Device for removing or installing turbine blades

Abstract

An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is provided. The apparatus includes an operating head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operating head to selectively engage the axial sidewall of the turbine blade base and apply an axial force to 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. Among other advantages, the support gantry allows for tuning the apparatus for different turbines and for using the head for multiple stages of any turbine.

Description

[Technical field]

[0001] The present disclosure relates generally to the removal of turbine blades in a turbomachine assembly, and more particularly, to an apparatus for removing or installing turbine blades from a turbine within a turbomachine. [Background technology]

[0002] Turbomachinery turbine rotors are often machined from large forgings. The rotor wheels cut from the forgings are usually grooved to accommodate the bases of the turbine blades. As the demand for increased turbine power and more efficient turbine performance continues to grow, turbomachinery is being fitted with larger and more articulated turbine blades. Dynamic properties that influence the design of these latter stage turbine blades include the various blade profiles and external shapes used in turbomachinery, which can affect the flow velocity profile and other characteristics of the working fluid in the system. In addition to the blade profile, 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 also significantly affect the performance of the system. Damping and blade fatigue are other characteristics that play a role in the mechanical design of the blades and their profiles. These blade mechanical and dynamic response characteristics, as well as other characteristics, all affect the relationship between performance and the surface profile of the turbine blade. As a result, the profiles of later stage turbine blades often contain complex blade geometries to improve performance while minimizing losses under a wide range of operating conditions.

[0003] The application of complex blade geometries to turbine blades, especially later stage turbine blades, poses particular challenges in the assembly and disassembly of these blades on the rotor wheel. For example, adjacent turbine blades on a rotor wheel are typically connected to each other by cover bands or interlocking tip shrouds placed around the periphery of the blades to confine the working fluid within a well-defined path and to increase the stiffness of the blades. These interlocking shrouds may prevent straightforward assembly and disassembly of the blades placed on the rotor wheel. In addition, the inner platforms of these blades and their dovetail slots are often angled with respect to the axis of the turbine rotor wheel to which they are attached, which may also prevent assembly to the rotor wheel. In many cases, turbine blades must be removed one by one. The working environment in which the turbine blades are used may cause, for example, corrosion and thermal distortion, and may require significant force to disassemble the blades.

[0004] One method of removal or installation of turbine blades requires the blades to be forced to move axially by applying a force against another part of the turbine, such as the adjacent rotor wheel. Applying force to adjacent structures can damage the structure. Another approach is to mount the removal or installation device in a cantilevered fashion to a portion of the turbine half-joint casing, i.e., at 3 o'clock or 9 o'clock relative to the axis of the turbine. This latter approach requires the turbine to be rotated to position each turbine blade at 3 o'clock or 9 o'clock so that the turbine blade extends generally horizontally from the rotor wheel in a cantilevered fashion. As a result, the weight of the turbine blade works against the removal or installation of the turbine blade by applying a torque to the dovetail connection at the base of the turbine blade, requiring a larger axial force to remove the turbine blade. Additionally, it is very difficult to support the turbine blades during removal and / or installation so that they do not drop or rotate in a manner that could damage the turbine blades, the rotor wheel, the half joint casing, or other components of the turbine. If the turbine blades are installed in angled dovetail slots, i.e., dovetail slots that face each other relative to the axis of the turbine, the rotor must be rotated as the turbine blades are inserted or pulled out of position, which is extremely difficult if the blades are generally horizontal. Summary of the Invention

[0005] One aspect of the disclosure provides an apparatus for removing or installing 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 selectively engage the axial sidewall of the turbine blade base and move the operative head to apply 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 at a location within the turbomachine.

[0006] Another aspect of the disclosure provides an apparatus for removing or installing a turbine blade from a turbine, the apparatus comprising: a manipulation head configured to engage an axial sidewall of a turbine blade base, the manipulation head including an arm; and an actuator configured to move the manipulation head to selectively engage the axial sidewall of the turbine blade base and apply an axial force to the turbine blade base to remove or install the turbine blade from or in the turbine; and a support gantry configured to position the actuator substantially vertically above the turbine blades, where 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 and a second state, where in the first state the mount member is axially and pivotally fixed to an axially extending support of the support gantry and the arm extends substantially vertically adjacent to a first stage of the plurality of turbine blade stages, and in the second state the mount member is pivotable relative to the axially extending member to position the arm radially outward of any turbine blades on the turbine and movably position the mount member along the axially extending support of the support gantry, and in the second state the actuator is moveable along the axially extending member for positioning relative to a different second stage of the plurality of turbine blades.

[0007] Another aspect of the disclosure relates to a method for installing or removing a turbine blade from a turbine of a turbomachine. The method includes mounting an apparatus to a portion of the turbomachine. The apparatus includes an actuator head configured to engage an axial sidewall of a turbine blade base, an actuator configured to selectively engage the axial sidewall of the turbine blade base and move the actuator head to apply an axial force to the turbine blade base, and a support gantry configured to position the actuator substantially vertically above the turbine blade. The method includes mechanically actuating the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via the actuator head such that the turbine blade base moves into or out of a rotor wheel of a first stage of the turbine blade.

