Patent Publication Number: US-2022235675-A1

Title: Apparatus for removal or installation of turbine blade

Description:
BACKGROUND 
     The present disclosure relates generally to the removal of turbine blades in turbomachine assemblies, and more particularly, to an apparatus for removing or installing a turbine blade from a turbine in a turbomachine. 
     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&#39;clock or nine o&#39;clock relative to the axis of the turbine. This latter approach requires rotating the turbine to position each turbine blade at the three o&#39;clock or nine o&#39;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. 
     SUMMARY 
     An aspect of the present disclosure provides an apparatus to remove or install a turbine blade 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. 
     Another aspect of the disclosure provides an apparatus to remove or install a turbine blade from a turbine, the apparatus comprising: an operative head configured to engage an axial sidewall of a turbine blade base, the operative head including an arm; 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 the turbine blade from the turbine or install the turbine blade in the turbine; and a support gantry configured to position the actuator substantially vertically above the turbine blade, wherein the actuator further includes: a mount member configured to couple to the support gantry; and a fastening member 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 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 member to position the arm radially outside of any turbine blade on the turbine, and axially movable along the axially-extending member of the support gantry, wherein, in the second state, the actuator is movable along the axially-extending member for positioning relative to a different second stage of the plurality of turbine blades. 
     Another aspect of the present disclosure 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; 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. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       These and other features of this disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings that depict various embodiments of the disclosure, in which: 
         FIG. 1  is a schematic view of a conventional turbomachine. 
         FIG. 2  is a cross-sectional view of a number of turbine blade stages of an illustrative turbomachine. 
         FIG. 3  is a perspective view of turbine blades coupled to a rotor wheel, and including an interlocking shroud interface. 
         FIG. 4  is a perspective view of an apparatus for removing and/or installing a turbine blade according to embodiments of the disclosure. 
         FIG. 5  is an enlarged perspective view of an apparatus for removing and/or installing a turbine blade according to embodiments of the disclosure. 
         FIG. 6  is an enlarged perspective of an actuator of the apparatus for removing and/or installing a turbine blade according to embodiments of the disclosure. 
         FIG. 7  is a perspective view of the apparatus for removing and/or installing a turbine blade in an adjustment state, according to embodiments of the disclosure. 
         FIG. 8  is a perspective view of the apparatus for removing and/or installing a turbine blade in an operative state, according to embodiments of the disclosure. 
     
    
    
     It is noted that the drawings of the disclosure are not necessarily to scale. 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. In the drawings, like numbering represents like elements between the drawings. 
     DETAILED DESCRIPTION 
     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&#39;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. 
     In addition, several descriptive terms may be used regularly herein, as described below. The terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. 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. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., “between” versus “directly between,” “adjacent” versus “directly adjacent,” etc.). As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed items. 
     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 +/−3°) 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 can include 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. 1  is a schematic view of an illustrative turbomachine  90  in the form of a combustion turbine or gas turbine (GT) system  100  (hereinafter, “GT system  100 ”). GT system  100  includes a compressor  102  and a combustor  104 . Combustor  104  includes a combustion region  105  and a fuel nozzle assembly  106 . GT system  100  also includes a turbine  108  and a common compressor/turbine shaft  110  (hereinafter referred to as “rotor  110 ”). In one non-limiting example, GT system  100  is a 9HA.01 engine, commercially available from General Electric Company, Greenville, S.C. 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. 2  shows a cross-section view of an illustrative portion of turbine  108  with four stages L 0 -L 3  that may be used with GT system  100  in  FIG. 1 . The four stages are referred to as L 0 , L 1 , L 2 , and L 3 . Stage L 0  is the first stage and is the smallest (in a radial direction) of the four stages. Stage L 1  is the second stage and is the next stage in an axial direction. Stage L 2  is the third stage and is the next stage in an axial direction. Stage L 3  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  112  cooperate with a set of rotating blades  114  to form each stage L 0 -L 3  of turbine  108  and to define a portion of a flow path through turbine  108 . Rotating blades  114  in each set are coupled to a respective rotor wheel  116  that couples them circumferentially to rotor  110 . That is, a plurality of rotating blades  114  are mechanically coupled in a circumferentially spaced manner to each rotor wheel  116 . A static nozzle section  115  includes a plurality of stationary nozzles  112  circumferentially spaced around rotor  110 . Each nozzle  112  may include at least one endwall (or platform)  120 ,  122  connected with an airfoil  129 . In the example shown, nozzle  112  includes a radially outer endwall  120  and a radially inner endwall  122 . Radially outer endwall  120  couples nozzle(s)  112  to a casing  124  of turbine  108 . 
