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 generally relates to the removal of turbine blades in a turbomachine assembly, and more particularly, to an apparatus for removing or attaching a turbine blade from a turbine within a turbomachine.

Background Art

[0002] Turbomachinery turbine rotors are often machined from large forgings. The rotor wheels cut from these forgings typically have grooves for mounting the turbine blade bases. As the demand for increased turbine power and improved turbine performance continues to grow, turbomachinery is increasingly fitted with larger and more articulated turbine blades. Dynamic properties influencing the design of these downstream turbine blades include the various blade profiles and external shapes used in turbomachinery, which can affect the fluid velocity profile and other characteristics of the working fluid within the system. In addition to the blade profile, other characteristics such as the effective 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 impact system performance. Damping and blade fatigue are other properties that play a role in the mechanical design of the blade and its profile. These mechanical and dynamic response characteristics, as well as other properties, all influence the relationship between performance and the turbine blade's surface profile. As a result, the profiles of latter-stage turbine blades often include complex blade geometries designed to improve performance while minimizing losses under a wide range of operating conditions.

[0003] The application of complex blade geometries to turbine blades, particularly latter-stage turbine blades, presents specific challenges in assembling and disassembling 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 positioned around the outer circumference of the blades to confine the working fluid within a well-defined path and increase blade rigidity. These interlocking shrouds can hinder the direct assembly and disassembly of the blades mounted on the rotor wheel. Furthermore, the inner platforms of these blades and their dovetail slots are often angled relative to the axis of the turbine rotor wheel to which they are mounted, which can also hinder assembly onto the rotor wheel. In many cases, turbine blades must be removed one at a time. The working environment in which turbine blades are used can cause issues such as corrosion and thermal distortion, and significant force may be required to disassemble the blades.

[0004] One method of removing or installing turbine blades requires forcing the blades axially by applying force to other parts of the turbine, such as the adjacent rotor wheel. Applying force to adjacent structures can damage them. Another approach involves cantilevering a removal or installation device to a portion of the turbine's half-joint casing, i.e., at the 3 o'clock or 9 o'clock position relative to the turbine axis. This latter approach requires rotating the turbine to position each turbine blade at the 3 o'clock or 9 o'clock position, so that the turbine blades extend roughly horizontally from the rotor wheel in a cantilevered manner. As a result, the weight of the turbine blades works against the removal or installation of the turbine blades by applying torque to the dovetail connection at the base of the turbine blades, requiring a greater axial force to remove the turbine blades. Furthermore, supporting the turbine blades during removal and / or installation to prevent them from falling or rotating in a way that could damage the turbine blades, rotor wheel, half-joint casing, or other components of the turbine is extremely difficult. If the turbine blades are mounted in angled dovetail slots, i.e., dovetail slots opposite the turbine axis, the rotor must be rotated when inserting or removing the turbine blades, which is extremely difficult if the blades are generally horizontal. [Overview of the Initiative]

[0005] One aspect of the present disclosure provides a device for removing or installing a turbine blade from a turbine of a turbomachinery, the device comprising: an operative head configured to engage with an axial sidewall of a turbine blade base; an actuator configured to selectively engage with the axial sidewall of a turbine blade base and move the operative head to apply an axial force to the turbine blade base in order to remove or install a turbine blade; and a support gantry configured to position the actuator substantially vertically above the turbine blade in a position within the turbomachinery.

[0006] Another aspect of the present disclosure provides a device for removing or installing a turbine blade from a turbine. The device includes an operating head configured to engage with the axial side wall of a turbine blade base, the operating head including an arm, and an actuator configured to move the operating head to selectively engage with the axial side wall of a turbine blade base and to apply an axial force to the turbine blade base to remove a turbine blade from a turbine or install a turbine blade in a turbine. The actuator includes a support gantry configured to position the actuator substantially vertically above the turbine blades. The actuator further includes a mounting member configured to be coupled to the support gantry and a fastening member configured to selectively position the mounting member between a first state and a second state, in which the mounting member is pivotally fixed to an axially extending support portion of the support gantry, with an arm extending substantially perpendicularly adjacent to a first stage of a plurality of turbine blade stages; in the second state, the mounting member is pivotable with respect to an axially extending member, positioning the arm radially outward of any turbine blade on the turbine, and positioning the mounting member movably along the axially extending support portion of the support gantry. In the second state, the actuator is movable along the axially extending member to position it to different second stages of a plurality of turbine blades.

[0007] Another aspect of the present disclosure relates to a method for attaching or removing a turbine blade from a turbine of a turbomachinery. The method includes the step of attaching a device to a part of the turbomachinery. The device includes an operating head configured to engage with the axial side wall of a turbine blade base; an actuator configured to selectively engage with the axial side wall of a turbine blade base and move the operating 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 the step of mechanically acting the turbine blade base with respect to the turbomachinery by applying an axial force to the turbine blade base via the operating head so that the turbine blade base moves in or out of the rotor wheel of the first stage of the turbine blade.

