axial direction ACA, the radial direction RCA, and/or the circumferential direction CCA relative to the annular track <NUM> to adjust a position of the combustion can <NUM> contained therein.

As shown, each combustion can cradle assembly <NUM> of the plurality of combustion can cradle assemblies <NUM> may include an upper assembly <NUM>, a lower assembly <NUM>, and one or more threaded rods <NUM>. The upper assembly <NUM> may include an upper pressure plate <NUM> and an upper connection member <NUM>, and the lower assembly <NUM> may include a lower pressure plate <NUM> and a lower connection member <NUM>. As shown, both the upper pressure plate <NUM> and the lower pressure plate <NUM> may extend partially along the circumferential direction CCA of the combustion can cradle assembly <NUM>. For example, both the upper pressure plate <NUM> and the lower pressure plate <NUM> may be contoured to correspond with a combustion can <NUM>, in order to provide for flush contact between the upper and lower pressure plates <NUM> and the combustion can <NUM> (<FIG>).

In many embodiments, as shown in <FIG>, the upper assembly <NUM> and the lower assembly <NUM> may be spaced apart from one another (e.g., spaced apart in the radial direction RCA). In many embodiments, the one or more threaded rods <NUM> may extend between, and couple to, the upper assembly <NUM> and the lower assembly <NUM>. In particular embodiments, the one or more threaded rods <NUM> extends between the upper connection member <NUM> and the lower connection member <NUM>. As shown in <FIG>, the upper connection member <NUM> and the lower connection member <NUM> may extend generally axially with respect to the axial centerline <NUM> of the combustion can assembly.

In particular embodiments, each combustion can cradle assembly <NUM> may include four threaded rods <NUM> extending between the upper assembly <NUM> and the lower assembly <NUM> (e.g., two threaded rods <NUM> on either side of the combustor can). In other embodiments (not shown), the cradle assembly <NUM> may include more or less than four threaded rods <NUM> (such as <NUM>, <NUM>, <NUM>, or up to <NUM>) and should not be limited to any particular number of threaded rods <NUM> unless specifically recited in the claims. Each of the threaded rods <NUM> may be coupled on both ends (e.g., coupled to the upper connection member <NUM> at a first end and coupled to the lower connection member <NUM> at a second end), such that rotation of the threaded rods <NUM> alters the distance between the upper and lower assemblies (e.g., a distance along the radial direction RCA). In this way, rotation of the threaded rods <NUM> in a first direction may increase the radial distance between the upper and lower pressure plates <NUM>, <NUM> (which may allow a combustion can to be removed from the combustion can cradle assembly <NUM>). Similarly, rotation of the threaded rods <NUM> in a second direction may decrease the radial distance between the upper and lower pressure plates <NUM>, <NUM> (which may allow a combustion can to be coupled to the combustion can cradle assembly <NUM>).

As shown in <FIG> and <FIG>, the drive assembly <NUM> may include a motor <NUM> (such as an electric motor, a hydraulic motor, or other suitable motor), a gearbox <NUM> connected to the motor <NUM>, and one or more sprockets <NUM> connected to the gearbox <NUM>. For example, the gearbox <NUM> may include an input shaft and an output shaft, with the input shaft connected to the motor <NUM> and the output shaft connected to the one or more sprockets <NUM>. The gearbox <NUM> may function to transform a rotational input (e.g., input speed and torque) provided by the motor <NUM> to a desired rotational output (e.g., output speed and torque). Alternatively, the drive assembly <NUM> may be a direct drive system (e.g., not having a gearbox), such that the output shaft of the motor <NUM> is directly coupled to the one or more sprockets <NUM>. The one or more sprockets <NUM> may be coupled to the drive chain <NUM>, such that the rotation of the sprocket <NUM> causes the drive chain <NUM> to translationally move in the circumferential direction Cgt of the gas turbine <NUM>.

In many embodiments, as shown in <FIG> and <FIG>, the drive chain <NUM> may be at least partially housed within a chain guide railing <NUM>. The chain guide railing <NUM> may be a rigid member that extends along the annular track <NUM>. For example, the chain guide railing <NUM> may extend circumferentially along the entire annular track <NUM> around the axial centerline <NUM> of the gas turbine <NUM>. In exemplary embodiments, as shown in <FIG> and <FIG>, the drive chain <NUM> may include connection members extending from the drive chain <NUM> to each cart <NUM> of the plurality of carts <NUM>. The connection members may couple to each cart <NUM> of the plurality of carts <NUM> and may allow the carts <NUM> to move with the drive chain <NUM> through the annular track <NUM>. For example, the carts <NUM> may be coupled to the drive chain <NUM> via the connection members and may move circumferentially with the drive chain <NUM>.