     In operation, air flows through compressor  102 , and compressed air is supplied to combustor  104 . Specifically, the compressed air is supplied to fuel nozzle assembly  106  that is integral to combustor  104 . Fuel nozzle assembly  106  is in flow communication with combustion region  105 . Fuel nozzle assembly  106  is also in flow communication with a fuel source (not shown in  FIG. 1 ) and channels fuel and air to combustion region  105 . Combustor  104  ignites and combusts fuel. Combustor  104  is in flow communication with turbine  108  within which gas stream thermal energy is converted to mechanical rotational energy. Turbine  108  is rotatably coupled to and drives rotor  110 . Compressor  102  also is rotatably coupled to rotor  110 . In the illustrative embodiment, there is a plurality of combustors  104  and fuel nozzle assemblies  106 . In the following discussion, unless otherwise indicated, only one of each component will be discussed. At least one end of rotor  110  may extend axially away from turbine  108  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. 3 , a plurality of blades  114  in a selected stage of blades are shown arranged in a row and mounted circumferentially adjacent to each other on rotor wheel  116 . Blades  114  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  114  is shown in  FIG. 3 , and embodiments of the present disclosure may be effective for installing and removing blades  114  designed for this arrangement or similar arrangements. Each blade  114  can be mechanically coupled to and mounted on rotor wheel  116  through a turbine blade base  130  including, e.g., a dovetail shape designed to fit within and engage a complementary slot within rotor wheel  116 . As shown in  FIG. 3 , blades  114  can extend from turbine blade base  130  with varying profiles and/or contours for accommodating a flow of fluid  132  ( FIG. 2 ) or other fluids across each blade  114 . A radial end of blade  114  can include a shroud portion  134  in the form of a mutually engaging, substantially identical block or plate formed and/or mounted on the tip of each blade  114 . Once each blade  114  is installed on rotor wheel  116 , the engaging blocks or plates of each shroud portion  134  can form a substantially continuous tip shroud element, e.g., a substantially continuous, annular body configured to direct a flow around rotor  110  ( FIG. 1 ). 
     Referring to  FIGS. 2 and 3  together, shroud portion  134  of each blade  114  can include, e.g., an interlocking profile  136  ( FIG. 3  only) for circumferential engagement with shroud portions  134  of adjacent blades  114 . In some examples, interlocking profile  136  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  136  can inhibit axial sliding of each blade  114  relative to rotor wheel  116  after each blade  114  has been installed. In addition, blades  114  may be positioned directly between turbine  108  of turbomachine  90  and an adjacent flow path  138  ( FIG. 2 ), e.g., an exhaust hood or diffusor section of turbomachine  90  ( FIG. 1 ). As shown in  FIG. 2 , each blade  114  may be designed for installation or removal substantially along the direction of axial path N. Interlocking profile  136  can be advantageous during operation of turbomachine  90 , e.g., by maintaining the relative position of each blade  114  relative to each other and to rotor wheel  116 . However, interlocking profile  136  may reduce the ability for one or more blades  114  to be installed or removed from a location directly between two other blades  114  during manufacture or servicing. 
