Patent Description:
Rotors for turbines of turbomachines are often machined from large forgings. Rotor wheels cut from the forgings are typically slotted to accept the bases of turbine blades for mounting. As the demand for greater turbine output and more efficient turbine performance continues to increase, larger and more articulated turbine blades are being installed in turbomachines. Dynamic properties that affect the design of these latter stage turbine blades include the contour and exterior surface profile of the various blades used in a turbomachine, which may affect the fluid velocity profile and/or other characteristics of operative fluids in a system. In addition to the contour of the blades, other properties such as the active length of the blades, the pitch diameter of the blades and the high operating speed of the blades in both supersonic and subsonic flow regions can significantly affect performance of a system. Damping and blade fatigue are other properties that have a role in the mechanical design of the blades and their profiles. These mechanical and dynamic response properties of the blades, as well as others, all influence the relationship between performance and surface profile of the turbine blades. Consequently, the profile of the latter stage turbine blades often includes a complex blade geometry for improving performance while minimizing losses over a wide range of operating conditions.

The application of complex blade geometries to turbine blades, particularly latter stage turbine blades, presents certain challenges in assembling and disassembling these blades on a rotor wheel. For example, adjacent turbine blades on a rotor wheel are typically connected together by cover bands or interlocking tip shrouds positioned around the outer periphery of the blades to confine a working fluid within a well-defined path and to increase the rigidity of the blades. These interlocking shrouds may impede the direct assembly and disassembly of blades positioned on the rotor wheel. In addition, inner platforms of these blades and their dovetail slots are often angled in relation to the axis of the turbine rotor wheel that they are mounted in, which also can impede their assembly on the rotor wheel. In many cases, the turbine blades must be removed one at a time. The working environment in which the turbine blades operate can cause, for example, corrosion, thermal distortion, etc., that can require significant force to disassemble the blades.

One approach to removal or installation of the turbine blades requires forcing the blades axially by application of force against another part of the turbine, e.g., an adjacent rotor wheel. Application of force to an adjacent structure can potentially cause damage to that structure. Another approach mounts a removal or installation apparatus to a part of the half-joint casing of the turbine in a cantilevered fashion, i.e., at three o'clock or nine o' clock relative to the axis of the turbine. This latter approach requires rotating the turbine to position each turbine blade at the three o'clock or nine o'clock position, such that the turbine blade extends generally horizontally from the rotor wheel in a cantilevered manner. Consequently, the weight of the turbine blade works against its removal or installation by applying a torque to the dovetail connection at the base of the turbine blade, requiring more axial force to remove the turbine blade. In addition, it is very challenging to support the turbine blade during removal and/or installation so that it does not fall or rotate in a manner that potentially damages the turbine blade, the rotor wheel, the half-joint casing or other parts of the turbine. Where the turbine blade is mounted in an angled dovetail slot, i.e., relative to the axis of the turbine, the rotor must be turned as the turbine blade is inserted or pulled out of position, which is extremely challenging where the blade is generally horizontal.

<CIT> and <CIT> each disclose an apparatus and a method for installing or removing a turbine blade in/from a turbine of a turbomachine having the features of the preambles of independent claims <NUM> and <NUM>.

An aspect of the present invention provides an apparatus for installing or removing a turbine blade in/from a turbine of a turbomachine, the apparatus comprising: an operative head configured to engage an axial sidewall of a turbine blade base; an actuator configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade; and a support gantry configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. The actuator includes: a mount member configured to couple to the support gantry; a slide system configured to slidably move the operative head relative to the mount member; and a linear actuator configured to selectively move the slide system axially relative to the mount member to apply the axial force. The operative head includes an arm operatively coupled to the actuator. The actuator further includes a coupler configured to selectively position the mount member between: a first state in which the mount member is axially and pivotally fixed to an axially-extending support member of the support gantry and the arm extends substantially vertically adjacent a first stage of a plurality of turbine blade stages, and a second state in which the mount member is pivotable relative to the axially-extending support member to position the arm radially outside of any turbine blade on the turbine, and axially movable along the axially-extending support member of the support gantry, wherein, in the second state, the actuator is movable along the axially-extending support member for positioning relative to a different second stage of the plurality of turbine blades.

Another aspect of the present invention relates to a method for installation or removal of a turbine blade from a turbine of a turbomachine, the method comprising: mounting an apparatus to a portion of a turbomachine, the apparatus including an operative head configured to engage an axial sidewall of a turbine blade base, an actuator configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base, and a support gantry configured to position the actuator substantially vertically above the turbine blade, wherein the operative head includes an arm extending from the actuator; and mechanically actuating the turbine blade base relative to the turbomachine by applying the axial force against the turbine blade base through the operative head, such that the turbine blade base transfers into or out of a rotor wheel of a first stage of turbine blades. The method is characterized by comprising: first rotating the actuator so as to rotate the arm from a first operative position adjacent the rotor wheel of the first stage of turbine blades to a position radially outside of any turbine blades on the turbine; axially moving the actuator along an axially-extending support member of the support gantry to an inoperative position in which the arm is radially outside of and axially over a space adjacent a different, second stage of turbine blades of the turbomachine; second rotating the actuator so as to rotate the arm from the inoperative position to a second operative position adjacent the different, second stage of turbine blades; and repeating the mechanical actuating the turbine blade base relative to the turbomachine by applying the axial force against the turbine blade base through the operative head, such that a turbine blade base transfers into or out of a rotor wheel of the different, second stage of turbine blades.