<FIG> and <FIG> illustrate a cross sectional view of a bearing assembly <NUM>, which may be incorporated in one of an upper pressure plate <NUM> or a lower pressure plate <NUM> in accordance with embodiments of the present disclosure. As shown, in some embodiments, one of the upper pressure plate <NUM> and/or the lower pressure plate <NUM> may be a bearing assembly <NUM> that provides for movement of the combustion can cradle assembly <NUM> relative to the cart <NUM> (e.g., in one of the axial direction ACA, the radial direction RCA, and/or the circumferential direction CCA). For example, <FIG> may be a cross section of the upper pressure plate <NUM> shown in <FIG> from along the line <NUM>-<NUM>. For example, the bearing assembly <NUM> may include a top plate <NUM> and a concave plate <NUM> fixedly coupled to top plate <NUM> (e.g., via welding or brazing). As shown a guide key <NUM> may be disposed between the top plate and the concave plate for ensuring alignment. Alternatively, the top plate <NUM> and the concave plate <NUM> may be a singular member (e.g., integrally formed as a unitary body). Additionally, the bearing assembly <NUM> may include a bottom plate <NUM> and a convex plate <NUM> fixedly coupled to the bottom plate <NUM> (e.g., via welding or brazing). Alternatively, the bottom plate <NUM> and the convex plate <NUM> may be a singular member (e.g., integrally formed as a unitary body). In many embodiments, one of the base plate or the top plate <NUM> may contact the combustion can <NUM> (such as the base plate in <FIG> and <FIG>). For example, in embodiments where the upper pressure plate <NUM> has a bearing assembly <NUM> construction, the bottom plate <NUM> may contact the combustion can <NUM>. Similarly, in embodiments where the lower pressure plate <NUM> has a bearing assembly <NUM> construction, the top plate <NUM> may contact the combustion can <NUM>. The convex plate <NUM> and the concave plate <NUM> may be in sliding contact with one another, thereby allowing the top and bottom plates <NUM>, <NUM> to move relative to one another. this movement advantageously allows the combustion can <NUM> to be adjusted, moved, aligned, or realigned within the combustion can cradle assembly <NUM> as desired. and a woven fabric disposed between and in contact with the concave plate <NUM> and the convex plate <NUM>.

Referring back to <FIG>, in embodiments where one or both of the upper pressure plate <NUM> and/or the lower pressure plate <NUM> include a bearing assembly <NUM> construction such as the ones shown in <FIG> and <FIG>, the combustion can cradle assembly <NUM> may allow the combustion can <NUM> to be circumferentially moved within the cradle assembly <NUM> (e.g., in the circumferential direction CCA). In such embodiments, as shown, the upper assembly <NUM> may further include a rotation stop member <NUM> extending from the upper pressure plate <NUM>. The rotation stop member <NUM> may extend from the upper pressure plate <NUM> towards the lower pressure plate <NUM> to prevent over-rotation of the combustion can <NUM>. For example, when circumferentially rotating the combustion can <NUM>, the rotation stop member <NUM> will eventually collide with the lower pressure plate <NUM>, thereby preventing over-rotation.

As illustrated in <FIG>, the exemplary system <NUM> for installation or removal of one or more combustion cans <NUM> from a combustion section <NUM> of a turbomachine described above with reference to <FIG> may further include or work alongside a robotic system <NUM>. The robotic system <NUM> may be operable to install and/or remove one or more combustion cans <NUM> from a combustion section <NUM> of a gas turbine <NUM>. For example, the robotic system <NUM> may be operable to install and/or remove a combustion can into each combustor assembly <NUM> of the gas turbine <NUM>.