[0008] These and other features of the Disclosure will be more readily apparent from the following detailed description of various aspects of the Disclosure, taken together with the accompanying drawings illustrating various embodiments of the Disclosure: [Brief explanation of the drawing]

[0009] [Figure 1] This is a schematic diagram of a conventional turbomachinery. [Figure 2] This is a cross-sectional view of multiple turbine blade stages of an exemplary turbomachinery. [Figure 3] This is a perspective view of a turbine blade connected to a rotor wheel, including an interlocking shroud interface. [Figure 4] This is a perspective view of a turbine blade removal and / or installation device according to an embodiment of the present disclosure. [Figure 5] This is an enlarged perspective view of a turbine blade removal and / or installation device according to an embodiment of the present disclosure. [Figure 6] This is an enlarged perspective view of the actuator for a turbine blade removal and / or installation device according to an embodiment of the present disclosure. [Figure 7] This is a perspective view of a device for removing and / or installing a turbine blade in an adjusted state, according to an embodiment of the present disclosure. [Figure 8] This is a perspective view of an apparatus for removing and / or installing a turbine blade in operation, according to an embodiment of the present disclosure.

[0010] Please note that the drawings in this disclosure are not necessarily to scale. The drawings are intended to depict only typical embodiments of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, similar numbers represent similar elements between drawings.

[0011] Firstly, in order to clearly describe the subject matter of this disclosure, it is necessary to select specific terminology when referring to and describing relevant mechanical components within turbomachinery. Wherever possible, common industry terminology will be used and adopted in a manner consistent with its general meaning. Unless otherwise specified, such terminology should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that certain components are often referred to using multiple different or overlapping terms. What is described as a single component in this specification may include and refer to a component consisting of multiple components in another context. Or, what is described as consisting of multiple components in this specification may be referred to as a single component elsewhere.

[0012] In addition, several descriptive terms may be used periodically in this specification, and it would be beneficial to define these terms at the beginning of this section. Unless otherwise noted, these terms and their definitions are as follows: As used herein, “downstream” and “upstream” are terms that indicate the direction of fluid flow, such as the working fluid through a turbine, the flow of air through a combustor, or the flow of coolant through one of the turbine components. The term “downstream” corresponds to the direction of fluid flow, while the term “upstream” refers to the direction opposite to the flow (i.e., the direction in which the flow originates). The terms “forward” and “rear” are not further specified and refer to direction, with “forward” referring to the front of the engine or the compressor end, and “rear” referring to the rear section of the turbomachinery.

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

[0014] The terms used herein are for the sole purpose of describing specific embodiments and are not intended to limit the disclosure. Where used herein, the singular forms “a,” “an,” and “the” are intended to include the plural form unless the context clearly indicates otherwise. Where used herein, the terms “comprises” and / or “comprising” identify the presence of a described feature, integer, step, operation, element, and / or component, 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 event or situation described thereafter may or may not occur, or the component or element described thereafter may or may not exist, and that the description includes both instances in which the event occurs or the component exists and instances in which it does not occur or does not exist.

[0015] When an element or layer is referred to as “being,” “engaged,” “connected,” or “joined” on another element or layer, it may be directly engaged, connected, or joined to the other element or layer, or there may be an intervening element or layer. In contrast, when an element is said to be “directly,” “directly engaged,” “directly connected,” or “directly joined” on another element or layer, there may be no intervening element or layer. 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 enumerated items relating to it.

[0016] As shown in these figures, axis "A" represents the axial orientation (along the axis of the rotor of the turbomachinery). As used herein, the terms "axial" and / or "axially" refer to the relative position / direction of an object along axis A that is substantially parallel (i.e., within ±3°) to the axis of rotation of the turbomachinery (in particular, its rotor section). As further used herein, the terms "radial" and / or "radially" refer to the relative position / direction of an object along axis (R) that is substantially perpendicular to axis A and intersects axis A at only one point. Often it is necessary to describe parts that are positioned at different radial positions with respect to a central axis. For example, if a first part is located closer to the axis than a second part, this specification states that the first part is "radially inward" or "inboard" than the second part. On the other hand, if a first component is located further from the axis than a second component, this specification may state that the first component is "radially outward" or "outboard" of the second component. Furthermore, the terms "circumferential direction" and / or "circumferential direction" refer to the relative position / direction of an object along a circumference (C) that surrounds axis A but does not intersect axis A at any point. In two-dimensional diagrams, the circumference C may be omitted for clarity.