The drawings are intended to depict only typical aspects of the disclosure and therefore should not be considered as limiting the scope of the disclosure.

As an initial matter, in order to clearly describe the subject matter of the current disclosure, it will become necessary to select certain terminology when referring to and describing relevant machine components within a turbomachine. To the extent possible, common industry terminology will be used and employed in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of the present application and the scope of the appended claims. Those of ordinary skill in the art will appreciate that often a particular component may be referred to using several different or overlapping terms. What may be described herein as being a single part may include and be referenced in another context as consisting of multiple components. Alternatively, what may be described herein as including multiple components may be referred to elsewhere as a single part.

In addition, several descriptive terms may be used regularly herein, and it should prove helpful to define these terms at the onset of this section. These terms and their definitions, unless stated otherwise, are as follows. As used herein, "downstream" and "upstream" are terms that indicate a direction relative to the flow of a fluid, such as the working fluid through the turbine or, for example, the flow of air through the combustor or coolant through one of the turbine's components. The term "downstream" corresponds to the direction of flow of the fluid, and the term "upstream" refers to the direction opposite to the flow (i.e., the direction from which the flow originates). The terms "forward" and "aft," without any further specificity, refer to directions, with "forward" referring to the front or compressor end of the engine, and "aft" referring to the rearward section of the turbomachine.

It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. "Optional" or "optionally" means that the subsequently described event or circumstance may or may not occur or that the subsequently describe component or element may or may not be present, and that the description includes instances where the event occurs or the component is present and instances where it does not or is not present.

Where an element or layer is referred to as being "on," "engaged to," "connected to" or "coupled to" another element or layer, it may be directly on, engaged to, connected to, or coupled to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being "directly on," "directly engaged to," "directly connected to" or "directly coupled to" another element or layer, there may be no intervening elements or layers present.

As denoted in these Figures, the "A" axis represents axial orientation (along the axis of a rotor of a turbomachine). As used herein, the terms "axial" and/or "axially" refer to the relative position/direction of objects along axis A, which is substantially parallel (i.e., within +/-<NUM>°) with the axis of rotation of the turbomachine (in particular, the rotor section thereof). As further used herein, the terms "radial" and/or "radially" refer to the relative position/direction of objects along axis (R), which is substantially perpendicular with axis A and intersects axis A at only one location. It is often required to describe parts that are disposed at differing radial positions with regard to a center axis. For example, if a first component resides closer to the axis than a second component, it will be stated herein that the first component is "radially inward" or "inboard" of the second component. If, on the other hand, the first component resides further from the axis than the second component, it may be stated herein that the first component is "radially outward" or "outboard" of the second component. Additionally, the terms "circumferential" and/or "circumferentially" refer to the relative position/direction of objects along a circumference (C) which surrounds axis A but does not intersect the axis A at any location. In figures that depict a two-dimensional view, circumference C may be omitted for clarity.

The term "transfer" or "axial transfer" refers to the process of moving (e.g., by sliding motion) a component such as a blade from one position to another, such as to or from a dovetail slot of a rotor wheel. Thus, embodiments of the present disclosure discussed herein can allow turbine blades to be installed within or removed from a rotor wheel of a turbine by transferring one or more turbine blades. Although removal of turbine blades is shown more specifically in the drawings, it is understood that the various embodiments described herein may be operable to install and/or remove turbine blades at a rotor wheel without modifying the various components and/or process methodologies discussed. Embodiments of the present disclosure also provide methods of installing turbine blades by using various apparatuses discussed herein and/or similar assemblies.

Embodiments of the disclosure provide an apparatus for removing or installing a turbine blade from a turbine of a turbomachine, and a related method. The apparatus includes an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade. A support gantry is configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. Among other advantages, the support gantry allows a wide range of adjustment of the apparatus for, for example, different angles, different turbines with different mounting locations. The apparatus also allows operation on more than one stage of any given turbine without unbolting the apparatus, saving time. In addition, due to the vertical positioning of the apparatus, the apparatus requires less axial force to transfer the turbine blade and allows for a safer install or removal of the blade by supporting it from above. The apparatus can be operated almost entirely remotely, adding more safety.