     Embodiments of the present disclosure can mitigate these properties of interlocking profile  136 , e.g., by imparting an axially-oriented force to install or remove blades  114 . In some embodiments, the installed or removed blade  114  can further be subjected to mechanical vibrations. Such vibrations, e.g., can impart oscillating motion to blade  114  and allow axial movement of blade  114  despite various impeding factors, e.g., corrosion, that may impede movement. Various embodiments for imparting axial force, and/or mechanical vibration against blade(s)  114  are discussed herein. As will be described, embodiments of the present disclosure can include an apparatus mounted on fixed structure  140 , such as an exhaust hood  142  ( FIG. 4 ) (e.g., a panel or strut thereof) of turbomachine  90 , a casing  124  of turbomachine  90  such as an outer shell, half-joint casing  150  ( FIG. 4 ), 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  FIGS. 4 and 5  together, an apparatus  200  for installing and/or removing turbine blades  114  at turbine blade base  130  is shown according to embodiments of the present disclosure. Turbine blade base  130  may include a root of turbine blade  114  or may include any portion of turbine blade  114  configured to couple to rotor wheel  116 .  FIG. 4  shows a perspective view of apparatus  200 ,  FIG. 5  shows an enlarged partial perspective view of apparatus  200  to better illustrate various components thereof, and  FIG. 6  shows an enlarged perspective view of an actuator  210  of the apparatus. 
     For purposes of description, blade(s)  114  illustrated in the following drawings may include last-stage (e.g., L 3  ( FIG. 1 )) blades in turbomachine  90 , which may include the same or similar features shown in  FIGS. 2-3  and described elsewhere herein. Last-stage blades  114  may differ from other blades  114  in turbomachine  90 , e.g., by being positioned where conventional vibrating assemblies and/or actuating devices for installing and removing blades  114  cannot be used, or are impractical. However, as will be described, apparatus  200  is advantageously adjustable to remove or install blade(s)  114  from a number of stages within turbomachine  90  without being moved. In addition, apparatus  200  can be located to operate on any stage of blades in practically any turbine  108 . Embodiments of apparatus  200  and other method or apparatus embodiments described herein, can be used to install or remove blade(s)  114  while being mechanically coupled to one or more portions of turbomachine  90 . 
     Apparatus  200  generally includes an operative head  202  movable by an actuator  210  supported by a support gantry  216 . 
     Referring to  FIGS. 4-6 , apparatus  200  includes operative head  202  configured to engage an axial sidewall  204  ( FIGS. 2, 5 and 6 ) of turbine blade base  130 . Operative head  202  is shaped to impart an axial force F against turbine blade base  130 . Operative head  202  can be shaped and/or positioned to engage axial sidewall  204  of turbine blade base  130  while applying mechanical force thereto in an axial direction, i.e., generally parallel to the axis of the turbomachine. Axial sidewall  204  may face upstream or downstream depending on where room is available to install or remove a respective blade  114  from rotor wheel  116 . In one embodiment, operative head  202  includes an arm  206 , which may extend vertically when operatively coupled to an actuator  210 , i.e., the arm is a vertically extending arm. Arm  206  may have any length necessary to properly position operative head  202 , i.e., end of arm  206 , to engage axial sidewall  204  of turbine blade base  130 . While one length of arm  206  is illustrated, arm  206  may be selected from a set of different length arms, which may be provided as part of apparatus  200  so it can be used with any radial length of turbine blade  114 , and/or a variety of different stages of a given turbine  108 . Alternatively, as shown in  FIG. 6 , vertically extending arm  206  may be length adjustable. It can be made length adjustable using any solution, for example, by changing its vertical position relative to actuator  210  using a coupling member  258  and/or plate couplers  260  (e.g., bolts, screws, etc.) joining the arm to coupling members  258 —see adjustment slot  262 . While a slot  262  is shown, any form of selectable opening(s) can also be used. Operative head  202  may include any structure to engage axial sidewall  204 , e.g., at end of arm  206  adjacent axial sidewall  204 . That is, operative head  202  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  202  can be embodied as, e.g., one or more vibrating hammers, plates, cylinders, rollers, etc. In one embodiment, operative head  202  may include an engagement element  208  ( FIG. 6 ) configured to engage axial sidewall  204  of turbine blade base  130 , and slide along axial sidewall  204  of turbine blade base  130  while the rotor rotates. 