[0008] These and other features of the present 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 illustrating various embodiments of the present disclosure: [Brief description of the drawings]

[0009] [Figure 1] 1 is a schematic diagram of a conventional turbomachine. [Diagram 2] 1 is a cross-sectional view of multiple turbine blade stages of an exemplary turbomachine; [Diagram 3] FIG. 1 is a perspective view of a turbine blade coupled to a rotor wheel and including an interlocking shroud interface. [Figure 4] 1 is a perspective view of a turbine blade removal and / or installation apparatus according to an embodiment of the present disclosure. [Diagram 5] 2 is an enlarged perspective view of a turbine blade removal and / or installation apparatus according to an embodiment of the present disclosure; FIG. [Figure 6] FIG. 2 is an enlarged perspective view of an actuator of a turbine blade removal and / or installation apparatus according to an embodiment of the present disclosure. [Figure 7] 1 is a perspective view of an apparatus for removing and / or installing a turbine blade in an adjustment state according to an embodiment of the present disclosure. [Figure 8] 1 is a perspective view of an apparatus for removing and / or installing turbine blades in an operational state according to an embodiment of the present disclosure.

[0010] It should be noted that the drawings of the present disclosure are not necessarily to scale. The drawings are intended to depict only typical aspects of the present disclosure, and therefore should not be considered as limiting the scope of the present disclosure. In the drawings, like numbers represent like elements between the drawings.

[0011] As an initial matter, in order to clearly explain the subject matter of this disclosure, it becomes necessary to select specific terms when referring to and describing relevant machine parts within turbomachinery. Wherever possible, common industry terms are used and employed in a manner consistent with their common meaning. Unless otherwise specified, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will appreciate that certain components are often referred to using several different or overlapping terms. What is described herein as being a single part may in other contexts include and be referred to as being made up of several parts. Alternatively, what is described herein as including several components may be referred to elsewhere as being a single part.

[0012] In addition, several descriptive terms may be used periodically herein, and it may be beneficial to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise noted: "Downstream" and "Upstream" as used herein are terms that indicate a direction relative to the flow of a fluid, such as the working fluid through a turbine or, for example, the flow of air through a combustor or the flow of a 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 in which the flow occurs). Additionally, the terms "forward" and "aft" refer to directions, without further specification, with "forward" referring to the front or compressor end of the engine and "aft" referring to the aft section of the turbomachine.

[0013] Furthermore, certain descriptive terms may be used regularly in this specification, as explained below: The terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to imply any position or importance of the individual components.

[0014] The terms used herein are for the purpose of describing particular embodiments only and are not intended to be limiting of the disclosure. As used herein, the singular forms "a," "an," and "the" are intended to include the plural unless the context clearly indicates otherwise. It will be further understood that as used herein, the terms "comprises" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not exclude 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 described component or element may or may not be present, and that the description includes instances in which the event occurs or the element is present as well as instances in which it does not occur or is not present.

[0015] When an element or layer is referred to as being "on," "engaged," "connected," or "coupled" to another element or layer, it may be directly engaged, connected, or coupled to the other element or layer, or there may be intervening elements or layers. In contrast, when an element is referred to as being "directly," "directly engaged," "directly connected," or "directly coupled" to another element or layer, there may not be any intervening elements or layers. Other words used to describe relationships between elements should be interpreted similarly (e.g., "between" vs. "directly between," "adjacent" vs. "directly adjacent," etc.). As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0016] As shown in these figures, the "A" axis represents an axial orientation (along the axis of the rotor of the turbomachine). As used herein, the terms "axial" and / or "axially" refer to the relative position / orientation of an object along an axis A that is substantially parallel (i.e., within ±3°) to the axis of rotation of the turbomachine (particularly its rotor section). As further used herein, the terms "radial" and / or "radially" refer to the relative position / orientation of an object along an axis (R) that is substantially perpendicular to axis A and intersects axis A at only one location. It is often necessary to describe components that are located at different radial positions relative to a central axis. For example, if a first component is located closer to the axis than a second component, the first component is described herein as being "radially inward" or "inboard" of the second component. On the other hand, if a first component is located farther from the axis than the second component, the first component may be described herein as being "radially outward" or "outboard" of the second component. Additionally, the terms "circumferential" and / or "circumferentially" refer to the relative position / orientation of an object along a circumference (C) that surrounds axis A but does not intersect axis A at any location. In diagrams showing two-dimensional views, circumference C may be omitted for clarity.

[0017] The terms "transfer" or "axial transfer" refer to a process of moving a component, such as a blade, from one location to another, such as into or out of a dovetail slot of a rotor wheel (e.g., by a sliding motion). Thus, embodiments of the disclosure described herein may allow for the installation or removal of a turbine blade into or from a rotor wheel of a turbine by moving one or more turbine blades. While removal of a turbine blade is shown with more particularity in the drawings, it is understood that various embodiments described herein may be operable to install and / or remove a turbine blade in a rotor wheel without altering the various components and / or process methodologies described. Embodiments of the disclosure also provide methods of installing turbine blades by using various apparatus and / or similar assemblies discussed herein.

[0018] An embodiment of the present disclosure provides an apparatus, and associated method, for removing or installing a turbine blade from a turbine of a turbomachine. The apparatus may include an operating head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operating head to selectively engage the axial sidewall of the turbine blade base and apply an axial force to 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. Among other advantages, the support gantry allows for a wide range of adjustments of the apparatus, for example, for different turbines at different angles and different installation positions. The apparatus may also be used to operate multiple stages of a turbine without removing the apparatus, saving time. Additionally, because the apparatus is vertically positioned, less axial force is required to move the turbine blade, and supporting the blade from above allows for a safer installation or removal of the blade. The apparatus may be operated almost remotely, further enhancing safety.