Referring to the drawings, <FIG> is a schematic view of an illustrative turbomachine <NUM> in the form of a combustion turbine or gas turbine (GT) system <NUM> (hereinafter, "GT system <NUM>"). GT system <NUM> includes a compressor <NUM> and a combustor <NUM>. Combustor <NUM> includes a combustion region <NUM> and a fuel nozzle assembly <NUM>. GT system <NUM> also includes a turbine <NUM> and a common compressor/turbine shaft <NUM> (hereinafter referred to as "rotor <NUM>"). In one non-limiting example, GT system <NUM> is a 9HA. <NUM> engine, commercially available from General Electric Company, Greenville, S. The present disclosure is not limited to any one particular GT system and may be implanted in connection with other engines including, for example, the other HA, F, B, LM, GT, TM and E-class engine models of General Electric Company and engine models of other companies. Further, the teachings of the disclosure are not necessarily applicable to only a GT system and may be applied to other types of turbomachines, e.g., steam turbines, jet engines, compressors, etc..

<FIG> shows a cross-section view of an illustrative portion of turbine <NUM> with four stages L0-L3 that may be used with GT system <NUM> in <FIG>. The four stages are referred to as L0, L1, L2, and L3. Stage L0 is the first stage and is the smallest (in a radial direction) of the four stages. Stage L1 is the second stage and is the next stage in an axial direction. Stage L2 is the third stage and is the next stage in an axial direction. Stage L3 is the fourth, last stage and is the largest (in a radial direction). It is to be understood that four stages are shown as one example only, and each turbine may have more or less than four stages.

A set of stationary vanes or nozzles <NUM> cooperate with a set of rotating blades <NUM> to form each stage L0-L3 of turbine <NUM> and to define a portion of a flow path through turbine <NUM>. Rotating blades <NUM> in each set are coupled to a respective rotor wheel <NUM> that couples them circumferentially to rotor <NUM>. That is, a plurality of rotating blades <NUM> are mechanically coupled in a circumferentially spaced manner to each rotor wheel <NUM>. A static nozzle section <NUM> includes a plurality of stationary nozzles <NUM> circumferentially spaced around rotor <NUM>. Each nozzle <NUM> may include at least one endwall (or platform) <NUM>, <NUM> connected with an airfoil <NUM>. In the example shown, nozzle <NUM> includes a radially outer endwall <NUM> and a radially inner endwall <NUM>. Radially outer endwall <NUM> couples nozzle(s) <NUM> to a casing <NUM> of turbine <NUM>.

In operation, air flows through compressor <NUM>, and compressed air is supplied to combustor <NUM>. Specifically, the compressed air is supplied to fuel nozzle assembly <NUM> that is integral to combustor <NUM>. Fuel nozzle assembly <NUM> is in flow communication with combustion region <NUM>. Fuel nozzle assembly <NUM> is also in flow communication with a fuel source (not shown in <FIG>) and channels fuel and air to combustion region <NUM>. Combustor <NUM> ignites and combusts fuel. Combustor <NUM> is in flow communication with turbine <NUM> within which gas stream thermal energy is converted to mechanical rotational energy. Turbine <NUM> is rotatably coupled to and drives rotor <NUM>. Compressor <NUM> also is rotatably coupled to rotor <NUM>. In the illustrative embodiment, there is a plurality of combustors <NUM> and fuel nozzle assemblies <NUM>. In the following discussion, unless otherwise indicated, only one of each component will be discussed. At least one end of rotor <NUM> may extend axially away from turbine <NUM> and may be attached to a load or machinery (not shown), such as, but not limited to, a generator, a load compressor, and/or another turbine.

Turning to <FIG>, a plurality of blades <NUM> in a selected stage of blades are shown arranged in a row and mounted circumferentially adjacent to each other on rotor wheel <NUM>. Blades <NUM> may be designed for continued circumferential engagement with each other during operation and when subjected to relatively high loads. An example form of mechanical engagement between circumferentially adjacent blades <NUM> is shown in <FIG>, and embodiments of the present disclosure may be effective for installing and removing blades <NUM> designed for this arrangement or similar arrangements. Each blade <NUM> can be mechanically coupled to and mounted on rotor wheel <NUM> through a turbine blade base <NUM> including, e.g., a dovetail shape designed to fit within and engage a complementary slot within rotor wheel <NUM>. As shown in <FIG>, blades <NUM> can extend from turbine blade base <NUM> with varying profiles and/or contours for accommodating a flow of fluid <NUM> (<FIG>) or other fluids across each blade <NUM>. A radial end of blade <NUM> can include a shroud portion <NUM> in the form of a mutually engaging, substantially identical block or plate formed and/or mounted on the tip of each blade <NUM>. Once each blade <NUM> is installed on rotor wheel <NUM>, the engaging blocks or plates of each shroud portion <NUM> can form a substantially continuous tip shroud element, e.g., a substantially continuous, annular body configured to direct a flow around rotor <NUM> (<FIG>).