[0017] The terms “transfer” or “axial transfer” refer to the process of moving components such as blades from one position to another (e.g., by sliding motion), such as into or out of a dovetail slot on a rotor wheel. Therefore, embodiments of the disclosure described herein can enable the mounting or removal of turbine blades within or from a turbine rotor wheel by moving one or more turbine blades. While the removal of turbine blades is more specifically illustrated in the drawings, it is understood that various embodiments described herein may enable the mounting and / or removal of turbine blades in a rotor wheel without altering the various components and / or process methodologies described herein. Embodiments of the disclosure also provide methods for mounting turbine blades using various devices and / or similar assemblies discussed herein.

[0018] Embodiments of this disclosure provide an apparatus and associated method for removing or installing turbine blades from a turbomachinery turbine. The apparatus may include an operating head configured to engage with the axial sidewall of the turbine blade base. The actuator is configured to move the operating head to selectively engage with the axial sidewall of the turbine blade base, thereby applying 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 different turbines with different angles and mounting positions. Furthermore, the apparatus allows for operation of multiple stages of the turbine without removing the apparatus, saving time. In addition, because the apparatus is positioned vertically, less axial force is required to move the turbine blade, and by supporting the blade from above, the installation or removal of the blade can be performed more safely. The apparatus is almost remotely operated, further enhancing safety.

[0019] Referring to the drawings, Figure 1 is a schematic diagram of an exemplary turbomachinery 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter referred to as "GT system 100"). The GT system 100 includes a compressor 102 and a combustor 104. The combustor 104 includes a combustion area 105 and a fuel nozzle assembly 106. The GT system 100 also includes a turbine 108 and a common compressor / turbine shaft 110 (hereinafter referred to as "rotor 110"). In one non-limiting embodiment, the GT system 100 is the 9HA.01 engine, which is commercially available from General Electric Company, Greenville, SC. ​​This disclosure is not limited to any particular GT system and can be adapted to 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 manufacturers. Furthermore, the teachings of this disclosure are not necessarily limited to GT systems but can be applied to other types of turbomachinery, such as steam turbines, jet engines, compressors, etc.

[0020] Figure 2 is a cross-sectional view of an exemplary portion of a turbine 108 with four stages L0-L3 that can be used with the GT system 100 of Figure 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 stage in the axial direction. Stage L2 is the third stage and is the next stage in the axial direction. Stage L3 is the fourth and final stage and is the largest (radially) stage. It should be understood that the four stages are shown as an example only, and each turbine may have more or fewer 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 part of the flow path through the turbine 108. Each set of rotating blades 114 is coupled to respective rotor wheels 116 that circumferentially couple them to the rotor 110. That is, the plurality of rotating blades 114 are mechanically coupled to each rotor wheel 116 with circumferential spacing therebetween. The static nozzle section 115 includes a plurality of stationary nozzles 112 circumferentially spaced around the rotor 110. Each nozzle 112 can include at least one endwall or platform 120, 122 connected to an airfoil 129. In the illustrated example, the nozzle 112 includes an outer radial endwall 120 and an inner radial endwall 122. The outer radial endwall 120 couples the nozzle 112 to the casing 124 of the turbine 108.

[0022] During operation, air flows through the compressor 102, and the compressed air is supplied to the combustor 104. Specifically, the compressed air is supplied to a fuel nozzle assembly 106, which is integrated with the combustor 104. The fuel nozzle assembly 106 is in flow communication with the combustion region 105. The fuel nozzle assembly 106 is also in flow communication with a fuel source (not shown in Figure 1), and supplies 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, where the thermal energy of the gas flow is converted into mechanical rotational energy. The turbine 108 is rotatably connected to a rotor 110 and drives the rotor 110. The compressor 102 is also rotatably connected to the rotor 110. In the illustrated embodiment, there are multiple combustors 104 and fuel nozzle assemblies 106. In the following description, unless otherwise specified, only one of each component will be described. 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 a generator, load compressor, and / or another turbine.

[0023] Looking at Figure 3, a selection of blades 114 are shown arranged in a row and mounted circumferentially adjacent to each other on a rotor wheel 116. The blades 114 can be designed to remain circumferentially engaged with each other during operation and under relatively high loads. An exemplary form of mechanical engagement between circumferentially adjacent blades 114 is shown in Figure 3, and embodiments of the present disclosure may be useful for mounting and removing blades 114 designed for this arrangement or similar arrangements. Each blade 114 can be mechanically coupled to and mounted on the rotor wheel 116 via a turbine blade base 130 which includes a dovetail slot shape designed to fit into and engage with complementary slots in the rotor wheel 116, for example. As shown in Figure 3, the blades 114 can extend from the turbine blade base 130 having varying profiles and / or contours to accommodate the flow of fluid 132 (Figure 2) or other fluids across each blade 114. The radial ends of the blades 114 may include shroud portions 134 in the form of substantially identical blocks or plates that engage with each other and are formed and / or attached to the tip of each blade 114. When each blade 114 is mounted to the rotor wheel 116, the engaging blocks or plates of each shroud portion 134 can form a substantially continuous tip shroud element, for example, a substantially continuous, annular body configured to guide the flow around the rotor 110 (Figure 1).