     Operative head  202  may also include a vibrating assembly  212  including a vibratory drive mechanism  214  coupled to arm  206 . In some implementations, vibratory drive mechanism  214  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  212 , e.g., through a fluid source. Vibratory drive mechanism  214  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  212  can be adjustably coupled to and/or positioned directly on arm  206  using any now known solution, e.g., fasteners, welding, etc. Vibrating assembly  212  may be adjustably mounted to arm  206  to allow positioning anywhere along a length of arm  206 . 
     Apparatus  200  also includes support gantry  216  configured to position actuator  210  substantially vertically above turbine blade  114 , while turbine blade  114  is in position in turbine  108  of turbomachine  90 . As used herein, “substantially vertical” indicates +/−10° from vertical. Support gantry  216  can include any now known or later developed bridge-like overhead structure with a platform supporting actuator  210 , and having sufficient strength to withstand the motive forces applied thereto. Support gantry  216  may mount to any fixed structure  140 . In certain embodiments, support gantry  216  may mount to a portion of turbomachine  90  in which turbine blade  114  is positioned. As illustrated in  FIG. 4 , an outer shell, upper half-joint casing (not shown) can be removed, leaving an outer shell, lower half-joint casing  150 . Here, turbine  108  including turbine blade  114  is in position for operation of turbine  108 , excepting for the remove of any outer shell, upper half-joint casing. The portion of turbomachine  90  to which support gantry  216  mounts may include fixed structure  140  that is, for example, adjacent to turbine  108 , and/or in which turbine  108  is positioned, e.g., lower half-joint casing  150 . In the example shown, support gantry  216  mounts to opposing sides  232 ,  234  of lower half-joint casing  150  in which turbine  108  is positioned, and an exhaust hood  142  adjacent to turbine  108 . While support gantry  216  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  140 , e.g., power plant floor, other casings, other structure adjacent turbine  108 , cranes within a power plant, among many other options. Any mounting mechanism  236  capable of fixedly attaching support gantry  216  to fixed structure  140  may be used, e.g., bolted or clamped mounting plates, etc. 
     As illustrated, in certain embodiments, support gantry  216  may include a plurality of adjustable support members  230  configured to accommodate a plurality of different turbines  108 , 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  230  may include scaffolding members similar to those used in construction applications. Any number of support members  230  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  230  are capable of positioning actuator  210  at any lateral position above turbine  108 , and any axial position along axis A of turbine  108 . For purposes described herein, in certain embodiments, at least one support member  238  extends axially, i.e., parallel to axis A of turbine  108 . 
     To effectuate movement of operative head  202 , apparatus  200  can include actuator  210  mechanically coupled to operative head  202 , i.e., arm  206 , such that actuation of actuator  210  causes operative head  202  and arm  206  to move relative to turbine blade base  130 . More particularly, actuator  210  is configured to move the operative head  202  to selectively engage axial sidewall  204  of turbine blade base  130  and impart an axial force F against turbine blade base  130  to remove or install turbine blade  114 . As shown best in  FIGS. 5 and 6 , actuator  210  can include a mount member  240  configured to couple to support gantry  216 . Mount member  240  may include any structural member capable of coupling to an axially-extending support member  238  of support gantry  216 . In certain embodiments, mount member  240  takes the form of a plate; however, other forms are also possible. Mount member  240  can include any number of couplers  242  in the form of, e.g., pipe clamps, or other forms of couplers appropriate for the shape and dimensions of axially-extending support member  238 . Couplers  242  may extend outward from mount member  240  to engage one or more portions of axially-extending support member  238 . Couplers  242  can be selectively fastened and unfastened to remove actuator  210  from support gantry  216 , or allow movement of actuator  210  relative to support gantry  216 . More particularly, couplers  242  can be selectively fastened and unfastened to allow actuator  210  to be moved axially relative to turbine blade  114  thereunder, e.g., along axially-extending support member  238 , to allow desired axially positioning of operative head  202 . In this manner, apparatus  200  can be used to remove or install turbine blades  114  on numerous stages of turbine  108  without having to move support gantry  216  or other parts of apparatus  200 . Axially-extending support member  238  can have any length required to allow movement to as many stages of turbine  108  as desired with a single mounting of apparatus  200 . 
