Patent Publication Number: US-10760434-B2

Title: Transfer of turbine blades to rotor wheel

Description:
BACKGROUND 
     The present disclosure relates generally to turbomachines, and more particularly, to fixtures and methods for transferring turbine blades to a rotor wheel by using components mounted proximally to, and substantially aligned with, the rotor wheel. 
     Rotors for turbomachines such as turbines are often machined from large forgings. Rotor wheels cut from the forgings are typically slotted to accept the roots 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. Latter stage turbine blades are one example in a turbine where blades are exposed to a wide range of flows, loads and strong dynamic forces. Consequently, optimizing the performance of these latter stage turbine blades in order to reduce aerodynamic losses and to improve the thermodynamic performance of the turbine can be a technical challenge. 
     Dynamic properties that affect the design of these latter stage turbine blades include 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. 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, such as aero-thermodynamic properties or material selection, all influence the relationship between performance and 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 latter stage turbine blades presents certain challenges in assembling these blades on a rotor wheel. For example, adjacent turbine blades on a rotor wheel are typically connected together by cover bands or shroud bands positioned around the periphery of the wheel to confine a working fluid within a well-defined path and to increase the rigidity of the blades. These interlocking shrouds may impede the assembly of blades on the rotor wheel. In addition, inner platforms of these blades may include tied-in edges, which also can impede their assembly on the rotor wheel. In some cases, it may be desirable to install multiple turbine blades in a rotor wheel simultaneously. Due to the size and design of each blade, doing so manually or with conventional tools may be impractical. 
     SUMMARY 
     A first aspect of the present disclosure provides a fixture for transferring a plurality of turbine blades, each having a dovetail, into a rotor wheel of a turbomachine, the rotor wheel including a plurality of circumferentially spaced dovetail slots, the fixture including: a first body having an arcuate radially inward surface shaped to contact a rotor of the turbomachine, and a radially outward surface including a plurality of dovetail slots therein shaped to engage the dovetails of the plurality of turbine blades; and a first alignment aperture extending axially through the first body relative to a centerline axis of the turbomachine, and positioned for alignment with a portion of the rotor wheel such that the plurality of dovetail slots of the first body are substantially axially aligned with the plurality of dovetail slots of the rotor wheel for at least partial transfer of the turbine blade thereto from the fixture, wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots of the first body for guided insertion into the plurality of dovetail slots of the rotor wheel. 
     A second aspect of the present disclosure provides a fixture for transferring a plurality of turbine blades, each having a dovetail, into a rotor wheel of a turbomachine having an open rotor therein, the rotor wheel including a plurality of circumferentially spaced dovetail slots, the fixture including: a first body having an arcuate radially inward surface shaped to contact a platform engaging an axial sidewall of the rotor wheel, and a radially outward surface including a plurality of dovetail slots therein shaped to engage the dovetails of the plurality of turbine blades; and a first alignment aperture extending axially through the first body relative to a centerline axis of the turbomachine, and positioned for alignment with a portion of the rotor wheel such that the plurality of dovetail slots of the first body are substantially axially aligned with the plurality of dovetail slots of the rotor wheel for at least partial transfer of the turbine blade thereto from the fixture, wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots of the first body for guided insertion into the plurality of dovetail slots of the rotor wheel. 
     A third aspect of the present disclosure provides a method for transferring a plurality of turbine blades having adjacent dovetails into a rotor wheel of a turbomachine, the rotor wheel having a plurality of circumferentially spaced dovetail slots, the method comprising: engaging a radially inward surface of a fixture with a radially exterior surface of the turbomachine axially proximal to the rotor wheel relative to a centerline axis of the turbomachine, such that a plurality of dovetail slots of the fixture are substantially axially aligned with the plurality of dovetail slots of the rotor wheel; loading a plurality of turbine blades into the plurality of dovetail slots of the fixture, wherein each of the plurality of dovetail slots of the fixture at least partially engage a respective dovetail one of the plurality of turbine blades after the loading; and transferring, in a substantially axial direction, the plurality of turbine blades from plurality of dovetail slots of the fixture to the plurality of dovetail slots of the rotor wheel. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a schematic view of a conventional power generation system. 
         FIG. 2  is a perspective view of a fixture and rotor wheel according to embodiments of the disclosure. 
         FIG. 3  is a perspective view of a fixture according to embodiments of the disclosure. 