[0024] Referring to FIGS. 2 and 3 together, the shroud portion 134 of each blade 114 can include, for example, an interlocking profile 136 (shown only in FIG. 3) 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. Further, the blade 114 can be disposed directly between the turbine 108 of the turbomachine 90 and an adjacent flow path 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 can be designed to be mounted or removed substantially along the direction of the axial path N. The interlocking profile 136 can be advantageous during operation of the turbomachine 90, for example, by maintaining the relative positions of each blade 114 with respect to each other and the rotor wheel 116. However, the interlock shape 136 can potentially reduce the ability to directly install or remove one or more blades 114 from a position between two other blades 114 during manufacturing or servicing.

[0025] Embodiments of the present disclosure can mitigate these characteristics of the meshing profile 136 by, for example, applying an axial force to attach or detach the blade 114. In some embodiments, the attached or detached blade 114 may be further subjected to mechanical vibrations. Such vibrations can impart oscillating motion to the blade 114, for example, enabling axial movement of the blade 114 despite various impediments that may hinder movement, such as corrosion. Various embodiments for applying axial force and / or mechanical vibration to the blade(s) 114 are discussed herein. As described herein, embodiments of the present disclosure may include devices attached to the casing 124 of the turbomachinery 90, such as the exhaust hood 142 (Figure 4) (e.g., its panels or supports), the outer shell, the half-joint casing 150 (Figure 4), and / or other turbomachinery components that may have various structural features attached thereto. In contrast to the current approach, the device is located vertically and radially above the turbine blades.

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

[0027] For illustrative purposes, one or more blades 114 illustrated in the following drawings may include final stage (e.g., L3 (Figure 1)) blades of the turbomachinery 90, which may have the same or similar features as those shown in Figures 2-3 and described elsewhere herein. Final stage blades 114 may differ from other blades 114 of the turbomachinery 90, for example, by being located in a place where conventional vibrating assemblies and / or actuators for mounting and removing blades 114 are unavailable or impractical. However, as will be described herein, the apparatus 200 is advantageously adjustable to remove or mount blades 114 without moving them from multiple stages within the turbomachinery 90. Furthermore, the apparatus 200 can be configured to operate on blades of virtually any stage of any turbine 108. Embodiments of the apparatus 200, and other methods or embodiments of apparatus described herein, can be used to mount or remove one or more blades 114 while being mechanically coupled to one or more parts of the turbomachinery 90.

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

[0029] Referring to Figures 4 to 6, the apparatus 200 includes an operable head 202 configured to engage with the axial sidewall 204 (Figures 2, 5, and 6) of the turbine blade base 130. The operable head 202 is formed to apply an axial force F to the turbine blade base 130. The operable head 202 can be shaped and / or positioned to apply a mechanical force axially, i.e., substantially parallel to the axis of the turbomachine, while engaging with the axial sidewall 204 of the turbine blade base 130. The axial sidewall 204 can face upstream or downstream, depending on the space available for mounting or removing each blade 114 from the rotor wheel 116. In one embodiment, the operable head 202 includes an arm 206 which can extend vertically when operably coupled to an actuator 210; i.e., the arm is a vertically extending arm. The arm 206 can have any length necessary to properly position the operating head 202, i.e., the end of the arm 206, so as to engage with the axial side wall 204 of the turbine blade base 130. Although one length of the arm 206 is illustrated, the arm 206 may be selected from a set of arms of different lengths that may be provided as part of the apparatus 200 so that it can be used for any radial length of the turbine blade 114 and / or for various different stages of a given turbine 108. Alternatively, as shown in Figure 6, the vertically extending arm 206 may be length adjustable. It can be made length-adjustable using any solution by changing the vertical position relative to the actuator 210 using coupling member 258 and / or plate couplers 260 (e.g., bolts, screws, etc.) that connect the arm to coupling member 258 (see adjustment slot 262). Although slot 262 is shown, any form of selectable opening(s) may be used. The operating head 202 may include any structure that engages with the axial side wall 204, for example, at the end of the arm 206 adjacent to the axial side wall 204. That is, the operating head 202 may be used to impart axial force, and possibly vibration, to components that mechanically engage with it. 、 It can be provided in any form of device. The operating 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 engaging element 208 (Figure 6) configured to engage with the axial side wall 204 of the turbine blade base 130 and slide along the axial side wall 204 of the turbine blade base 130 while the rotor rotates.