Referring to <FIG> and <FIG> together, shroud portion <NUM> of each blade <NUM> can include, e.g., an interlocking profile <NUM> (<FIG> only) for circumferential engagement with shroud portions <NUM> of adjacent blades <NUM>. In some examples, interlocking profile <NUM> may include a Z-shape, a V-shape, a zig-zag path with multiple transition points, a curvilinear surface, a complex geometry including straight-faced and curved surfaces, etc. However embodied, interlocking profile <NUM> can inhibit axial sliding of each blade <NUM> relative to rotor wheel <NUM> after each blade <NUM> has been installed. In addition, blades <NUM> may be positioned directly between turbine <NUM> of turbomachine <NUM> and an adjacent flow path <NUM> (<FIG>), e.g., an exhaust hood or diffusor section of turbomachine <NUM> (<FIG>). As shown in <FIG>, each blade <NUM> may be designed for installation or removal substantially along the direction of axial path N. Interlocking profile <NUM> can be advantageous during operation of turbomachine <NUM>, e.g., by maintaining the relative position of each blade <NUM> relative to each other and to rotor wheel <NUM>. However, interlocking profile <NUM> may reduce the ability for one or more blades <NUM> to be installed or removed from a location directly between two other blades <NUM> during manufacture or servicing.

Embodiments of the present disclosure can mitigate these properties of interlocking profile <NUM>, e.g., by imparting an axially-oriented force to install or remove blades <NUM>. In some embodiments, the installed or removed blade <NUM> can further be subjected to mechanical vibrations. Such vibrations, e.g., can impart oscillating motion to blade <NUM> and allow axial movement of blade <NUM> despite various impeding factors, e.g., corrosion, that may impede movement. Various embodiments for imparting axial force, and/or mechanical vibration against blade(s) <NUM> are discussed herein. As will be described, embodiments of the present disclosure can include an apparatus mounted on fixed structure <NUM>, such as an exhaust hood <NUM> (<FIG>) (e.g., a panel or strut thereof) of turbomachine <NUM>, a casing <NUM> of turbomachine <NUM> such as an outer shell, half-joint casing <NUM> (<FIG>), and/or other turbomachine components capable of having various structural features mounted thereon. In contrast to current approaches, the apparatus is vertically, radially above the turbine blades.

Referring to <FIG> and <FIG> together, an apparatus <NUM> for installing and/or removing turbine blades <NUM> at turbine blade base <NUM> is shown according to embodiments of the present disclosure. Turbine blade base <NUM> may include a root of turbine blade <NUM> or may include any portion of turbine blade <NUM> configured to couple to rotor wheel <NUM>. <FIG> shows a perspective view of apparatus <NUM>, <FIG> shows an enlarged partial perspective view of apparatus <NUM> to better illustrate various components thereof, and <FIG> shows an enlarged perspective view of an actuator <NUM> of the apparatus.

For purposes of description, blade(s) <NUM> illustrated in the following drawings may include last-stage (e.g., L3 (<FIG>)) blades in turbomachine <NUM>, which may include the same or similar features shown in <FIG> and described elsewhere herein. Last-stage blades <NUM> may differ from other blades <NUM> in turbomachine <NUM>, e.g., by being positioned where conventional vibrating assemblies and/or actuating devices for installing and removing blades <NUM> cannot be used, or are impractical. However, as will be described, apparatus <NUM> is advantageously adjustable to remove or install blade(s) <NUM> from a number of stages within turbomachine <NUM> without being moved. In addition, apparatus <NUM> can be located to operate on any stage of blades in practically any turbine <NUM>. Embodiments of apparatus <NUM> and other method or apparatus embodiments described herein, can be used to install or remove blade(s) <NUM> while being mechanically coupled to one or more portions of turbomachine <NUM>.

Apparatus <NUM> generally includes an operative head <NUM> movable by an actuator <NUM> supported by a support gantry <NUM>.