As shown in <FIG>, The robotic system <NUM> may include a support structure <NUM> and a robotic arm <NUM> coupled to the support structure <NUM>. For example, as shown in <FIG> the support structure <NUM> may include one or more beams <NUM> that support the weight of the robotic arm <NUM>. In exemplary embodiments, the robotic arm <NUM> may be translated along the one or more beams <NUM> (e.g., by applying a force to the robotic arm or automatically by a controller). Additionally or alternatively, as shown in <FIG>, the support structure <NUM> may include a circumferentially extending track <NUM>, and the robotic arm may be movably coupled to the circumferentially extending track <NUM> via a guide arm <NUM>. The guide arm <NUM> and the circumferentially extending track <NUM> may support the weight of the robotic arm <NUM>, and the robotic arm may be translated along the track <NUM> (e.g., by applying a force to the robotic arm or by operation of a controller). In this way, the support structure <NUM> may allow the robotic arm to be translated freely (e.g., in any direction) without requiring excessive force from the operator.

In many embodiments, the robotic arm <NUM> may include a gripper assembly <NUM> for grabbing, gripping, or removably coupling to a combustion can <NUM>. For example, the gripper assembly <NUM> may include motorized jaws <NUM> capable of opening and closing to securely grab a combustion can <NUM>. The gripper jaws may include combustion can jaws <NUM> that are contoured to correspond with the shape of the combustion can <NUM> (to facilitate the gripping thereof). Additionally, the robotic arm <NUM> may include a gripper motor <NUM> coupled to the gripper assembly <NUM> for opening and closing the motorized jaws <NUM>.

In exemplary embodiments of the robotic system <NUM>, in addition to the robotic arm <NUM> being free to translate in any direction (e.g., via the support structure <NUM> described hereinabove), the robotic arm may also be configured to rotate the gripper assembly <NUM> in any direction (thereby allowing for rotation of a combustion can <NUM>). For example, as shown in <FIG>, the robotic arm <NUM> may define an orthogonal coordinate system an X direction, a Y direction, and a Z direction mutually perpendicular to one another. For example, the robotic arm <NUM> may include a helical spur gearmotor <NUM> (such as a parallel shaft mounted helical spur gearmotor). The helical spur gearmotor <NUM> may be mounted to a steering assembly <NUM> and may provide for rotation about the X direction. Additionally, the robotic arm <NUM> may include a cylindrical joint <NUM> that provides for rotation about the Y direction. Furthermore, the robotic arm <NUM> may further include a motorized hinge <NUM> that provides for rotation about the Z direction. As shown, the robotic arm <NUM> may include a pneumatic cylinder <NUM> disposed between the gripper motor <NUM> and the motorized hinge <NUM>. The pneumatic cylinder <NUM> may provide for translation along the X direction.

The robotic system <NUM> may be user controlled (such as by operator <NUM>). For example, the robotic arm may include a steering assembly <NUM> having one or more handlebars <NUM>. The steering assembly <NUM> may be operated by a user to control a position of the robotic arm (e.g., along the support structure <NUM>). In some embodiments, the steering assembly <NUM> may a human-machine or user interface for displaying message windows and/or alerts to the operator and/or for allowing the operator to interface with the robotic system's <NUM> controller or computing system. In some embodiments, the user interface may include joysticks, buttons, knobs and/or any other suitable input devices that allow the operator to provide user inputs to an associated controller or computing system, including wifi (unwired) or wired remote control. Operator may have full control whether close or far away from robotic system <NUM> during full operator vision to mange or control combustion cans handling or operation.

In alternative embodiments, the robotic system <NUM> may be entirely controlled by a computerized operating system (e.g., a controller). In general, the computing system that may control the robotic system <NUM> may correspond to any suitable processor-based device(s), such as a computing device or any combination of computing devices. Thus, the computing system may generally include one or more processor(s) and associated memory devices configured to perform a variety of computer-implemented functions (e.g., performing the methods, steps, algorithms, calculations, and the like disclosed herein). As used herein, the term "processor" refers not only to integrated circuits referred to in the art as being included in a computer, but also refers to a controller, a microcontroller, a microcomputer, a programmable logic controller (PLC), an application specific integrated circuit, and other programmable circuits. Additionally, the memory device may generally include memory element(s) including, but not limited to, computer readable medium (e.g., random access memory (RAM)), computer readable non-volatile medium (e.g., a flash memory), a floppy disk, a compact disc-read only memory (CD-ROM), a magneto-optical disk (MOD), a digital versatile disc (DVD) and/or other suitable memory elements. Such memory device may generally be configured to store information accessible to the processor(s), including data that can be retrieved, manipulated, created and/or stored by the processor(s) and instructions that can be executed by the processor(s).