         FIG. 4  is a partial cross-sectional view of a turbine blade dovetail and a dovetail slot in a fixture according to embodiments of the disclosure. 
         FIG. 5  is a partial perspective view of a fixture on a platform for an open rotor according to embodiments of the disclosure. 
         FIG. 6  is a side view of a fixture on a platform for an open rotor according to embodiments of the disclosure. 
         FIG. 7  is perspective view of a fixture axially coupled to a connecting aperture of a rotor wheel according to embodiments of the present disclosure. 
         FIG. 8  is a perspective view of a plurality of turbine blades in a fixture being transferred to a rotor wheel according to embodiments of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     Spatially relative terms, such as “inner,” “outer,” “beneath,” “below,” “lower,” “above,” “upper,” “inlet,” “outlet,” and the like, may be used herein for ease of description to describe one element or feature&#39;s relationship to another element(s) or feature(s) as illustrated in the figures. Spatially relative terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as “below” or “beneath” other elements or features would then be oriented “above” the other elements or features. Thus, the example term “below” can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly. 
       FIG. 1  shows a schematic view of a conventional turbomachine  10 . A gas turbine is a type of turbomachine  10  in which compressed air is reacted with a fuel source to generate a stream of hot air. The hot air enters a turbine section and flows against several turbine blades to impart work against a rotatable shaft. The shaft can rotate in response to the stream of hot air, thereby creating mechanical energy for powering one or more loads (e.g., compressors and/or generators) coupled to the shaft. Embodiments of the present disclosure include a fixture for transferring rotor-mounted turbine blades into machines such as turbomachine  10 , e.g., gas turbines, steam turbines, and/or other turbine assemblies. Fixtures according to the present disclosure can be operable to transfer turbine blades to turbomachine  10  where conventional devices may not be usable or practical. Embodiments of the present disclosure may also be capable of transferring turbine blades which cannot be installed or removed solely by the application of mechanical force in one direction. To better illustrate features of the present disclosure during operation, example characteristics of turbomachine  10  are discussed. Combustors T 1 , connected to fuel nozzles T 2 , are typically located between compressor T 3  and turbine T 4  sections of turbomachine  10 . Fuel nozzles T 2  can introduce fuel into combustor T 1  which reacts with compressed air yielded from compressor T 3 . Air T 5  flows sequentially through compressor T 3 , combustor T 1 , and lastly through turbine T 4 . Work imparted to a rotor  12  through turbine T 4  can, in part, drive compressor T 3 . Other forms of turbomachinery besides gas turbines (e.g., gas turbine assembly T) may feature a similar arrangement of components. 
     Referring to the drawings,  FIG. 2  illustrates a fixture  100  adapted for transferring a plurality of turbine blades  120 , each having a respective dovetail protrusion  122 , into a rotor wheel  130  of turbomachine  10  ( FIG. 1 ). In operation, fixture  100  can engage rotor  12  at a predetermined location where turbine blades can be mounted and/or engaged. Each turbine blade  120  can initially be mechanically coupled to fixture  100 . Fixture  100  can be substantially axially aligned (i.e., aligned substantially along the direction of the rotor) with similarly sized and profiled dovetail slots  132  of rotor wheel  130  axially proximal to fixture  100 . Turbine blades  120  can be at least partially axially transferred from fixture  100  to adjacent rotor wheels  130  during operation. As used herein, the term “transfer” or “axial transfer” refers to the process of moving (e.g., by sliding motion) turbine blade(s)  120  from one position to another, such as from fixture  100  into rotor wheel  130 . Thus, embodiments of fixture  100  and other fixtures discussed herein can allow turbine blades  120  to be installed within turbomachine  10  without additional and/or intervening structures or processes. Embodiments of the present disclosure can therefore include methods of installing turbine blades  120  by using embodiments of fixture  100 . 