[0030] The operating head 202 may also include a vibration assembly 212 which includes a vibration drive mechanism 214 coupled to the arm 206. In some embodiments, the vibration drive mechanism 214 may include a pneumatic motor configured to generate mechanical vibrations and / or other forms of motion using compressed air supplied to the vibration assembly 212, for example, via a fluid source. Alternatively, the vibration drive mechanism 214 may be coupled to an electric motor, a combustion engine, and / or, for example, an eccentric weight vibrator system, to generate mechanical work. ofThe device may include or be embodied as such. The vibration assembly 212 may be adjustably coupled to and / or mounted directly on the arm 206 using any currently known solution, e.g., fasteners, welding, etc. The vibration assembly 212 may be adjustably mounted to the arm 206 so 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 turbomachinery 90. As used herein, “substantially vertical” refers to ±10° from vertical. The support gantry 216 has a platform for supporting the actuator 210 and is strong enough to withstand the driving force applied thereto. 、 A bridge-like overhead structure may be included. The support gantry 216 can be attached to any fixed structure 140. In certain embodiments, the support gantry 216 can be attached to a portion of the turbomachinery 90 in which the turbine blades 114 are located. As shown in Figure 4, the outer shell, upper half-joint casing (not shown) can be removed, leaving the outer shell, lower half-joint casing 150. Here, the turbine 108, including the turbine blades 114, is located in the outer shell, upper side Except for removing the half-joint casing, the turbine 108 is in position for operation. The part of the turbomachinery 90 to which the support gantry 216 is attached is, for example, adjacent to the turbine 108 and / or the fixed structure 140 in which the turbine 108 is positioned, for example, below. sideA half-joint casing 150 may be included. In the illustrated example, the support gantry 216 is attached to the opposing sides 232, 234 of the lower half-joint casing 150 in which the turbine 108 is located, and to the exhaust hood 142 adjacent to the turbine 108. Although the support gantry 216 is shown mounted in a particular manner in the drawing, it is emphasized that it can be mounted to any various alternative fixed structures 140, such as the floor of the power plant, other casings, other structures adjacent to the turbine 108, cranes within the power plant, etc., among many other options. Any mounting mechanism 236 can be used to permanently attach the support gantry 216 to the fixed structure 140, such as bolted or clamped mounting plates.

[0032] As illustrated, in certain embodiments, the support gantry 216 may include a plurality of adjustable support members 230 configured to accommodate a plurality of different turbines 108, i.e., turbines of different sizes having different outer radii and different distances than those shown. In the non-limiting examples shown, the support members 230 may include scaffolding members similar to those used in construction applications. Any number of support members 230 can be used. 、 The support members 230 can be connected in any way, for example, by 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 the 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 enable movement of the operating head 202, the apparatus 200 may include an actuator 210 mechanically coupled to the operating head 202, i.e., the arm 206, so that the operation of the actuator 210 causes the operating head 202 and the arm 206 to move relative to the turbine blade base 130. More specifically, the actuator 210 is configured to move the operating head 202 to selectively engage with the axial side wall 204 of the turbine blade base 130, thereby applying an axial force F to the turbine blade base 130 to remove or install the turbine blade 114. As best shown in Figures 5 and 6, the actuator 210 may include a mounting member 240 configured to be coupled to a support gantry 216. The mounting member 240 may include any structural member that can be coupled to an axially-extending support member 238 of the support gantry 216. In certain embodiments, the mounting member 240 takes the form of a plate, but other forms are also possible. The mounting member 240 may include any number of couplers 242 in the form of, for example, pipe clamps or other forms of couplers appropriate to the shape and dimensions of the axially extending support member 238. The couplers 242 may extend outward from the mounting member 240 to engage with one or more portions of the axially extending support member 238. The couplers 242 may be selectively engaged and disengaged to detach the actuator 210 from the support gantry 216 or to allow relative movement of the actuator 210 with respect to the support gantry 216. More specifically, the couplers 242 may be selectively engaged and disengaged so that the actuator 210 can be moved axially relative to the turbine blade 114 below it, for example, along the axially extending support member 238, in order to enable a desired axial positioning of the operating head 202.In this way, the apparatus 200 can be used to remove or attach turbine blades 114 to multiple stages of the turbine 108 without moving the support gantry 216 or other parts of the apparatus 200. The axially extending support member 238 can have any length necessary to allow movement to any desired number of stages of the turbine 108 in a single installation of the apparatus 200.

[0034] The actuator 210 also includes a slide system 250 configured to slide the operating head 202 axially relative to the mounting member 240 and, consequently, 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 mounting member 240 in order to apply an axial force F to the axial side wall 204 of the turbine blade base 130. The slide system 250 may include one or more axial guides 254 to allow relative movement of the operating head 202, having an arm 206, in at least one direction relative to the mounting member 240, for example, along line T. The axial guide 254 can be embodied as slidable couplings such as rails, raceways, or slots, and / or may include alternative forms of structures that allow unidirectional movement, such as gear bearings, rack-and-pinion assemblies, threaded housings, and / or other mechanical bearings. If the axial guide 254 is embodied as rails or other slidable bearings, a pair of slidable couplings 256 can each be slidably connected to and / or mounted to their respective axial guides 254. The slidable coupling 256 may take the form of trolleys, wheels, gears, and / or other sliding components or bearings designed to allow relative movement of one component to another, for example, along the direction of arrow T. The coupling member 258 may be provided as a one-piece housing shaped to engage with the outer surface shape of the arm 206, or it may be coupled to one surface 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.) will connect the two coupling members 258. As recognized, various alternative mechanisms may also be employed for coupling the arm 206 to the slide system 250.