[0019] Referring to the drawings, FIG. 1 is a schematic diagram of an exemplary turbomachine 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter "GT system 100"). The GT system 100 includes a compressor 102 and a combustor 104. The combustor 104 includes a combustion section 105 and a fuel nozzle assembly 106. The GT system 100 also includes a turbine 108 and a common compressor / turbine shaft 110 (hereinafter "rotor 110"). In one non-limiting example, the GT system 100 is a 9HA.01 engine available from General Electric Company, Greenville, SC. ​​The present disclosure is not limited to any particular GT system and may be adapted in connection with other engines including, for example, other HA, F, B, LM, GT, TM and E class engine models from General Electric Company as well as engine models from other companies. Additionally, the teachings of the present disclosure do not necessarily apply only to GT systems but may be applied to other types of turbomachines such as steam turbines, jet engines, compressors, etc.

[0020] FIG. 2 is a cross-sectional view of an example portion of a turbine 108 with four stages L0-L3 that may be used with the GT system 100 of FIG. 1. The four stages are designated L0, L1, L2, and L3. Stage L0 is the first stage and is the smallest (radially) of the four stages. Stage L1 is the second stage and is the next axially. Stage L2 is the third stage and is the next axially. Stage L3 is the fourth and final stage and is the largest (radially). It should be understood that four stages are shown by way of example only and that each turbine may have more or less than four stages.

[0021] A set of stationary vanes or nozzles 112 cooperate with a set of rotating blades 114 to form each stage L0-L3 of the turbine 108 and define a portion of the flowpath through the turbine 108. Each set of rotating blades 114 is coupled to a respective rotor wheel 116 that circumferentially couples them to the rotor 110. That is, the plurality of rotating blades 114 are circumferentially spaced apart and mechanically coupled to each rotor wheel 116. A static nozzle section 115 includes a plurality of stationary nozzles 112 that are circumferentially spaced apart about the rotor 110. Each nozzle 112 may include at least one endwall or platform 120, 122 connected to an airfoil 129. In the illustrated example, the nozzle 112 includes a radially outer endwall 120 and a radially inner endwall 122. A radially outer endwall 120 couples the nozzle 112 to a casing 124 of the turbine 108 .

[0022] In operation, air flows through the compressor 102 and the compressed air is delivered to the combustor 104. Specifically, the compressed air is delivered to a fuel nozzle assembly 106 that is integral with the combustor 104. The fuel nozzle assembly 106 is in flow communication with a combustion region 105. The fuel nozzle assembly 106 is also in flow communication with a fuel source (not shown in FIG. 1 ) and channels fuel and air to the combustion region 105. The combustor 104 ignites and burns the fuel. The combustor 104 is in flow communication with a turbine 108 in which thermal energy in the gas stream is converted to mechanical rotational energy. The turbine 108 is rotatably coupled to and drives a rotor 110. The compressor 102 is also rotatably coupled to the rotor 110. In the illustrated embodiment, there are multiple combustors 104 and fuel nozzle assemblies 106. In the following description, only one of each component is described unless otherwise noted. At least one end of the rotor 110 may extend axially away from the turbine 108 and may be attached to a load or machine (not shown), such as, but not limited to, an electrical generator, a load compressor, and / or another turbine.

[0023] Turning to FIG. 3, a plurality of blades 114 of selected stages are shown arranged in a row and mounted circumferentially adjacent on a rotor wheel 116. The blades 114 may be designed to remain circumferentially engaged with one another during operation and when subjected to relatively high loads. An exemplary form of mechanical engagement between circumferentially adjacent blades 114 is shown in FIG. 3, and embodiments of the present disclosure may be effective for installation and removal of blades 114 designed for this or similar arrangements. Each blade 114 may be mechanically coupled to and mounted to the rotor wheel 116 via a turbine blade base 130 that includes, for example, a dovetail slot configuration designed to fit and engage within a complementary slot in the rotor wheel 116. As shown in FIG. 3, the blades 114 may extend from the turbine blade base 130 with varying profiles and / or contours to accommodate the flow of a fluid 132 (FIG. 2) or other fluid across each blade 114. The radial ends of the blades 114 may include shroud portions 134 in the form of interlocking, substantially identical blocks or plates formed and / or attached to a tip of each blade 114. When each blade 114 is attached to the rotor wheel 116, the engaging blocks or plates of each shroud portion 134 may form a substantially continuous tip shroud element, e.g., a substantially continuous, annular body configured to direct flow around the rotor 110 (FIG. 1).

[0024] 2 and 3 together, the shroud portion 134 of each blade 114 can include, for example, an interlocking profile 136 ( FIG. 3 only) for circumferentially engaging the shroud portion 134 of an adjacent blade 114. In some examples, the interlocking profile 136 can 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, and the like. However embodied, the interlocking profile 136 can inhibit axial sliding of each blade 114 relative to the rotor wheel 116 after each blade 114 is attached. Additionally, the blades 114 may be positioned directly between the turbine 108 of the turbomachine 90 and an adjacent flowpath 138 ( FIG. 2 ), such as an exhaust hood or diffuser section of the turbomachine 90 ( FIG. 1 ). As shown in FIG. 2 , each blade 114 may be designed to be installed or removed substantially along the direction of an axial path N. The interlocking profile 136 may be advantageous during operation of the turbomachine 90, for example, by maintaining the relative position of each blade 114 relative to each other and to the rotor wheel 116. However, the interlocking shape 136 may reduce the ability to install or remove one or more blades 114 directly from a position between two other blades 114 during manufacturing or maintenance.