Referring to <FIG>, apparatus <NUM> includes operative head <NUM> configured to engage an axial sidewall <NUM> (<FIG>, <FIG> and <FIG>) of turbine blade base <NUM>. Operative head <NUM> is shaped to impart an axial force F against turbine blade base <NUM>. Operative head <NUM> can be shaped and/or positioned to engage axial sidewall <NUM> of turbine blade base <NUM> while applying mechanical force thereto in an axial direction, i.e., generally parallel to the axis of the turbomachine. Axial sidewall <NUM> may face upstream or downstream depending on where room is available to install or remove a respective blade <NUM> from rotor wheel <NUM>. Operative head <NUM> includes an arm <NUM>, which may extend vertically when operatively coupled to an actuator <NUM>, i.e., the arm is a vertically extending arm. Arm <NUM> may have any length necessary to properly position operative head <NUM>, i.e., end of arm <NUM>, to engage axial sidewall <NUM> of turbine blade base <NUM>. While one length of arm <NUM> is illustrated, arm <NUM> may be selected from a set of different length arms, which may be provided as part of apparatus <NUM> so it can be used with any radial length of turbine blade <NUM>, and/or a variety of different stages of a given turbine <NUM>. Alternatively, as shown in <FIG>, vertically extending arm <NUM> may be length adjustable. It can be made length adjustable using any solution, for example, by changing its vertical position relative to actuator <NUM> using a coupling member <NUM> and/or plate couplers <NUM> (e.g., bolts, screws, etc.) joining the arm to coupling members <NUM> - see adjustment slot <NUM>. While a slot <NUM> is shown, any form of selectable opening(s) can also be used. Operative head <NUM> may include any structure to engage axial sidewall <NUM>, e.g., at end of arm <NUM> adjacent axial sidewall <NUM>. That is, operative head <NUM> can be provided in the form of any now known or later-developed instrument for imparting axial force, and perhaps vibrational oscillation, against components mechanically engaged thereto. Operative head <NUM> can be embodied as, e.g., one or more vibrating hammers, plates, cylinders, rollers, etc. In one embodiment, operative head <NUM> may include an engagement element <NUM> (<FIG>) configured to engage axial sidewall <NUM> of turbine blade base <NUM>, and slide along axial sidewall <NUM> of turbine blade base <NUM> while the rotor rotates.

Operative head <NUM> may also include a vibrating assembly <NUM> including a vibratory drive mechanism <NUM> coupled to arm <NUM>. In some implementations, vibratory drive mechanism <NUM> can include a pneumatic motor configured to generate mechanical vibrations and/or other forms of movement using, for example, compressed air fed to vibrating assembly <NUM>, e.g., through a fluid source. Vibratory drive mechanism <NUM> can alternatively include, or be embodied as, an electric motor, combustion engine, and/or other currently-known or later developed instruments for producing mechanical work, coupled with, e.g., an eccentric weight vibrator system. Vibrating assembly <NUM> can be adjustably coupled to and/or positioned directly on arm <NUM> using any now known solution, e.g., fasteners, welding, etc. Vibrating assembly <NUM> may be adjustably mounted to arm <NUM> to allow positioning anywhere along a length of arm <NUM>.

Apparatus <NUM> also includes support gantry <NUM> configured to position actuator <NUM> substantially vertically above turbine blade <NUM>, while turbine blade <NUM> is in position in turbine <NUM> of turbomachine <NUM>. As used herein, "substantially vertical" indicates +/- <NUM>° from vertical. Support gantry <NUM> can include any now known or later developed bridge-like overhead structure with a platform supporting actuator <NUM>, and having sufficient strength to withstand the motive forces applied thereto. Support gantry <NUM> may mount to any fixed structure <NUM>. In certain embodiments, support gantry <NUM> may mount to a portion of turbomachine <NUM> in which turbine blade <NUM> is positioned. As illustrated in <FIG>, an outer shell, upper half-joint casing (not shown) can be removed, leaving an outer shell, lower half-joint casing <NUM>. Here, turbine <NUM> including turbine blade <NUM> is in position for operation of turbine <NUM>, excepting for the remove of any outer shell, upper half-joint casing. The portion of turbomachine <NUM> to which support gantry <NUM> mounts may include fixed structure <NUM> that is, for example, adjacent to turbine <NUM>, and/or in which turbine <NUM> is positioned, e.g., lower half-joint casing <NUM>. In the example shown, support gantry <NUM> mounts to opposing sides <NUM>, <NUM> of lower half-joint casing <NUM> in which turbine <NUM> is positioned, and an exhaust hood <NUM> adjacent to turbine <NUM>. While support gantry <NUM> has been shown mounted in a particular manner in the drawings, it is emphasized that it can be mounted to any variety of alternative fixed structures <NUM>, e.g., power plant floor, other casings, other structure adjacent turbine <NUM>, cranes within a power plant, among many other options. Any mounting mechanism <NUM> capable of fixedly attaching support gantry <NUM> to fixed structure <NUM> may be used, e.g., bolted or clamped mounting plates, etc..

As illustrated, in certain embodiments, support gantry <NUM> may include a plurality of adjustable support members <NUM> configured to accommodate a plurality of different turbines <NUM>, i.e., different sized turbines having blade stages at different distances and with different outer radii than illustrated. In the non-limiting example shown, support members <NUM> may include scaffolding members similar to those used in construction applications. Any number of support members <NUM> may be used, and may be coupled together in any now known or later developed fashion, e.g., clamps, fasteners, threaded couplings, etc. In any event, support members <NUM> are capable of positioning actuator <NUM> at any lateral position above turbine <NUM>, and any axial position along axis A of turbine <NUM>. For purposes described herein, in certain embodiments, at least one support member <NUM> extends axially, i.e., parallel to axis A of turbine <NUM>.