[0035] The operator can further control the positions of the operating head 202 and arm 206 relative to the mounting member 240 using additional components contained within and / or operably connected to the actuator 210. For example, the linear actuator 252 may include any form of drive mechanism 253, such as a mechanical motor, electrical motor, pneumatic motor, etc., which can generate and transmit the mechanical work to move the operating head 202 and 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 operating head 202 and arm 206. The linear actuator 252 may be coupled to the mounting member 240, for example, via a bearing 266 shaped to receive a portion of the linear actuator 252 therein. The bearings 266 can be positioned at opposing ends of the mounting member 240 to allow the worm gear 255 to rotate freely in order to move the slide system 250. The slide system 250, worm gear 255, and / or drive mechanism 252 can be coupled using necessary adapters (not shown). Each bearing 266 can be attached to a portion of the mounting member 240 by mechanical fastening via conventional fasteners such as bolts, screws, rivets, etc.

[0036] As described herein, in addition to axially positioning the actuator 210 on an axially extending support member 238, the coupler 242 is also configured to selectively position the mounting member 240 of the actuator 210 between two states. As shown in Figures 4 and 5, the first operating state is in which the mounting member 240 is fixed axially and rotatably to the axially extending support member 238 of the support gantry 216. Here, the arm 206 extends substantially perpendicularly and adjacent to the first stage 270 of a plurality of turbine blade stages (see a plurality of empty rotor wheels 116). This state is the operating state of the device 200 which can actuate the actuator 210 to remove or install turbine blades 114 on a selected rotor wheel 116 for a selected blade stage. Figure 7 shows another second adjustment state in which the coupler 242 is fully released so that the mounting member 240 is rotatable relative to the axially extending support member 238 (see arrow B), allowing the arm 206 to be positioned radially outward of any turbine blade 114 on the turbine 108 and the mounting member 240 to be axially movable 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 to position multiple turbine blades 114 for different second stages 272 (see arrow C). Once in a new desired position, the actuator 210 can rotate back so that the operating 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 (see arrow D). In this way, the device 200 can operate in multiple stages even though the support gantry 216 does not move, and turbine blade removal or installation can be performed significantly quickly and safely in many stages.

[0037] In operation, a method for attaching or detaching a turbine blade 114 from the turbine 108 of the turbine machine 90 may include attaching a device 200, as described herein, to a portion of the turbine machine 90. In one non-limiting example, the attachment includes attaching a support gantry 216 to opposing sides 232, 234 of a half-joint casing 150 in which the turbine 108 is positioned, and to an exhaust hood 142 adjacent to the turbine 108 of the turbomachinery 90. The operating head 202 can be substantially axially aligned with the turbine blade base 130 of the selected blade 114. An actuator 210 may be used to move the operating head 202 to engage the operating head 202 of the device 200 with the turbine blade base 130 (before acting on the turbine blade base). As shown in Figure 8, the method may further include mechanically acting 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 so that the turbine blade base 130 moves into or out of the rotor wheel 116 at the first stage of the turbine blade 114. That is, the operating head 202, under the operation of the actuator 210 via the arm 206, biases the turbine blade 114 into or out of the rotor wheel 116. In the case of installation, these movements can move the blade 114 axially toward the rotor wheel 116 so that the blade 114 is positioned between two other blades 114. In the case of removal, the operating head 202 can contact the blade 114 and move it axially so that the blade 114 is removed from its position between two adjacent blades 114 and away from the rotor wheel 116. Both the removal and installation processes can be employed when the blades need to be "fanned out," which means that the blades must be removed one by one while the rotor is rotating.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 operating head 202 of the apparatus, for example, via an arm 206, and the turbine blade base 130 may vibrate simultaneously with the application of an axial force F. As shown in Figure 8, the positions of the operating head 202 and the arm 206 change as the operating head 202 vibrates and the mounting member 240 moves downward. side It may be adjusted as it remains stationary relative to the half-joint casing 150.

[0038] The method for installing and / or removing the blades 114 may be particularly effective for installing or removing blades 114 including a shroud portion 134 configured to form a meshing profile 136 (Figure 3) with circumferentially adjacent blades 114. As best shown in Figure 8, the use of the arm 206 in the apparatus 200 allows the user to substantially align the operating head 202 (with or without the vibration assembly 212) with the stage of the turbine 108, regardless of the turbine arrangement. As illustrated, the apparatus 200 can alternatively be used to install or remove blades 114 other than the final stage blades, for example, in an axially positioned location between stages 270, 272. Thus, the apparatus 200 can be used in any location of the turbomachinery 90 where access to the blades 114 would be difficult with conventional installations or apparatus.