[0025] Embodiments of the present disclosure can mitigate these characteristics of the mating profile 136, for example, by applying an axial force to install or remove the blade 114. In some embodiments, the installed or removed blade 114 can further be subjected to mechanical vibrations. Such vibrations can, for example, impart a vibratory motion to the blade 114, allowing axial movement of the blade 114 despite various impeding factors, e.g., erosion, that may prevent the movement. Various embodiments for applying axial forces and / or mechanical vibrations to the blade(s) 114 are discussed herein. As will be described, embodiments of the present disclosure can include devices attached to a stationary structure 140, such as an exhaust hood 142 ( FIG. 4 ) (e.g., a panel or column thereof) of the turbomachine 90, an outer shell, a casing 124 of the turbomachine 90, such as a half-joint casing 150 ( FIG. 4 ), and / or other turbomachine components that can have various structural features mounted thereon. In contrast to current approaches, the device is vertically, radially above the turbine blades.

[0026] 4 and 5 together, an apparatus 200 for installing and / or removing a turbine blade 114 from a turbine blade base 130 is shown in accordance with an embodiment of the present disclosure. The turbine blade base 130 may include the root of the turbine blade 114 or may include any portion of the turbine blade 114 configured to couple to a rotor wheel 116. FIG. 4 is a perspective view of the apparatus 200, FIG. 5 is an enlarged partial perspective view of the apparatus 200 to better illustrate its various components, and FIG. 6 is an enlarged perspective view of an actuator 210 of the apparatus.

[0027] For purposes of illustration, the one or more blades 114 illustrated in the following figures may include a final stage (e.g., L3 (FIG. 1)) blade of the turbomachine 90, which may include the same or similar features as those shown in FIGS. 2-3 and described elsewhere herein. The final stage blade 114 may differ from other blades 114 of the turbomachine 90, for example, by being located in a location where conventional vibratory assemblies and / or actuation devices for installing and removing the blade 114 are unavailable or impractical. However, as will be described, the apparatus 200 is advantageously adjustable to remove or install the blade 114 from multiple stages within the turbomachine 90 without moving the blade 114. Furthermore, the apparatus 200 may be arranged to operate on blades of substantially any stage of any turbine 108. Embodiments of the apparatus 200, as well as other method or apparatus embodiments described herein, may be used to install or remove one or more blades 114 while mechanically coupled to one or more portions of the turbomachine 90.

[0028] The apparatus 200 generally includes a scanning head 202 that is movable by an actuator 210 supported by a support gantry 216 .

[0029] 4-6, the apparatus 200 includes an Operative head 202 configured to engage an axial sidewall 204 (FIGS. 2, 5 and 6) of the turbine blade base 130. The Operative head 202 is configured to apply an axial force F to the turbine blade base 130. The Operative head 202 can be shaped and / or positioned to apply a mechanical force in an axial direction, i.e., generally parallel to the axis of the turbomachine, while engaging the axial sidewall 204 of the turbine blade base 130. The axial sidewall 204 can face upstream or downstream depending on the space available to install or remove the respective blade 114 from the rotor wheel 116. In one embodiment, the Operative head 202 includes an arm 206 that can extend vertically when operably coupled to the actuator 210, i.e., the arm is a vertically extending arm. The arm 206 may have any length necessary to properly position the manipulation head 202, i.e., the end of the arm 206, to engage the axial sidewall 204 of the turbine blade base 130. Although one length of the arm 206 is shown, the arm 206 may be selected from a set of arms of different lengths that may be provided as part of the apparatus 200 for use with any radial length of the turbine blade 114 and / or a variety of different stages of a given turbine 108. Alternatively, as shown in FIG. 6, the vertically extending arm 206 may be adjustable in length. It can be length adjustable using any solution, for example, by changing the vertical position relative to the actuator 210 using coupling members 258 and / or plate couplers 260 (e.g., bolts, screws, etc.) that couple the arms to the coupling members 258 (see adjustment slots 262). Although slots 262 are shown, any form of selectable opening(s) can be used. The manipulating head 202 can include any structure that engages the axial sidewall 204, for example, at the end of the arm 206 adjacent the axial sidewall 204. That is, the manipulating head 202 can be provided in the form of any now known or later developed device for applying axial forces, and possibly vibratory vibrations, to a component mechanically engaged therewith. The manipulating head 202 can be embodied, for example, as one or more vibrating hammers, plates, cylinders, rollers, etc. In one embodiment, the operating head 202 may include an engagement element 208 ( FIG. 6 ) configured to engage the axial sidewall 204 of the turbine blade base 130 and slide along the axial sidewall 204 of the turbine blade base 130 while the rotor rotates.

[0030] The manipulation head 202 can also include a vibratory assembly 212 including a vibratory drive mechanism 214 coupled to the arm 206. In some embodiments, the vibratory drive mechanism 214 can include a pneumatic motor configured to generate mechanical vibrations and / or other forms of motion, for example, using compressed air supplied to the vibratory assembly 212 via a fluid source. The vibratory drive mechanism 214 can alternatively include or be embodied as an electric motor, a combustion engine, and / or other now known or later developed device for generating mechanical work, for example, coupled with an eccentric weight vibrator system. The vibratory assembly 212 can be adjustably coupled to and / or positioned directly on the arm 206 using any currently known solution, for example, fasteners, welding, etc. The vibratory assembly 212 can be adjustably attached to the arm 206 such that it can be positioned anywhere along the length of the arm 206.