To effectuate movement of operative head <NUM>, apparatus <NUM> can include actuator <NUM> mechanically coupled to operative head <NUM>, i.e., arm <NUM>, such that actuation of actuator <NUM> causes operative head <NUM> and arm <NUM> to move relative to turbine blade base <NUM>. More particularly, actuator <NUM> is configured to move the operative head <NUM> to selectively engage axial sidewall <NUM> of turbine blade base <NUM> and impart an axial force F against turbine blade base <NUM> to remove or install turbine blade <NUM>. As shown best in <FIG> and <FIG>, actuator <NUM> can include a mount member <NUM> configured to couple to support gantry <NUM>. Mount member <NUM> may include any structural member capable of coupling to an axially-extending support member <NUM> of support gantry <NUM>. In certain embodiments, mount member <NUM> takes the form of a plate; however, other forms are also possible. Mount member <NUM> can include any number of couplers <NUM> in the form of, e.g., pipe clamps, or other forms of couplers appropriate for the shape and dimensions of axially-extending support member <NUM>. Couplers <NUM> may extend outward from mount member <NUM> to engage one or more portions of axially-extending support member <NUM>. Couplers <NUM> can be selectively fastened and unfastened to remove actuator <NUM> from support gantry <NUM>, or allow movement of actuator <NUM> relative to support gantry <NUM>. More particularly, couplers <NUM> can be selectively fastened and unfastened to allow actuator <NUM> to be moved axially relative to turbine blade <NUM> thereunder, e.g., along axially-extending support member <NUM>, to allow desired axially positioning of operative head <NUM>. In this manner, apparatus <NUM> can be used to remove or install turbine blades <NUM> on numerous stages of turbine <NUM> without having to move support gantry <NUM> or other parts of apparatus <NUM>. Axially-extending support member <NUM> can have any length required to allow movement to as many stages of turbine <NUM> as desired with a single mounting of apparatus <NUM>.

Actuator <NUM> also includes a slide system <NUM> configured to slidably move operative head <NUM> relative to mount member <NUM> (axially), and hence, turbine blade <NUM>. Actuator <NUM> also includes a linear actuator <NUM> configured to selectively move slide system <NUM> axially relative to mount member <NUM> to apply the axial force F to axial sidewall <NUM> of turbine blade base <NUM>. Slide system <NUM> may include one or more axial guides <NUM> to enable movement of operative head <NUM> with arm <NUM> relative to mount member <NUM> in at least one direction, e.g., along line T. Axial guides <NUM> may be embodied as slidable couplings such as rails, raceways, slots, etc., and/or may include alternative forms of structure permitting movement in one direction such as gear bearings, rack-and-pinion assemblies, threaded housings, and/or other mechanical bearings. Where axial guides <NUM> are embodied as a rail or other slidable bearing, a pair of slidable couplings <NUM> may each be slidably connected to and/or mounted on respective axial guides <NUM>. Slidable couplings <NUM> may take the form of trolleys, wheels, gears, and/or other sliding components or bearings designed to enable movement of one component relative to another, e.g., along the direction of arrow T. In alternative scenarios where axial guides <NUM> are in the form of a gear bearing or alternative component for providing a slidable coupling between two mechanically engaged elements, slidable couplings <NUM> may be substituted for, e.g., wheels, gears, threaded members, etc., for providing movement substantially in the direction of axial axis A. A coupling member <NUM> may be provided as a unitary housing shaped to engage an outer surface profile of arm <NUM>, or alternatively may be coupled to one surface of arm <NUM>. In this case, another coupling member <NUM> can be coupled to another surface of arm <NUM>, with plate couplers <NUM> (e.g., bolts, screws, rivets, etc.) joining the two coupling members <NUM> together. As will be recognized, a variety of alternative mechanisms to couple arm <NUM> to slide system <NUM> may also be employed.

An operator may further control the position of operative head <NUM> and arm <NUM> relative to mount member <NUM> with additional components included within and/or operably connected to actuator <NUM>. For example, linear actuator <NUM> may include any form of drive mechanism <NUM> in the form of, e.g., a mechanical motor, electrical motor, pneumatic motor, etc., that can produce and transmit mechanical work to move operative head <NUM> and arm <NUM> across axial guide(s) <NUM>. In the non-limiting example illustrated, linear actuator <NUM> includes a worm gear <NUM> that interacts with coupling member <NUM> to move operative head <NUM> and arm <NUM>. Linear actuator <NUM> can be coupled to mount member <NUM>, e.g., through a bearing <NUM> shaped to receive a portion of linear actuator <NUM> therein. Bearing <NUM> can be positioned at opposing ends of mount member <NUM> to allow for a worm gear <NUM> to rotate freely in order to move a slide system <NUM>. Slide system <NUM>, worm gear <NUM> and/or drive mechanism <NUM> may be coupled using any necessary adapters (not shown). Each bearing <NUM> can be mounted on a portion of mount member <NUM>, e.g., by being mechanically affixed thereto through conventional fasteners such as bolts, screws, rivets, etc..