[0039] As shown in Figure 7, when different stages of the turbine blades are removed or installed, the method may include a first rotation in which the actuator 210 rotates the arm 206 (and operating head 202) from a first operating position (Figures 4-5) adjacent to the rotor wheel 116 of the first stage of the turbine blade 114 to a position radially outward of any turbine blade 114 on the turbine 108. As also shown in Figure 7, the actuator 210 may move axially along a support member 238 extending axially from the support gantry 216 to a non-operating position (Figure 7) radially outward and axially on the space 276 adjacent to a different second stage 272 of the turbine blade 114 of the turbomachinery 90. The different second stage 272 may be any stage accessible by the arm 206 and actuator 210 via the axially extending support member 238. Next, the actuator 210 can be reversed (arrow D in Figure 7) to rotate the arm 206 from a non-operating position to another operating position (dashed line in Figure 7) adjacent to a different second stage 272 of the turbine blade 114. The mechanical operation 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, that is, the turbine blade base 130 moves the turbine blades 114 of different second stages 272 into or out of the rotor wheel 116.

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

[0041] Embodiments of the present disclosure can provide several technical and commercial advantages, some of which are described herein by example. Embodiments of the fixtures and methods discussed herein can provide substantially uniform manufacturing and / or service of turbine blades, such as those used in turbomachinery. Embodiments of the present disclosure can also be employed in processes and / or events that require at least partial disassembly of turbomachinery and / or stages, such as during inspection of specific components (e.g., final stage blades of a gas turbine). Various embodiments described herein may be capable of operating to install or remove blades in relatively hard-to-reach locations without requiring partial or complete disassembly of adjacent components. The support gantry allows for a wide range of adjustments of the apparatus for different turbines having different angles and / or different mounting positions. The apparatus can also operate multiple stages of any turbine without unbolting the apparatus, saving time. Furthermore, because the apparatus is vertically positioned, less axial force is required to move the turbine blade base, and the mounting or removal of blades can be performed more safely by supporting the blades from above. The apparatus can be used, for example, in currently known remotely operated systems. of It can be used to operate almost entirely remotely. Furthermore, it is understood that embodiments of the present disclosure may offer advantages and features in the context of other operations and / or maintenance not specifically addressed herein.

[0042] The terms used herein are for the sole purpose of describing specific embodiments and are not intended to limit the disclosure. Where used herein, the singular forms "a," "an," and "the" are intended to include the plural form unless the context clearly indicates otherwise. Where used herein, the terms "comprises" and / or "comprising" identify the presence of the described 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.

[0043] This specification uses examples, including best-function embodiments, to enable those skilled in the art to implement the disclosure, including the manufacture and use of any device or system, and the execution of any method incorporated therein. The patentable scope of this disclosure is defined by the claims and may include other examples conceivable to those skilled in the art. Such other examples are intended to be included in the claims if they have structural elements not different from the language of the claims, or if they include equivalent structural elements not substantially different from the language of the claims. [Explanation of symbols]

[0044] 90: Turbocharger 100: Gas turbine (GT) system 102: Compressor 104: Combustor 105: Combustion region 106: Fuel nozzle assembly 108: Turbine 110: Rotor 112: Nozzle 114: Rotating blade 115: Stationary nozzle section 116: Rotor wheel 120: Radially outer end wall 122: Radially inner end wall 124: Casing 129: Aerofoil 130: Turbine blade base 132: Fluid 134: Shroud section 136: Meshing profile 138: Flow path 140: Fixed structure 142: Exhaust hood 150: Half-joint casing 200: Device 202: Operating head 204: Axial side wall 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: Mounting mechanism 238: Axial support member 240: Mounting 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 C: Circumferential F: Axial force L0: First stage L1: Second stage L2: Third stage L3: Final stage N: Axial path R: Radial

Claims

1. A device for removing or installing turbine blades from a turbomachinery turbine, wherein the turbomachinery includes an upper half-joint casing and a lower half-joint casing, and includes a casing in which the turbine is housed while the turbine is operating and while the device is in use, An operating head configured to engage with the axial side wall of the turbine blade base, An actuator configured to selectively engage with the axial side wall of the turbine blade base and move an operating head to apply axial force in order to remove or install a turbine blade, A support gantry configured to position the actuator substantially vertically above the turbine blades, A device comprising a support gantry, the turbine being positioned for removal or installation of turbine blades, and the upper half-joint casing being attached to the removed casing.

2. The apparatus according to claim 1, wherein the support gantry is attached to a part of the turbomachinery on which the turbine blades are arranged, and the part of the turbomachinery is adjacent to the turbine or includes at least one of the structures on which the turbine is arranged.