Referring now to <FIG>, a flow diagram of one embodiment of a method <NUM> installation of one or more combustion cans <NUM> from a combustion section <NUM> of a turbomachine (such as the gas turbine <NUM>) in accordance with aspects of the present subject matter. In general, the method <NUM> will be described herein with reference to the system <NUM> and the gas turbine <NUM> described above with reference to <FIG>. However, it will be appreciated by those of ordinary skill in the art that the disclosed method <NUM> may generally be utilized with any suitable turbomachine and/or may be utilized in connection with a system having any other suitable system configuration. In addition, although <FIG> depicts steps performed in a particular order for purposes of illustration and discussion, the methods discussed herein are not limited to any particular order or arrangement. One skilled in the art, using the disclosures provided herein, will appreciate that various steps of the methods disclosed herein can be omitted, rearranged, combined, and/or adapted in various ways without deviating from the scope of the present disclosure.

As shown, the method <NUM> may include an initial step <NUM> of positioning a lower rail portion <NUM> of an annular track partially about a combustion section <NUM> of a turbomachine (such as the gas turbine <NUM>). As discussed above, a second portion <NUM> (or second half) of a drive chain <NUM> may extends along the lower rail portion <NUM>. As shown, in <FIG>, the lower rail portion may be positioned about the lower half of the gas turbine <NUM> (e.g., below the horizontal plane <NUM> that divides the turbine <NUM> into an upper half and a lower half). For example, the lower rail may be lifted by a crane or other lifting means and rested on the one or more vertical legs <NUM> (such as in the position shown in <FIG>).

In exemplary embodiments, the method <NUM> may further include a step <NUM> of lifting an upper rail portion <NUM> of the annular track <NUM>. As discussed above in more detail, a first portion <NUM> of the drive chain <NUM> may extends along the upper rail portion <NUM>. A first plurality of carts <NUM> are movably coupled to the upper rail portion <NUM> and coupled to the first portion <NUM> of the drive chain <NUM>. Each cart <NUM> of the first plurality of carts <NUM> may be coupled to a combustion can cradle assembly <NUM> in a first plurality of combustion can cradle assemblies <NUM>. Each combustion can cradle assembly <NUM> in the first plurality of combustion can cradle assemblies <NUM> being removably coupled to a combustion can <NUM> in a first plurality <NUM> of combustion cans <NUM>.

The method may include a step <NUM> of coupling the upper rail portion <NUM> to the lower rail portion <NUM>. Coupling the upper rail portion <NUM> to the lower rail portion <NUM> may form the annular track <NUM> that entirely surrounds the combustion section <NUM> of the gas turbine. Additionally, the method may include a step <NUM> of coupling the first portion <NUM> of the drive chain <NUM> to the second portion <NUM> of the drive chain <NUM>. This will provide a single continuous drive chain <NUM> that extends entirely circumferentially around the combustion section <NUM> of the gas turbine <NUM>.

In various embodiments, the method may include a step <NUM> of operating a drive assembly <NUM> to move the first plurality of carts <NUM> from the upper rail portion <NUM> of the annular track <NUM> to the lower rail portion <NUM> of the annular track <NUM>. For example, the drive assembly <NUM> may include a motor <NUM> operably connected to the drive chain <NUM> via one or more sprockets <NUM>, such that operation of the motor <NUM> moves the drive chain <NUM> along the annular track <NUM>. In exemplary embodiments, the method may include a step <NUM> of installing the first plurality <NUM> of combustion cans <NUM> into a lower half of the combustion section <NUM> of the turbomachine. For example, each combustion can <NUM> may be installed into a respective combustor assembly <NUM> disposed in the lower half of the combustion section <NUM> (e.g., below the horizontal plane <NUM>).

Once the first plurality <NUM> of combustion cans <NUM> have been installed in the lower half of the combustion section <NUM>, the method <NUM> may further include decoupling the first portion <NUM> of the drive chain <NUM> to the second portion <NUM> of the drive chain <NUM> (e.g., when the portions <NUM>, <NUM> are positioned along one of the upper rail portion <NUM> or the lower rail portion <NUM>). Additionally, the method <NUM> may include decoupling the upper rail portion <NUM> from the lower rail portion <NUM>. Subsequently, the upper rail portion <NUM> may be lifted and lowered (e.g., via a crane or other suitable lifting means) to the ground or floor, where a second plurality <NUM> of combustion cans <NUM> may be coupled to the upper rail portion <NUM>.