     Fixture  100  can be operable to transfer turbine blades  120  into a corresponding set of circumferentially spaced dovetail slots  132  of rotor wheel  130 . Fixture  100  may be advantageous for transferring multiple turbine blades  120  to rotor wheel  130  simultaneously, e.g., where structural features of blades  120  impede or prevent successive transfer of each blade  120 , and/or where simultaneously transferring blades  120  offers a significant reduction in time and/or cost. Fixture  100  can include a first body  140  including an arcuate radially inward surface  142  shaped to contact rotor  12  of turbomachine  10 , e.g., at a position axially adjacent or otherwise proximal to rotor wheel  130 . First body  140  and/or other components of fixture  100  can be composed of any currently-known or later-developed material adapted for supporting the composition of turbine blades  120 , and as general examples can include one or more polymerous materials (e.g., a thermoelastic polymer such as polyoxymethylene, acrylonitrile butadiene styrene) and/or metal compounds (e.g., steel, iron, aluminum, etc.). In some embodiments, fixture  100  can be positioned directly axially adjacent to rotor wheel  132  such that fixture  100  engages an axial sidewall  143  of rotor wheel  132 , e.g., through direct contact. Fixture  100  can also include a radially outward surface  144  with multiple dovetail slots  146 . Each dovetail slot  146  of fixture  100  can be shaped to engage a corresponding dovetail protrusion  122  of one turbine blade  120 . Thus, fixture  100  can engage multiple turbine blades  120  therein through dovetail slots  146 . First body  140  can include one or more support members  148  extending, e.g., radially outward such that the radial displacement between dovetail slots  146  and a centerline axis of turbomachine  10  is substantially equal to that between dovetail slots  132  and the same centerline axis. It is understood that the number of support members  148  in fixture  100  can vary, for example, based on the size of fixture  100  and/or rotor wheel  130 . 
     Dovetail slots  146  of fixture  100  can be shaped for insertion of turbine blades  120  therein before turbine blades are transferred to rotor wheel  130 . In some cases, axial mismatch between dovetail slots  146  may impede or prevent transfer of turbine blades  120  to rotor wheel  130 . Axial mismatch refers to a situation where dovetail slots  146  extend axially in parallel relative to dovetail slots  132  of rotor wheel  130  without being substantially aligned with dovetail slots  132  while positioned in fixture  100 . To avoid problems associated with mismatch between dovetail slots  132  of rotor wheel  130  and dovetail slots  146  of fixture  100 , fixture  100  can include a first alignment aperture  150  extending axially through first body  140  relative to centerline axis A of turbomachine  10 . First alignment aperture  150  can conceivably be positioned in any desired region of fixture  100  such that dovetail slots  146  of first body  140  are substantially axially aligned with corresponding dovetail slots  132  of rotor wheel  130 . In further embodiments, first body  140  can also include a second alignment aperture  152  positioned adjacent to dovetail slot  146  opposite from first alignment aperture  150 . First and second alignment apertures  150 ,  152  can define an axial boundary between dovetail slots  146  substantially coincident with portions of rotor wheel  130  which circumferentially separate adjacent dovetail slots  132  therein. Although first alignment aperture  150  may be embodied as a hole, portal, passage, etc., it is understood that first alignment aperture  150  may alternatively embodied as, e.g., a scallop or partially enclosed passage (e.g., quarter circle, half circle, etc.) shaped to receive and at least partially engage an alignment pin  180 , as discussed elsewhere herein. Other apertures discussed herein can similarly be embodied in such alternative forms. 
     When fixture  100  is positioned on rotor  12 , alignment apertures  150 ,  152  can be positioned circumferentially adjacent to successive dovetail slots  146  on first body  140 . Alignment apertures  150 ,  152  being positioned circumferentially between dovetail slots  146  on fixture  100  can allow a user to axially align alignment aperture(s) with portions of rotor wheel  130  positioned circumferentially between dovetail slots  132 . Regardless of where alignment apertures  150 ,  152  are positioned relative to rotor wheel  130 , a user may align fixture  100  with corresponding portions of rotor wheel  130  by way of visual inspection and/or other instruments used with alignment apertures  150 ,  152  described elsewhere herein. Alignment apertures  150 ,  152  can allow a user to visually inspect whether turbine blades  120  are slidably removable from dovetail slots  146  of first body  140  for guided insertion into dovetail slots  132  of rotor wheel at a predetermined position. In addition, alignment apertures  150 ,  152  can allow a user to determine whether multiple dovetail slots  146  of fixture  100  are aligned with multiple dovetail slots  132  of rotor wheel  130 . Axial alignment between multiple dovetail slots  132 ,  146  of fixture  100  and rotor wheel  130  can allow multiple turbine blades  120  to be transferred to rotor wheel  130  together, e.g., as part of a single transferring process. Methods for using fixture  100  to transfer turbine blades  120  to rotor wheel  130  are shown in other FIGS. and described in detail elsewhere herein. 