In addition to positioning actuator <NUM> axially on axially-extending support member <NUM>, as described herein, coupler <NUM> is also configured to selectively position mount member <NUM> of actuator <NUM> between two states. A first, operative state, as shown in <FIG> and <FIG>, is one in which mount member <NUM> is axially and pivotally fixed to axially-extending support member <NUM> of support gantry <NUM>. Here, arm <NUM> extends substantially vertically adjacent a first stage <NUM> of a plurality of turbine blade stages (see plurality of emptied rotor wheels <NUM>). This state is an operative state of apparatus <NUM> in which actuator <NUM> can be actuated to remove or install turbine blades <NUM> in the selected rotor wheel <NUM> for the selected blade stage. <FIG> shows another, second adjustment state in which couplers <NUM> have been released sufficiently to allow mount member <NUM> to be pivotable relative to axially-extending support member <NUM> (see arrow B) to position arm <NUM> radially outside of any turbine blade <NUM> on turbine <NUM>, and axially movable along axially-extending support member <NUM> of support gantry <NUM>. In the second state, actuator <NUM> is movable along axially-extending support member <NUM> for positioning relative to a different second stage <NUM> of plurality of turbine blades <NUM> (see arrow C). Once in a new, desired position, actuator <NUM> can be rotated back so that operative head <NUM> is in a location to apply axial force F to axial sidewall <NUM> of a selected turbine blade base <NUM> (see arrow D). In this manner, despite support gantry <NUM> not moving, apparatus <NUM> can operate on more than one stage, making removal or installing of turbine blades in a number of stages significantly faster and safer.

In operation, a method for installation or removal of a turbine blade <NUM> from a turbine <NUM> of turbomachine <NUM> includes mounting apparatus <NUM>, as described herein, to a portion of turbomachine <NUM>. In one non-limiting example, mounting includes mounting support gantry <NUM> to opposing sides <NUM>, <NUM> of half-joint casing <NUM> in which turbine <NUM> is positioned, and to exhaust hood <NUM> adjacent to turbine <NUM> in turbomachine <NUM>. Operative head <NUM> may be substantially axially aligned with turbine blade base <NUM> of a selected blade <NUM>. Using actuator <NUM>, operative head <NUM> is moved to engage operative head <NUM> of apparatus <NUM> with turbine blade base <NUM> (before actuating turbine blade base). As shown in <FIG>, the method further includes mechanically actuating turbine blade base <NUM> relative to turbomachine <NUM> by applying axial force F against turbine blade base <NUM> through operative head <NUM> causing turbine blade base <NUM> to transfers into or out of rotor wheel <NUM> of a first stage of turbine blades <NUM>. That is, operative head <NUM> under actuation by actuator <NUM> through arm <NUM> forces turbine blade <NUM> into or out of rotor wheel <NUM>. In terms of installation, these actions can move blade <NUM> axially toward rotor wheel <NUM> such that blade <NUM> is installed between two other blades <NUM>. In the case of removal, operative head <NUM> can contact and axially move blade <NUM> out of position between two adjacent blades <NUM>, and out of rotor wheel <NUM>. Both the removal and the installation process can be employed where the blades need to be "fanned out", meaning one has to remove the blades one by one, a bit at a time while also turning the rotor. Fanning out is necessary, for example, where a skewed dovetail or interlocking tip shrouds will not allow removal or installation of a single blade on its own. Optionally, vibrating assembly <NUM> may be coupled to operative head <NUM>, e.g., via arm <NUM>, of the apparatus, and turbine blade base <NUM> may be vibrated concurrently with applying axial force F. As shown in <FIG>, the position of operative head <NUM> and arm <NUM> may be adjusted as operative head <NUM> vibrates and as mount member <NUM> remains stationary relative to lower half-joint casing <NUM>.

Methods of installing and/or removing blade <NUM> may be particularly effective for installing or removing blades <NUM> which include shroud portion <NUM> configured to form an interlocking profile <NUM> (<FIG>) with circumferentially adjacent blades <NUM>. As shown best in <FIG>, the use of arm <NUM> in apparatus <NUM> can allow a user to substantially align operative head <NUM> (with or without vibrating assembly <NUM>) with a stage of turbine <NUM>, regardless of turbine arrangement. As illustrated, apparatus <NUM> may alternatively be used to install or remove blades <NUM> other than last-stage blades, e.g., at a location positioned axially between stages <NUM>, <NUM>. Apparatus <NUM> can thus be used at any position of turbomachine <NUM> where conventional installation or apparatus have difficulty accessing blades <NUM>.