[0031] The apparatus 200 also includes a support gantry 216 configured to position the actuator 210 substantially vertically above the turbine blade 114 while the turbine blade 114 is in place within the turbine 108 of the turbomachine 90. As used herein, "substantially vertical" refers to ±10° from vertical. The support gantry 216 may include any now known or later developed bridge-like overhead structure having a platform that supports the actuator 210 and sufficient strength to withstand the motive forces applied thereto. The support gantry 216 may be attached to any fixed structure 140. In certain embodiments, the support gantry 216 may be attached to a portion of the turbomachine 90 in which the turbine blade 114 is disposed. As shown in FIG. 4, the outer shell, upper half-joint casing (not shown) may be removed to leave the outer shell, lower half-joint casing 150. Here, the turbine 108, including the turbine blades 114, is in position for operation of the turbine 108, except for removing the outer shell, the upper half joint casing. The portion of the turbomachine 90 to which the support gantry 216 is attached may include, for example, a stationary structure 140 adjacent to and / or on which the turbine 108 is disposed, such as the lower half joint casing 150. In the illustrated example, the support gantry 216 is attached to opposing sides 232, 234 of the lower half joint casing 150 on which the turbine 108 is disposed, and to an exhaust hood 142 adjacent to the turbine 108. It is emphasized that while the support gantry 216 is shown attached in a particular manner in the drawings, it may be attached to any of a variety of alternative stationary structures 140, such as the floor of the power plant, other casings, other structures adjacent to the turbine 108, cranes within the power plant, among many other options.Any mounting mechanism 236 capable of fixedly attaching the support gantry 216 to the fixed structure 140 may be used, such as, for example, bolted or clamped mounting plates.

[0032] As shown, in certain embodiments, the support gantry 216 can include a number of adjustable support members 230 configured to accommodate a number of different turbines 108, i.e., turbines of different sizes with blade stages of different outer radii and different distances than those shown. In the illustrated non-limiting example, the support members 230 can include scaffolding members similar to those used in construction applications. Any number of support members 230 can be used and can be coupled in any manner now known or later developed, such as clamps, fasteners, threaded couplings, etc. In any case, the support members 230 can position the actuator 210 at any lateral position above the turbine 108 and at any axial position along the axis A of the turbine 108. For purposes described herein, in certain embodiments, at least one support member 238 extends axially, i.e., parallel to the axis A of the turbine 108.

[0033] To achieve movement of the manipulation head 202, the apparatus 200 may include an actuator 210 mechanically coupled to the manipulation head 202, i.e., the arm 206, such that actuation of the actuator 210 moves the manipulation head 202 and the arm 206 relative to the turbine blade base 130. More specifically, the actuator 210 is configured to move the manipulation head 202 to selectively engage the axial sidewall 204 of the turbine blade base 130 and apply an axial force F to the turbine blade base 130 to remove or install the turbine blade 114. As best shown in FIGS. 5 and 6, the actuator 210 may include a mounting member 240 configured to couple to the support gantry 216. The mounting member 240 may include any structural member that may be coupled to the axially-extending support member 238 of the support gantry 216. In a particular embodiment, the mounting member 240 takes the form of a plate, although other forms are possible. The mount member 240 may include any number of couplers 242 in the form of, for example, pipe clamps or other forms of couplers appropriate for the shape and dimensions of the axially extending support member 238. The couplers 242 may extend outwardly from the mount member 240 to engage one or more portions of the axially extending support member 238. The couplers 242 may be selectively fastened and unfastened to remove the actuator 210 from the support gantry 216 or to allow movement of the actuator 210 relative to the support gantry 216. More specifically, the couplers 242 may be selectively fastened and unfastened to allow the actuator 210 to be moved axially relative to the underlying turbine blade 114, for example along the axially extending support member 238, to allow a desired axial positioning of the manipulation head 202.In this manner, the apparatus 200 can be used to remove or install turbine blades 114 on multiple stages of the turbine 108 without moving the support gantry 216 or other portions of the apparatus 200. The axially extending support members 238 can have any length necessary to allow movement of as many stages of the turbine 108 as desired with a single installation of the apparatus 200.

[0034] The actuator 210 also includes a slide system 250 configured to slide (axially) the manipulation head 202 relative to the mount member 240 and thus the turbine blade 114. The actuator 210 also includes a linear actuator 252 configured to selectively move the slide system 250 axially relative to the mount member 240 to apply an axial force F to the axial sidewall 204 of the turbine blade base 130. The slide system 250 may include one or more axial guides 254 to enable relative movement of the manipulation head 202 with the arm 206 relative to the mount member 240 in at least one direction, e.g., along a line T. The axial guides 254 may be embodied as slidable couplings, such as rails, raceways, slots, and / or may include alternative forms of structure that allow for unidirectional movement, such as gear bearings, rack-and-pinion assemblies, threaded housings, and / or other mechanical bearings. If the axial guides 254 are embodied as rails or other slidable bearings, each of the pair of slidable couplings 256 may be slidably connected to and / or attached to a respective axial guide 254. The slidable couplings 256 may take the form of trolleys, wheels, gears, and / or other sliding components or bearings designed to permit relative movement of one component with respect to the other, for example along the direction of arrow T. The coupling members 258 may be provided as an integral housing shaped to engage the outer shape of the arm 206 or may be coupled to one side of the arm 206.In this case, another coupling member 258 can be coupled to another surface of the arm 206, and a plate coupler 260 (e.g., bolts, screws, rivets, etc.) couples the two coupling members 258. As will be appreciated, a variety of alternative mechanisms for coupling the arm 206 to the slide system 250 may also be employed.