     Referring to  FIGS. 2 and 3  together, fixture  100  may include additional components for increasing mechanical stability, alignment between dovetail slots  132 ,  146 , and/or other operational characteristics of fixture  100 . For example, fixture  100  can include an axial member  154  coupled to an axial sidewall Si of first body  140 . Axial member  154  may include, e.g., a rigid beam, pole, bolt, etc., with the same material composition as first body  140  or may include a different material composition. As shown in the accompanying FIGS., multiple axial members  154  may each be coupled to first body  140  at respective locations, and can extend substantially in axial direction A relative to turbomachine  10 . One or more axial members  154  may also be coupled to an axial sidewall S 2  of a second body  160  at an opposite end relative to first body  140 . Second body  160  may be structurally similar or identical to first body  140 , and thus may include the same or similar features therein. For example, second body  160  may include an arcuate radially inward surface  142  shaped to circumferentially engage rotor  12 . Second body  160  may also include a radially outer surface  164  with multiple dovetail slots  166 . Each dovetail slot  166  of second body  160  can be shaped to engage a corresponding dovetail protrusion  122  of one turbine blade  120 . Thus, each body  140 ,  160  of fixture  100  can engage multiple turbine blades  120  therein through dovetail slots  146 ,  166 . Axial members  154  of fixture  100  can connect and axially align first and second bodies  140 ,  160 . Axial members  154  can cause each dovetail slot  146  of first body  140  to be substantially axially aligned with a respective dovetail slot  166  of second body  160  and a respective dovetail slot  132  of rotor wheel  130 . Second body  160  may also include first and second alignment apertures  150 ,  152  similar to those of first body  140  and/or arranged in the same manner. For example, first and second alignment apertures  150 ,  152  may be positioned adjacent to opposing circumferential sidewalls of one or more dovetail slots  166  of second body  160 . 
     Fixture  100  may also include additional components for maintaining first and second bodies  140 ,  160  in a fixed position before turbine blades  120  are installed. For example, first or second body  140 ,  160  can include slots  170  shaped to receive a coupler  172  therein. Coupler  172  may be provided in the form of, e.g., a bolt, a rod, a threaded member, and/or any other mechanical instrument shaped to extend through slot(s)  170  to engage a portion of rotor wheel  130 . Coupler  172  may engage a complementary surface of rotor wheel  130  when extending through slot  170 , e.g., as shown, or may extend into complementary features of rotor wheel  130  as described elsewhere herein. In any event, coupler(s)  172  can be inserted into slot(s)  170  of fixture  100  after fixture  100  is mounted on rotor wheel  12  to secure fixture  100  in a predetermined position. 
     Fixture  100  may include a group of alignment pins  180  coupled to fixture  100  (e.g., at first body  140 ) through a tether  182  to align fixture  100  with slots  132 . Each alignment pin  180  can include one or more inflexible materials shaped to extend linearly through first and/or second alignment apertures  150 ,  152  of fixture  100  and along axial axis A. Before positioning turbine blades  120  in dovetail slots  146 ,  166  or transferring turbine blades  120  therefrom, a user may insert alignment pins  180  through alignment apertures  150 ,  152  to define an axial path along which each turbine blade  120  may travel when being transferred to dovetail slots  132  of rotor wheel  130 . Alignment pins  180  may obstruct turbine blades  120  from entering axially misaligned dovetail slots  132  and/or contacting other portions of rotor wheel  130 . Tethers  182  may be composed of a flexible material (e.g., plastics and/or fibrous materials which may be reinforced with metals therein) to physically couple each alignment pin  180  to fixture  100 . Tethers  182  can prevent alignment pins  180  from being dislodged or separated from fixture  100  in the event of a mechanical shock, and/or can prevent alignment pins  180  from being misplaced or accidentally dropped, inserted, etc., into sensitive portions of turbomachine  10 . Alignment pins  180  are shown by example to be disconnected from tethers  182  in  FIG. 3  for the sake of demonstration. Each alignment pin  180  can be mechanically connected to a respective tether  182  before fixture  100  is positioned on rotor  12 . 