     Actuator  210  also includes a slide system  250  configured to slidably move operative head  202  relative to mount member  240  (axially), and hence, turbine blade  114 . Actuator  210  also includes a linear actuator  252  configured to selectively move slide system  250  axially relative to mount member  240  to apply the axial force F to axial sidewall  204  of turbine blade base  130 . Slide system  250  may include one or more axial guides  254  to enable movement of operative head  202  with arm  206  relative to mount member  240  in at least one direction, e.g., along line T. Axial guides  254  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  254  are embodied as a rail or other slidable bearing, a pair of slidable couplings  256  may each be slidably connected to and/or mounted on respective axial guides  254 . Slidable couplings  256  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  254  are in the form of a gear bearing or alternative component for providing a slidable coupling between two mechanically engaged elements, slidable couplings  256  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  258  may be provided as a unitary housing shaped to engage an outer surface profile of arm  206 , or alternatively may be coupled to one surface of arm  206 . In this case, another coupling member  258  can be coupled to another surface of arm  206 , with plate couplers  260  (e.g., bolts, screws, rivets, etc.) joining the two coupling members  258  together. As will be recognized, a variety of alternative mechanisms to couple arm  206  to slide system  250  may also be employed. 
     An operator may further control the position of operative head  202  and arm  206  relative to mount member  240  with additional components included within and/or operably connected to actuator  210 . For example, linear actuator  252  may include any form of drive mechanism  253  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  202  and arm  206  across axial guide(s)  254 . In the non-limiting example illustrated, linear actuator  252  includes a worm gear  255  that interacts with coupling member  258  to move operative head  202  and arm  206 . Linear actuator  252  can be coupled to mount member  240 , e.g., through a bearing  266  shaped to receive a portion of linear actuator  252  therein. Bearing  266  can be positioned at opposing ends of mount member  240  to allow for a worm gear  255  to rotate freely in order to move a slide system  250 . Slide system  250 , worm gear  255  and/or drive mechanism  252  may be coupled using any necessary adapters (not shown). Each bearing  266  can be mounted on a portion of mount member  240 , e.g., by being mechanically affixed thereto through conventional fasteners such as bolts, screws, rivets, etc. 
     In addition to positioning actuator  210  axially on axially-extending support member  238 , as described herein, coupler  242  is also configured to selectively position mount member  240  of actuator  210  between two states. A first, operative state, as shown in  FIGS. 4 and 5 , is one in which mount member  240  is axially and pivotally fixed to axially-extending support member  238  of support gantry  216 . Here, arm  206  extends substantially vertically adjacent a first stage  270  of a plurality of turbine blade stages (see plurality of emptied rotor wheels  116 ). This state is an operative state of apparatus  200  in which actuator  210  can be actuated to remove or install turbine blades  114  in the selected rotor wheel  116  for the selected blade stage.  FIG. 7  shows another, second adjustment state in which couplers  242  have been released sufficiently to allow mount member  240  to be pivotable relative to axially-extending support member  238  (see arrow B) to position arm  206  radially outside of any turbine blade  114  on turbine  108 , and axially movable along axially-extending support member  238  of support gantry  216 . In the second state, actuator  210  is movable along axially-extending support member  238  for positioning relative to a different second stage  272  of plurality of turbine blades  114  (see arrow C). Once in a new, desired position, actuator  210  can be rotated back so that operative head  202  is in a location to apply axial force F to axial sidewall  204  of a selected turbine blade base  130  (see arrow D). In this manner, despite support gantry  216  not moving, apparatus  200  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  114  from a turbine  108  of turbomachine  90  may include