[0035] An operator can further control the position of the manipulation head 202 and the arm 206 relative to the mount member 240 using additional components contained within and / or operably connected to the actuator 210. For example, the linear actuator 252 can include any form of drive mechanism 253, e.g., in the form of a mechanical motor, electrical motor, pneumatic motor, etc., capable of generating and transmitting mechanical work to move the manipulation head 202 and the arm 206 across one or more axial guides 254. In the illustrated non-limiting example, the linear actuator 252 includes a worm gear 255 that interacts with a coupling member 258 to move the manipulation head 202 and the arm 206. The linear actuator 252 can be coupled to the mount member 240, e.g., via a bearing 266 shaped to receive a portion of the linear actuator 252 therein. The bearings 266 can be located at opposing ends of the mount member 240 to allow the worm gear 255 to rotate freely to move the slide system 250. The slide system 250, the worm gear 255 and / or the drive mechanism 252 can be coupled using a necessary adapter (not shown). Each bearing 266 can be attached to a portion of the mount member 240 by being mechanically fastened via conventional fasteners such as bolts, screws, rivets, etc.

[0036] In addition to axially positioning the actuator 210 on the axially extending support member 238 as described herein, the coupler 242 is also configured to selectively position the mount member 240 of the actuator 210 between two states. As shown in FIGS. 4 and 5, the first operating state is a state in which the mount member 240 is axially and pivotally fixed to the axially extending support member 238 of the support gantry 216. Here, the arm 206 extends substantially perpendicularly adjacent to a first stage 270 of a plurality of turbine blade stages (referring to a plurality of vacant rotor wheels 116). This state is an operating state of the apparatus 200 that can operate the actuator 210 to remove or install turbine blades 114 on a selected rotor wheel 116 for a selected blade stage. 7 shows another second adjustment state in which the coupler 242 is sufficiently released so that the arm 206 is positioned radially outward of any turbine blade 114 on the turbine 108 and the mount member 240 is pivotable relative to the axially extending support member 238 (see arrow B) so that it can move axially along the axially extending support member 238 of the support gantry 216. In the second state, the actuator 210 is movable along the axially extending support member 238 (see arrow C) to position against different second stages 272 of the plurality of turbine blades 114. Once in the new desired position, the actuator 210 can rotate back (see arrow D) so that the manipulating head 202 is in a position to apply an axial force F to the axial side wall 204 of the selected turbine blade base 130. In this way, the apparatus 200 can operate in multiple stages, even though the support gantry 216 does not move, making the removal or installation of turbine blades in multiple stages significantly faster and safer.

[0037] In operation, a method for installing or removing a turbine blade 114 from a turbine 108 of a turbine machine 90 can include mounting an apparatus 200 as described herein to a portion of the turbine machine 90. In one non-limiting example, the mounting includes mounting a support gantry 216 to opposing sides 232, 234 of a half joint casing 150 in which the turbine 108 is disposed, and to an exhaust hood 142 adjacent the turbine 108 of the turbomachine 90. The manipulation head 202 can be substantially axially aligned with the turbine blade base 130 of a selected blade 114. An actuator 210 can be used to move the manipulation head 202 to engage the manipulation head 202 of the apparatus 200 with the turbine blade base 130 (prior to actuating the turbine blade base). As shown in FIG. 8 , the method may further include mechanically actuating the turbine blade base 130 relative to the turbomachine 90 by applying an axial force F to the turbine blade base 130 via the manipulating head 202 such that the turbine blade base 130 is moved into or out of the rotor wheel 116 of the first stage of the turbine blade 114. That is, the manipulating head 202 urges the turbine blade 114 into or out of the rotor wheel 116 under actuation by the actuator 210 via the arm 206. In the case of installation, these actions may move the blade 114 axially toward the rotor wheel 116 such that the blade 114 is installed between two other blades 114. In the case of removal, the manipulating head 202 may contact and move the blade 114 axially to move the blade 114 out of position between two adjacent blades 114 and out of the rotor wheel 116. Both removal and installation processes can be employed when the blades need to be "fanned out", meaning that they need to be removed bit by bit, one at a time, while the rotor is spinning.Fan-out is necessary, for example, when skewed dovetail slots or interlocking tip shrouds do not allow a single blade to be removed or installed independently. Optionally, the vibration assembly 212 may be coupled to the manipulation head 202 of the machine, for example via an arm 206, and the turbine blade base 130 may be vibrated simultaneously with application of the axial force F. As shown in FIG. 8, the position of the manipulation head 202 and the arm 206 may be adjusted as the manipulation head 202 vibrates and as the mounting member 240 remains stationary relative to the lower half joint casing 150.

[0038] The method of installing and / or removing the blades 114 may be particularly useful for installing or removing the blades 114 including the shroud portion 134 configured to form an interlocking profile 136 ( FIG. 3 ) with circumferentially adjacent blades 114. As best shown in FIG. 8 , the use of the arm 206 in the apparatus 200 allows a user to substantially align the manipulation head 202 (with or without the vibrating assembly 212) with a stage of the turbine 108 regardless of the turbine's placement. As shown, the apparatus 200 may alternatively be used to install or remove blades 114 other than the last stage blades, for example, at locations axially positioned between the stages 270, 272. Thus, the apparatus 200 may be used in any location of the turbomachine 90 where the blades 114 are difficult to access with conventional installations or devices.