     Alignment pins  180  may be embodied as, e.g., quick release pins configured to be selectively mechanically secured to fixture  100  at a desired position. For instance, alignment pins  180  may be configured to lock into place against fixture  100  when fully inserted through alignment aperture(s)  150 ,  152  to engage rotor wheel  130 . An operator of fixture  100  may then selectively disengage alignment pin(s)  180  from fixture  100  to remove alignment pin(s) from alignment apertures  150 ,  152 . In alternative embodiments, alignment pins  180  may include other fastening elements (e.g., simple pins, locks, clamps, etc.) for maintaining alignment pins  180  in a selected position relative to fixture  100  and/or rotor wheel  130 . Such fastening elements may lack quick release components and/or functionality, and/or may be structured to accommodate multiple gas turbine frame sizes. In still further embodiments, alignment pins  180  may include multiple axially-aligned and/or axially connected segments, members, etc., to accommodate gas turbine frames of varying size. Alignment pin(s)  180  may thus include two or more individual members mechanically connected and/or matingly engaged to each other before being inserted in to alignment aperture(s)  150 ,  152  as a single alignment pin  180 . 
     In  FIG. 4 , geometrical features of the engagement between a turbine blade  120  and dovetail slot(s)  146 ,  166  of fixture  100  are shown. It is understood that the various features shown in  FIG. 4  may be included in dovetail slot(s)  146  of first body  140  ( FIGS. 2-3 ) or dovetail slot  166  of second body  160  ( FIGS. 2-3 ) in any embodiment.  FIG. 4  includes a cross-sectional view of dovetail slot  146 ,  166  engaging a turbine blade  120  by receiving a dovetail protrusion  122  within dovetail slot  146 ,  166 . Dovetail slot(s)  146 ,  166  of fixture  100  can include a profile with a substantially undulating or “fir tree” shape with multiple necks  210  alternating with hooks  212  (e.g., in the form of protrusions or similar surfaces) for engaging similarly contoured surfaces of turbine blade  120 , with or without direct contact between the two components throughout dovetail slot(s)  146 ,  166 . Each neck  210  can include a substantially planar contact surface for engaging a dovetail of turbine blade  120 . Although dovetail slot  146 ,  166  is shown by example as substantially complementing a cross-section of turbine blade  120 , it is understood that dovetail slot  146 ,  166  can be of any desired shape or geometry, e.g., a substantially v-shaped slot, one or more triangular wedges, a rectangular or semicircular slot, a slot formed in the shape of a complex geometry, etc. 
     Several hooks  212  can include non-contacting portions (e.g., surfaces) separated from the dovetail of turbine blade  120  when turbine blade  120  engages dovetail slot  146 ,  166  of fixture  100 . These non-contacting portions can define a group of pockets  214  which separate portions of fixture  100  from turbine blade  120 . Pockets  214  can protect portions of dovetail slot  146 ,  166  of fixture  100  from damage caused by, e.g., manufacturing variances between turbine blades  120 , vibratory motion or damage, external shocks and events, frictional contact between the two components, etc. Pockets  214  can be formed, e.g., by removing portions of material from fixture  100  and/or otherwise manufacturing or modifying fixture  100  to define pockets  214 . Among other things, pockets  214  can prevent the structure of fixture  100  from contacting turbine blade  120  at sensitive locations. In operation, fixture  100  and turbine blade  120  can mechanically engage each other at a group of contacting surfaces  216  distributed throughout dovetail slot  146 ,  166  and turbine blade  120 . Pockets  214  can also be formed by manufacturing, modifying, and/or otherwise machining turbine blade  120  to create separation between turbine blade  120  and dovetail slot  146 ,  166 . 
     Dovetail protrusion  122  of turbine blade  120  may include a height dimension H of lesser magnitude than a corresponding height dimension of dovetail slot  146 ,  166 . These differing heights can create a spacing differential between the two components and define a window space  218 . Although one window space  218  is shown by example in  FIG. 4 , it is understood that multiple window spaces  218  can be defined between fixture  100  and turbine blade  120  in embodiments of the present disclosure. It is also understood that pockets  214  can also function as an at least partial window for providing view between fixture  100  and turbine blade  120  where applicable. Window space  218  can be present between dovetail slot  146 ,  166  and dovetail protrusion  122  when dovetail protrusion  122  is installed within fixture  100 . Window space  218  can provide an axial view of an aligned dovetail slot of a rotor wheel (not shown) when dovetail protrusion  122  is positioned and/or secured within dovetail slot  146 ,  166 . 