mounting apparatus  200 , as described herein, to a portion of turbomachine  90 . In one non-limiting example, mounting includes mounting support gantry  216  to opposing sides  232 ,  234  of half-joint casing  150  in which turbine  108  is positioned, and to exhaust hood  142  adjacent to turbine  108  in turbomachine  90 . Operative head  202  may be substantially axially aligned with turbine blade base  130  of a selected blade  114 . Using actuator  210 , operative head  202  may be moved to engage operative head  202  of apparatus  200  with turbine blade base  130  (before actuating turbine blade base). As shown in  FIG. 8 , the method may further include mechanically actuating turbine blade base  130  relative to turbomachine  90  by applying axial force F against turbine blade base  130  through operative head  202  causing turbine blade base  130  to transfers into or out of rotor wheel  116  of a first stage of turbine blades  114 . That is, operative head  202  under actuation by actuator  210  through arm  206  forces turbine blade  114  into or out of rotor wheel  116 . In terms of installation, these actions can move blade  114  axially toward rotor wheel  116  such that blade  114  is installed between two other blades  114 . In the case of removal, operative head  202  can contact and axially move blade  114  out of position between two adjacent blades  114 , and out of rotor wheel  116 . 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  212  may be coupled to operative head  202 , e.g., via arm  206 , of the apparatus, and turbine blade base  130  may be vibrated concurrently with applying axial force F. As shown in  FIG. 8 , the position of operative head  202  and arm  206  may be adjusted as operative head  202  vibrates and as mount member  240  remains stationary relative to lower half-joint casing  150 . 
     Methods of installing and/or removing blade  114  may be particularly effective for installing or removing blades  114  which include shroud portion  134  configured to form an interlocking profile  136  ( FIG. 3 ) with circumferentially adjacent blades  114 . As shown best in  FIG. 8 , the use of arm  206  in apparatus  200  can allow a user to substantially align operative head  202  (with or without vibrating assembly  212 ) with a stage of turbine  108 , regardless of turbine arrangement. As illustrate, apparatus  200  may alternatively be used to install or remove blades  114  other than last-stage blades, e.g., at a location positioned axially between stages  270 ,  272 . Apparatus  200  can thus be used at any position of turbomachine  90  where conventional installation or apparatus have difficulty accessing blades  114 . 
     Where a different stage of turbine blades is to be removed or installed, as shown in  FIG. 7 , the method may include first rotating actuator  210  so as to rotate arm  206  (and operative head  202 ) from a first operative position ( FIGS. 4-5 ) adjacent rotor wheel  116  of first stage of turbine blades  114  to a position radially outside of any turbine blades  114  on turbine  108 . As also shown in  FIG. 7 , actuator  210  may be axially moved along axially-extending support member  238  of support gantry  216  to an inoperative position ( FIG. 7 ) in which arm  206  is radially outside of and axially over a space  276  adjacent a different, second stage  272  of turbine blades  114  of turbomachine  90 . The different, second stage  272  can be any stage accessible by arm  206  and actuator  210  via axially-extending support member  238 . Actuator  210  may then be rotated back again (arrow D in  FIG. 7 ) so as to rotate arm  206  from the inoperative position to another operative position (dashed lines in  FIG. 7 ) adjacent a different, second stage  272  of turbine blades  114 . The mechanical actuating of turbine blade base  130  relative to turbomachine  90  by applying axial force F against turbine blade base  130  through operative head  202  can then be repeated for any number of turbine blades  114  in second stage  272 . That is, such that turbine blade base  130  transfers into or out of rotor wheel  116  of different, second stage  272  of turbine blades  114 . 
     Apparatus  200  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. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. 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. 
     This written description uses examples, including the best mode, and to enable any person skilled in the art to practice the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.