[0039] As shown in FIG. 7, when a different stage of turbine blades is to be removed or installed, the method can include a first rotation of rotating the actuator 210 to rotate the arm 206 (and the operating head 202) from a first operating position adjacent the rotor wheel 116 of the first stage of the turbine blades 114 (FIGS. 4-5) to a position radially outboard of any turbine blades 114 on the turbine 108. As also shown in FIG. 7, the actuator 210 can be moved axially along the axially extending support member 238 of the support gantry 216 to a non-operating position (FIG. 7) where the arm 206 is radially outboard and axially above a space 276 adjacent a different second stage 272 of the turbine blades 114 of the turbomachine 90. The different second stage 272 can be any stage accessible by the arm 206 and the actuator 210 via the axially extending support member 238. The actuator 210 can then reverse rotate again (arrow D in FIG. 7 ) to rotate the arm 206 from the non-actuated position to another actuated position (dashed line in FIG. 7 ) adjacent a different second stage 272 of the turbine blade 114. The mechanical actuation of the turbine blade base 130 relative to the turbomachine 90 by applying an axial force F to the turbine blade base 130 via the operating head 202 can then be repeated for any number of turbine blades 114 of the second stage 272, i.e., transferring the turbine blade base 130 into or out of the rotor wheel 116 of the turbine blade 114 of a different second stage 272.

[0040] The apparatus 200 may comprise one or more materials including, but not limited to, metals, plastics, ceramics, and / or other materials suitable for use in the field of turbomachinery installation or maintenance.

[0041] The embodiments of the present disclosure may provide several technical and commercial advantages, some of which are described herein by way of example. The embodiments of the fixtures and methods discussed herein may provide substantially uniform manufacturing and / or servicing of turbine blades, such as those used in turbomachines. The embodiments of the present disclosure may also be employed in processes and / or events that require at least partial disassembly of turbomachines and / or stages, such as during inspection of certain components (e.g., final stage blades of a gas turbine). Various embodiments described herein may be operable to install or remove blades in relatively inaccessible locations without requiring partial or total dismantling of adjacent components. The support gantry allows for a wide range of adjustments of the apparatus, for example, for different turbines having different angles and / or different mounting locations. The apparatus may also operate multiple stages of any turbine without unbolting the apparatus, saving time. Additionally, the apparatus is vertically oriented, requiring less axial force to move the turbine blade base, and supporting the blades from above makes installation or removal of the blades safer. The apparatus may be substantially completely remotely operated, for example, using now known or later developed remote operation systems, and it will be appreciated that embodiments of the present disclosure may provide advantages and features in other operational and / or maintenance contexts not specifically addressed herein.

[0042] The terms used herein are for the purpose of describing particular embodiments only and are not intended to limit the disclosure. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms unless the context clearly indicates otherwise. It will be further understood that as used herein, the terms "comprises" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0043] This written description uses examples, including the best mode, to enable any person skilled in the art to practice the disclosure, including making and using any devices or systems, and performing any methods incorporated herein. 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 that do not differ insubstantially from the literal language of the claims. [Explanation of symbols]

[0044] 90: turbomachine 100: gas turbine (GT) system 102: compressor 104: combustor 105: combustion region 106: fuel nozzle assembly 108: turbine 110: rotor 112: nozzle 114: rotating blades 115: stationary nozzle section 116: rotor wheel 120: radially outer endwall 122: radially inner endwall 124: casing 129: airfoil 130: turbine blade base 132: fluid 134: shroud section 136: mating profile 138: flow passage 140: fixed structure 142: exhaust hood 150: half joint casing 200: device 202: operating head 204: axial sidewall 206: arm 208: engaging element 210: actuator 212: vibration assembly 214: vibration drive mechanism 216: support gantry 230: Support member 232, 234: Opposing sides 236: Attachment mechanism 238: Axially extending support member 240: Mount member 242: Coupler 250: Slide system 252: Linear actuator 253: Drive mechanism 254: Axial guide 255: Worm gear 256: Slidable coupling 258: Coupling member 260: Plate coupler 262: Adjustment slot 266: Bearing 270: First stage 272: Different second stage 276: Space A: Axial direction C: Circumferential direction F: Axial force L0: First stage L1: Second stage L2: Third stage L3: Final stage N: Axial path R: Radial direction

Claims

1. 1. An apparatus for removing or installing turbine blades from a turbine of a turbomachine, the turbomachine including a casing in which the turbine is housed during operation and during use of the apparatus, the apparatus comprising: an operating head configured to engage an axial sidewall of the turbine blade base; an actuator configured to move the operating head to selectively engage and apply an axial force to an axial sidewall of the turbine blade base to remove or install the turbine blade; a support gantry configured to position the actuators substantially vertically above the turbine blades; wherein the support gantry is configured to be attached to a casing in which the turbine is disposed for removal or installation of turbine blades.

2. The apparatus of claim 1 , wherein the support gantry is attached to a portion of the turbomachine on which the turbine blades are disposed, the portion of the turbomachine including at least one of adjacent the turbine or a structure on which the turbine is disposed.

3. The apparatus of claim 2 , wherein the support gantries are mounted to opposing sides of a lower half joint casing in which the turbine is located and to an exhaust hood adjacent the turbine.