     Referring to  FIGS. 5 and 6  together, embodiments of the present disclosure can allow a user to transfer turbine blades  120  to rotor wheel  130  even when portions of rotor  12  ( FIGS. 1-3 ) are not present. Rotor  12  of turbomachine  10  may be partially disassembled before turbine blades  120  are ready to be installed or removed within rotor wheel  130 . In this situation, an operator may refer to turbomachine  10  as having an open rotor (e.g., vacant rotor space) therein. Other elements of turbomachine  10 , e.g., rotor wheel  130  and dovetail slots  132 , may be unchanged. A fixture  300  can enable transfer of turbine blades  120  without engaging rotor  12  of turbomachine  10 , as discussed herein. For example, a platform  302  may be axially coupled to and/or mounted on a portion of rotor wheel  130 , e.g., an axial sidewall of rotor wheel  130 . Platform  302  may extend axially outward from rotor wheel  130  in a manner similar to that of rotor  12  in other embodiments. Platform  302  may include an arcuate profile  304  for receiving complimentary portions of fixture  300 . In an example, fixture  300  may include a first body  340  with an arcuate radially inward surface  342  shaped to contact arcuate profile  304  of platform  302 . First body  340  may also include a radially outward surface  344  with multiple dovetail slots  346  therein. Each dovetail slot  346  in fixture  300  can be shaped to receive a portion of turbine blade  120  therein, e.g., dovetail protrusion  122  of turbine blade  120 . When turbine blades  120  are positioned within dovetail slots  346  of fixture  300 , turbine blades  120  can be slidably removable therefrom for guided insertion into dovetail slots  132  of rotor wheel  130 . 
     As described elsewhere relative to alternative embodiments, first body  340  of fixture  300  can include first and/or second alignment apertures  350 ,  352  extending axially therethrough. As noted herein, axial mismatch between dovetail slots  132 ,  346  may impede or prevent transfer of turbine blades  120  to rotor wheel  130 . To avoid problems associated with mismatch between dovetail slots  132  of rotor wheel  130  and dovetail slots  346  of fixture  300 , fixture  300  first and second alignment apertures  350 ,  352  can extend axially through first body  340  relative to centerline axis A of turbomachine  10 . Alignment aperture  350 ,  352  can conceivably be positioned in any desired region of fixture  300  such that dovetail slots  346  of first body  340  are substantially axially aligned with corresponding dovetail slots  132  of rotor wheel  130 . In some cases, second alignment aperture  352  may be positioned adjacent to dovetail slot  346  on an opposing side of dovetail slot  346  relative to first alignment aperture  350 . First and second alignment apertures  350 ,  352  can define an axial boundary between dovetail slots  346  substantially coincident with portions of rotor wheel  130  which circumferentially separate adjacent dovetail slots  132  therein. 
     Fixture  300  may also include components for providing increased mechanical stability on platform  302 . Fixture  100  can include an axial member  354  coupled to an axial sidewall S 1  of first body  340 . Axial member  354  may include, e.g., one or more of the example components and/or material compositions described herein relative to axial member  154  ( FIGS. 2-3 ). As shown in the accompanying FIGS., multiple axial members  354  may each be coupled to first body  340  at respective locations, and can extend substantially in axial direction A relative to turbomachine  10 . One or more axial members  354  may also be coupled to an axial sidewall S 2  of a second body  360  at an opposite end relative to first body  340 . Second body  360  may be structurally similar or identical to first body  340 , and thus may include the same or similar features therein. For example, second body  360  may include an arcuate radially inward surface  342  shaped to engage the radial exterior of platform  302 . Second body  360  may also include a radially outer surface  364  with multiple dovetail slots  366 . 
     Each dovetail slot  366  of second body  360  can be shaped to engage dovetail protrusion  122  of a respective turbine blade  120 . Thus, first and second bodies  340 ,  360  of fixture  300  can engage multiple turbine blades  120  therein through dovetail slots  346 ,  366 . Axial members  354  of fixture  300  can provide a mechanical connection and physical alignment between first and second bodies  340 ,  360 , e.g., such that each dovetail slot  146  is substantially axially aligned with a respective dovetail slot  366  of body  360  and a respective dovetail slot  132  of rotor wheel  130 . Second body  360  may also include first and second alignment apertures  350 ,  352  similar to those of first body  340  and/or arranged in the same manner. For example, first and second alignment apertures  350 ,  352  may be positioned adjacent to opposing circumferential sidewalls of one or more dovetail slots  366  of second body  360 . 