Where a different stage of turbine blades is to be removed or installed, as shown in <FIG>, the method includes first rotating actuator <NUM> so as to rotate arm <NUM> (and operative head <NUM>) from a first operative position (<FIG>) adjacent rotor wheel <NUM> of first stage of turbine blades <NUM> to a position radially outside of any turbine blades <NUM> on turbine <NUM>. As also shown in <FIG>, actuator <NUM> is axially moved along axially-extending support member <NUM> of support gantry <NUM> to an inoperative position (<FIG>) in which arm <NUM> is radially outside of and axially over a space <NUM> adjacent a different, second stage <NUM> of turbine blades <NUM> of turbomachine <NUM>. The different, second stage <NUM> can be any stage accessible by arm <NUM> and actuator <NUM> via axially-extending support member <NUM>. Actuator <NUM> is then rotated back again (arrow D in <FIG>) so as to rotate arm <NUM> from the inoperative position to another operative position (dashed lines in <FIG>) adjacent a different, second stage <NUM> of turbine blades <NUM>. The mechanical actuating of turbine blade base <NUM> relative to turbomachine <NUM> by applying axial force F against turbine blade base <NUM> through operative head <NUM> is then repeated for any number of turbine blades <NUM> in second stage <NUM>. That is, such that turbine blade base <NUM> transfers into or out of rotor wheel <NUM> of different, second stage <NUM> of turbine blades <NUM>.

Apparatus <NUM> can include one or more materials including and without limitation: metals, plastics, ceramics, and/or other materials adapted for use in the field of turbomachine installation or servicing.

Embodiments of the present disclosure can provide several technical and commercial advantages, some of which are discussed herein by way of example. Embodiments of the fixtures and methods discussed herein can provide substantially uniform manufacturing and/or servicing of turbine blades, such as those used in turbomachines. Embodiments of the present disclosure can also be employed for processes and/or events requiring at least partial disassembly of a turbomachine and/or stage, such as during the inspection of particular components (e.g., last-stage blades of a gas turbine). The various embodiments discussed herein can be operable to install or remove blades in relatively inaccessible locations, without necessitating partial or total deconstruction of adjoining components. The support gantry allows a wide range of adjustment of the apparatus for, for example, different angles and/or different turbines with different mounting locations. The apparatus also allows operation on more than one stage of any given turbine without unbolting the apparatus, saving time. In addition, due to the vertical positioning of the apparatus, the apparatus requires less axial force to transfer the turbine blade base and allows for a safer install or removal of the blade by supporting the blade from above. The apparatus can be operated almost entirely remotely, e.g., using any now known or later developed remote control systems. It is also understood that embodiments of the present disclosure can provide advantages and features in other operational and/or servicing contexts not addressed specifically herein.

Claim 1:
An apparatus (<NUM>) for installing or removing a turbine blade (<NUM>) from a turbine (<NUM>) of a turbomachine (<NUM>), the apparatus (<NUM>) comprising:
an operative head (<NUM>) configured to engage an axial sidewall (<NUM>) of a turbine blade base (<NUM>);
an actuator (<NUM>) configured to move the operative head (<NUM>) to selectively engage the axial sidewall (<NUM>) of the turbine blade base (<NUM>) and impart an axial force against the turbine blade base (<NUM>) to remove or install the turbine blade (<NUM>); and
a support gantry (<NUM>) configured to position the actuator (<NUM>) substantially vertically above the turbine blade (<NUM>) in position in the turbomachine (<NUM>);
wherein the actuator (<NUM>) includes:
a mount member (<NUM>) configured to couple to the support gantry (<NUM>);
a slide system (<NUM>) configured to slidably move the operative head (<NUM>) relative to the mount member (<NUM>); and
a linear actuator (<NUM>) configured to selectively move the slide system (<NUM>) axially relative to the mount member (<NUM>) to apply the axial force;
wherein the operative head (<NUM>) includes an arm (<NUM>) operatively coupled to the actuator (<NUM>); and
wherein the actuator (<NUM>) further includes a coupler (<NUM>) configured to selectively position the mount member (<NUM>);
characterized in that the coupler (<NUM>) is configured to selectively position the mount member (<NUM>) between:
a first state in which the mount member (<NUM>) is axially and pivotally fixed to an axially-extending support member (<NUM>) of the support gantry (<NUM>) and the arm (<NUM>) extends substantially vertically adjacent a first stage (<NUM>) of a plurality of turbine blade stages (<NUM>, <NUM>), and
a second state in which the mount member (<NUM>) is pivotable relative to the axially-extending support member (<NUM>) to position the arm (<NUM>) radially outside of any turbine blade (<NUM>) on the turbine (<NUM>), and axially movable along the axially-extending support member (<NUM>) of the support gantry (<NUM>),
wherein, in the second state, the actuator (<NUM>) is movable along the axially-extending support member (<NUM>) for positioning relative to a different second stage (<NUM>) of the plurality of turbine blade stages (<NUM>, <NUM>).