4. 1. An apparatus for removing or installing turbine blades from a turbine, the turbomachine including a casing in which the turbine is housed during operation and during use of the apparatus, the apparatus comprising: an operating head configured to engage an axial sidewall of the turbine blade base; an actuator configured to selectively engage an axial sidewall of the turbine blade base and apply an axial force to the turbine blade base to remove the turbine blade from the turbine or to install the turbine blade; a support gantry configured to position the actuators substantially vertically above the turbine blades, the support gantry configured to be mounted to a casing in which the turbine is located for removal or installation of the turbine blades; Including, The actuator further comprises: a mount member configured to couple to a support gantry; a slide system configured to slidably move the operating head relative to the mount member; a linear actuator configured to selectively move the slide system axially relative to the mount member to apply an axial force; Equipped with The operating head includes an arm operably coupled to the actuator, the actuator further including a coupler configured to selectively position the mounting member between the first condition and the second condition. In a first condition, the mount member is axially pivotally secured to an axially extending support of the support gantry, and the arm extends substantially perpendicularly adjacent to a first stage of the plurality of turbine blade stages; In a second condition, the mount member is pivotable relative to the axially extending support member to position the arm radially outward of the turbine blades on the turbine and axially movable along the axially extending support member of the support gantry; In a second condition, the actuator is movable along the axially extending support member for positioning relative to a different second stage of the plurality of turbine blades.

5. 1. An apparatus for removing or installing turbine blades from a turbine, the turbomachine including a casing in which the turbine is housed during operation and during use of the apparatus, the apparatus comprising: a manipulator head configured to engage an axial sidewall of the turbine blade base and including an arm; an actuator configured to selectively engage an axial sidewall of the turbine blade base and apply an axial force to the turbine blade base to remove or install the turbine blade; a support gantry configured to position the actuators substantially vertically above the turbine blades while the turbine is disposed within the casing; Including, The actuator further comprises: a mount member configured to couple to a support gantry; a coupler configured to selectively position the mounting member between a first condition and a second condition; Equipped with In a first condition, the mount member is axially pivotally secured to an axially extending support of the support gantry, and the arm extends substantially perpendicularly adjacent to a first stage of the plurality of turbine blade stages; In a second condition, the mount member is pivotable relative to the axially extending support member, the arm is positioned radially outward of the turbine blades on the turbine, and the arm is axially movable along the axially extending support member of the support gantry; In the second condition, the actuator is movable along the axially extending support member for positioning relative to a different second stage of the plurality of turbine blades.

6. The apparatus of claim 5 further comprising a vibration assembly including a vibration drive mechanism coupled to the arm.

7. The apparatus of claim 5 , wherein the support gantry includes a plurality of adjustable support members configured to accommodate a plurality of different turbines.

8. 6. The apparatus of claim 5, wherein the manipulation head includes a vertically extending arm operably coupled to the actuator, the vertically extending arm being selectable from a set of arms of a plurality of different lengths.

9. The actuator further comprises: a slide system configured to slidably move the operating head relative to the mount member; a linear actuator configured to selectively move the slide system axially relative to the mount member; The apparatus of claim 8 , comprising:

10. 6. The apparatus of claim 5, wherein the support gantry is attached to opposing sides of a half joint casing in which the turbine is located and to an exhaust hood adjacent the turbine.

11. 1. A method for removing or installing turbine blades from a turbine of a turbomachine, the method including a casing in which the turbomachine turbine is housed during at least one of the removal and installation while the turbine is in operation, the method comprising: mounting an apparatus to a portion of a turbomachine, the apparatus including an actuator head configured to engage an axial sidewall of a turbine blade base, an actuator configured to move the actuator head to selectively engage the axial sidewall of the turbine blade base and apply an axial force against the turbine blade base, and a support gantry configured to position the actuator and the actuator head substantially vertically above the turbine blade; mechanically actuating the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via the manipulation head such that the turbine blade base moves into or out of a rotor wheel of a first stage of the turbine blade; The method includes:

12. coupling a vibration assembly to an operating head of the device; vibrating the turbine blade base simultaneously with applying the axial force; The method of claim 11 , comprising:

13. The method of claim 11 further comprising the stage of moving the manipulation head into engagement with the turbine blade base prior to mechanically actuating the turbine blade base.

14. 1. A method for installing or removing a turbine blade from a turbine of a turbomachine, comprising: mounting an apparatus to a portion of a turbomachine, the apparatus including an actuator head configured to engage an axial sidewall of a turbine blade base, an actuator configured to move the actuator head to selectively engage the axial sidewall of the turbine blade base and apply an axial force against the turbine blade base, and a support gantry configured to position the actuator and the actuator head substantially vertically above the turbine blade; mechanically actuating the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via an actuation head including an arm extending from the actuator such that the turbine blade base moves into or out of a rotor wheel of a first stage of the turbine blade; performing a first rotation of the actuator to rotate the arm from a first operating position adjacent a rotor wheel of a first stage of the turbine blades to a position radially outboard of the turbine blades; moving the actuator axially along an axially extending support member of the support gantry to a non-operating position where the arm is radially outwardly and axially above a space adjacent another second stage of turbine blades of the turbomachine; performing a second rotation of the actuator to rotate the arm from the non-actuated position to a second actuated position adjacent a different second stage turbine blade; repeating mechanically actuating the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via the manipulating head such that the turbine blade base moves into or out of the rotor wheel of different second stage turbine blades; The method includes:

15. The method of claim 14 , wherein mounting includes mounting the support gantry to a plurality of opposing sides of a half joint casing in which the turbine is located and an exhaust hood adjacent the turbine within the turbomachine.

Images