     First and second alignment apertures  350 ,  352  of fixture  300  may each be shaped to house an alignment pin  380  therein. Each alignment pin  380  may optionally be coupled to other portions of fixture  300 , e.g., through one or more tethers (e.g., tether  182  ( FIGS. 2-3 )). Alignment pins  380  can be shaped shaped to extend linearly through first and/or second alignment apertures  350 ,  352  of fixture  300 . As noted elsewhere herein relative to fixture  100  ( FIGS. 2-3 ), a user may insert alignment pin(s)  380  through alignment apertures  350 ,  352  to define axial boundaries during transfer of each turbine blade  120 . Alignment pins  380  may obstruct turbine blades  120  from entering axially misaligned dovetail slots  132  and/or contacting other portions of rotor wheel  130 . 
     Referring to  FIG. 7 , embodiments of fixture(s)  100 ,  300  can include additional components for mechanically securing first body  140 ,  340  to rotor  12 . Some features of fixture(s)  100 ,  300  (e.g., platform  302  ( FIGS. 5-6 )) are omitted from  FIG. 7  for the sake of clarity and to better demonstrate the features shown therein. In addition, although only first body  140 ,  340  is shown by example in  FIG. 7 , further embodiments of fixture(s)  100 ,  300  can alternatively or additionally include the various elements described herein used in conjunction with second body  160 ,  360 , e.g., through modifications apparent to those having ordinary skill in the art. Fixture  100 ,  300  may include a coupler  390  therein such as an axially-extending bolt, fastener, clamp, etc., configured to mechanically couple fixture  100 ,  300  to a connecting member  392 . Connecting member  392  may include or otherwise be embodied as a radially-extending component such as a non-flexible beam, arm, plate, etc., secured to fixture  100 ,  300  through coupler  390 . Connecting member  392  may include one or more metallic and/or polymerous materials described elsewhere herein, or may have a different material composition. Connecting member  392  may be connected to coupler  390  on one end, and may also be connected to a rotor coupler  394  at another end. Rotor coupler  394  may engage an axial surface  396  of rotor  12 , e.g., by being embodied as a threaded or length-adjustable member for mechanically engaging rotor  12 . In addition, rotor coupler  394  may be coupled to connecting member  392  by extending through a passage  398  of connecting member  392 . However embodied, rotor coupler  394  may extend from connecting member  392  proximal to rotor  12 , while coupler  390  may extend from connecting member  392  proximal to fixture  100 ,  300 . 
     In some embodiments, axial surface  396  of rotor  12  may be adapted for receiving a fastener thereon, e.g., by not including additional elements, mechanical connections, etc., where rotor coupler  394  engages rotor  12 . In other embodiments, rotor  12  may be modified such that axial surface  396  is shaped, designed, etc., to accommodate the shape of rotor coupler  394  thereon. However embodied, coupler  390 , connecting member  392 , and/or rotor coupler  394  can further secure fixture  100 ,  300  to rotor  12  during operation to prevent sliding movement of fixture  100 ,  300  during the installation of turbine blades  120  as discussed elsewhere herein. In addition, axial passage  398  of connecting member  392  may also have a size and shape for receiving an axial-cross section of rotor coupler  394  therein. Thus, the surface area of axial surface  396  on rotor  12  may have a similar or identical surface area to that of axial passage  398 . 
     Turning to  FIG. 8 , embodiments of a method for transferring turbine blades  120  into rotor wheel  130  of turbomachine  10  according to embodiments of the present disclosure are described. Similar to other FIGS. described herein, the various processes described herein may be implemented through embodiments of fixture  100 ,  300  and/or equivalent alternatives where applicable. Embodiments of fixture  100 ,  300  may be effective for installing a plurality PB of circumferentially adjacent turbine blades  120 , each having respective dovetail protrusions  122 , together without removing other turbine blades  120  from rotor  12 . Methods of transferring turbine blades  120  through fixture  100 ,  300  can thereby reduce the time and costs of transferring all turbine blades  120  onto rotor  12  during and/or after a servicing operation (e.g., replacement of one or more turbine blades  120 ). In an embodiment, a radially inward surface I F  of fixture  100 ,  300  can be engaged with a radially outward surface I T  of turbomachine  10 , e.g., by being positioned on a rotor stub shaft (“shaft”)  400 , proximal to rotor wheel  130 . 