In exemplary embodiments, the method <NUM> may further include lifting the upper rail portion <NUM> of the annular track <NUM> (e.g., for a second time to complete the installation of combustion cans <NUM> into the combustion section <NUM>). During the second lift, second plurality of carts <NUM> may be movably coupled to the upper rail portion <NUM> and coupled to the first portion <NUM> of the drive chain <NUM>. Each cart <NUM> of the second plurality of carts <NUM> may be coupled to a combustion can cradle assembly <NUM> in a second plurality of combustion can cradle assemblies <NUM>. Each combustion can cradle assembly <NUM> in the second plurality of combustion can cradle assemblies <NUM> may be coupled to a second combustion can <NUM> of a second plurality <NUM> combustion cans <NUM>. In many embodiments, the method <NUM> may further include coupling the upper rail portion <NUM> to the lower rail portion <NUM>. Coupling the upper rail portion <NUM> to the lower rail portion <NUM> may form the annular track <NUM> that entirely surrounds the combustion section <NUM> of the gas turbine. In many embodiments, the method <NUM> may include installing the second plurality <NUM> of combustion cans <NUM> into an upper half (e.g., above the horizontal plane <NUM>) of the combustion section <NUM> of the turbomachine. For example, each combustion can <NUM> in the second plurality of combustion cans <NUM> may be installed into a respective combustor assembly <NUM> disposed in the upper half of the combustion section <NUM> (e.g., above the horizontal plane <NUM>).

As provided hereinabove, the method <NUM> and system <NUM> described herein provide a compact, safe, and efficient design for installation and removal of one or more combustion cans <NUM> from the combustion section <NUM> of a gas turbine. For example, although <FIG> illustrate a sequential process of utilizing the system <NUM> for installing all the combustion cans <NUM> into the combustion section <NUM>, it should be appreciated that the system <NUM> described herein may be utilized for installation or removal of any number of combustion cans <NUM> in any position on the gas turbine <NUM>.

Referring now to <FIG>, each of which illustrate an upper rail portion <NUM> of the annular track <NUM> carrying one or more combustion cans <NUM>. As shown, one or more combustion cans <NUM> may arranged within the upper rail portion <NUM> to uniformly distribute the weight and keep the upper rail portion <NUM> upright when in use. For example, each of the circles illustrated in <FIG> may represent a combustion can <NUM> removably coupled to a respective combustion can cradle assembly <NUM>. As shown, the upper rail portion <NUM> may define a vertical lifting axis <NUM> along which an upward lifting force may be applied to move the upper rail portion <NUM> and the plurality of combustion cans <NUM>. In such embodiments, the one or more combustion cans <NUM> may be arranged equally on either side of the vertical lifting axis <NUM>, in order to keep the upper rail portion <NUM> of the annular track <NUM> in an upright position when it is being moved. Additionally or alternatively, when lifting and/or moving the upper rail portion <NUM> of the annular track <NUM> along the vertical lifting axis <NUM>, one or more counterweights may be utilized to equalize the distribution of weight within the upper rail portion <NUM> (e.g., instead of or in addition to the one or more combustion cans <NUM>).

Claim 1:
A system (<NUM>) for installation or removal of one or more combustion cans (<NUM>) from a combustion section (<NUM>) of a turbomachine, the system (<NUM>) comprising:
an annular track (<NUM>) surrounding the turbomachine, the annular track (<NUM>) including an upper rail portion and a lower rail portion removably coupled to one another;
a drive assembly (<NUM>) operably coupled to the annular track (<NUM>), the drive assembly (<NUM>) including a drive chain extending along the annular track (<NUM>);
a plurality of carts (<NUM>) rotatably coupled to the annular track (<NUM>) and connected to the drive chain such that operation of the drive assembly (<NUM>) alters a circumferential position of the plurality of carts (<NUM>) with respect to an axial centerline of the turbomachine; and
a plurality of combustion can cradle assemblies (<NUM>) each coupled to a respective cart (<NUM>) of the plurality of carts (<NUM>), and wherein each combustion can cradle assembly (<NUM>) of the plurality of combustion can cradle assemblies (<NUM>) is configured to removably couple to a combustion can (<NUM>) of the one or more combustion cans (<NUM>).