     Radially outward surface I T  can be positioned on any desired component of turbomachine  10 , and in an example embodiment can be a portion of rotor wheel  130 . In addition to coupler  390 , connecting member  392 , and/or other elements described herein for mechanically securing fixture  100 ,  300  to turbomachine  10  in a selected position, fixture  100  may also be mechanically secured to turbomachine  10  through a securing member  402 , e.g., a plate, mount, and/or other mechanical element. As shown, securing member  402  may extend radially and may be mounted on portions of fixture  100 ,  300 , shaft  400 , and/or rotor wheel  130  to further prevent movement of fixture  100 ,  300  relative to turbomachine  10 . Securing member  402  may be coupled to an axial end of rotor wheel  130 , e.g., by including bolts which extend into corresponding slots (not shown) of rotor wheel  130 . Securing member  402  can thereby by adjusted to align with predetermined turbine blades  120 . In some embodiments, fixture  100 ,  300  may be mounted on shaft  400  without securing member  402  being present. 
     Upon engagement of fixture  100 ,  300  with turbomachine  10 , embodiments of the present disclosure can include loading turbine blades  120  into dovetail slots  146 ,  346  of fixture  100 ,  300 . As noted elsewhere herein, fixture  100 ,  300  can include multiple dovetail slots  146 ,  346  for loading each turbine blade  120  of plurality P B . A user may load turbine blades  120  into fixture  100 ,  300  manually and/or with the aid of external devices for mechanically loading turbine blades  120  into dovetail slots  146 ,  346 . As discussed elsewhere herein relative to  FIG. 4 , turbine blades  120  may partially or fully engage dovetail slots  146 ,  346  when loaded therein. Initially, upon being loaded within fixture  100 ,  300 , each turbine blade  120  may be axially displaced from dovetail slot(s)  132  ( FIGS. 2, 5-6 ) of rotor wheel  130 . Embodiments of the present disclosure can further include mechanically securing fixture  100 ,  300  to rotor  12  before or after loading turbine blades  120  into fixture  100 ,  300 . For example, components such as, e.g., coupler  172 , coupler  390 , shaft  400 , securing member  402 , etc., may be connected to fixture  100 ,  300  and turbomachine  10  before turbine blades  120  are installed to maintain fixture  100 ,  300  in a predetermined location. Where the above-noted components mechanically secure fixture  100 ,  300  to turbomachine  10  before turbine blades  120  are loaded into dovetail slots  146 ,  346 , fixture  100 ,  300  may remain in a predetermined position as turbine blades  120  are transferred to rotor wheel  130 . 
     Methods according to the present disclosure can further include transferring turbine blades  120  to their intended sites of placement within rotor wheel  130 . As noted elsewhere herein, a user of fixture  100 ,  300  may insert alignment pin(s)  180 ,  380  through alignment apertures  150 ,  152 ,  350 ,  352  to define an axial path (e.g., direction S) for transfer. Plurality P B  of turbine blades  120 , after being loaded into fixture  100 ,  300  may then be axially transferred (e.g., along direction S) from dovetail slots  146 ,  346  of fixture  100 ,  300  to a corresponding dovetail slot  132  ( FIGS. 2, 5-6 ) of rotor wheel  130 . Each turbine blade  120  may be transferred from fixture  100  to rotor wheel  130  manually by a user and/or with the aid of external tools or other types of equipment for moving turbine blades  120 . Embodiments according to the present disclosure can thereby provide methods in which multiple turbine blades  120  are transferred axially from the same fixture  100 ,  300  into one rotor wheel  130  together, without being installed one-at-a-time or through more time-consuming processes. 
     Embodiments of the present disclosure can provide several technical and commercial settings, some of which are discussed herein by way of example. Embodiments of the present disclosure can also be employed for processes and/or events requiring at least partial disassembly of a rotating component and/or turbine stage, such as during the inspection of a hot gas path section of particular components (e.g., stage three blades of a steam or gas turbine). The application of a fixture with turbine blade holders furthermore can allow multiple turbine blades to be transferred to a rotor wheel together, without each blade being transferred to a rotor wheel individually. 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 to disclose the invention, including the best mode, and to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention 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.