3. The apparatus according to claim 2, wherein the support gantry is attached to opposing sides of the lower half-joint casing in which the turbine is located and to an exhaust hood adjacent to the turbine.

4. A device for removing or installing turbine blades from a turbine, wherein the turbomachinery includes an upper half-joint casing and a lower half-joint casing, and the device includes a casing in which the turbine is housed while the turbine is operating and while the device is in use, An operating head configured to engage with the axial side wall of the turbine blade base, An actuator configured to selectively engage with the axial side wall of a turbine blade base and apply an axial force to the turbine blade base in order to remove a turbine blade from the turbine or to install a turbine blade, A support gantry configured to position an actuator substantially vertically above the turbine blades, wherein the turbine is positioned for removal or installation of the turbine blades, and the support gantry is configured to be attached to the casing from which the upper half-joint casing has been removed, Includes, The actuator further, A mounting member configured to be connected to a support gantry, A sliding system configured to allow the operating head to slide relative to the mounting member, A linear actuator configured to selectively move a slide system axially relative to a mounting member in order to apply an axial force, Equipped with, The operating head includes an arm operably coupled to an actuator, and the actuator further includes a coupler configured to selectively position a mounting member between a first state and a second state. In the first state, the mounting member is fixed to a support portion extending axially from the support gantry so as to be pivotable in the axial direction, and the arm extends substantially perpendicularly and adjacent to the first stage of a plurality of turbine blade stages. In the second state, the mounting member is pivotable with respect to a support member extending in the axial direction, the arm is positioned radially outward from the turbine blades on the turbine, and is movable in the axial direction along the support member extending in the axial direction of the support gantry. In a second state, the actuator is movable along an axially extending support member to position it relative to different second stages of a plurality of turbine blades.

5. A device for removing or installing turbine blades from a turbine, wherein the turbomachinery includes an upper half-joint casing and a lower half-joint casing, and includes a casing in which the turbine is housed while the turbine is operating and while the device is in use, The operating head, which includes an arm, is configured to engage with the axial side wall of the turbine blade base. An actuator configured to selectively engage with the axial side wall of the turbine blade base and apply an axial force to the turbine blade base in order to remove or install the turbine blade, With the upper half-joint casing removed and the turbine positioned within the casing, a support gantry is configured to position the actuator substantially vertically above the turbine blades, Includes, The actuator further, A mounting member configured to be connected to a support gantry, A coupler configured to selectively position a mounting member between a first state and a second state, Equipped with, In the first state, the mounting member is fixed to a support portion extending axially from the support gantry so as to be pivotable in the axial direction, and the arm extends substantially perpendicularly adjacent to the first stage of a plurality of turbine blade stages. In the second state, the mounting member is pivotable with respect to a support member extending in the axial direction, the arm is located radially outward of the turbine blades on the turbine, and the arm is movable in the axial direction along the support member extending in the axial direction of the support gantry. In a second state, the actuator is movable along an axially extending support member to position it relative to a different second stage of a plurality of turbine blades.

6. The apparatus according to claim 5, further comprising a vibration assembly including a vibration drive mechanism coupled to an arm.

7. The apparatus according to claim 5, wherein the operating head includes a vertically extending arm operably coupled to an actuator, the vertically extending arm being selectable from a set of arms of multiple different lengths.

8. The actuator further, A sliding system configured to allow the operating head to slide relative to the mounting member, A linear actuator configured to selectively move the slide system axially relative to the mounting member, The apparatus according to claim 7, including the following:

9. The apparatus according to claim 5, characterized in that the support gantry is attached to a plurality of opposing sides of the lower half-joint casing in which the turbine is located, and to an exhaust hood adjacent to the turbine.

10. A method for removing or installing turbine blades from a turbomachinery turbine, comprising an upper half-joint casing and a lower half-joint casing, and including a casing in which the turbomachinery turbine is housed during at least one of the removal or installation while the turbine is in operation, the method is A step of attaching the device to a part of a turbomachinery while the upper half-joint casing is removed, the device comprising: an operating head configured to engage with the axial side wall of a turbine blade base; an actuator configured to selectively engage with the axial side wall of a turbine blade base and move the operating head to apply an axial force to the turbine blade base; and a support gantry configured to position the actuator and the operating head substantially vertically above the turbine blades; The steps of mechanically acting the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via an operating head so that the turbine blade base moves in or out of the rotor wheel of the first stage of the turbine blade, A method that includes this.

11. The steps include coupling the vibration assembly to the operating head of the device, The steps include applying axial force and simultaneously vibrating the turbine blade base, The method according to claim 10, including the method described in claim 10.

12. The method according to claim 10, further comprising a stage for moving an operating head to engage with a turbine blade base before mechanically operating the turbine blade base.

13. A method for attaching or removing turbine blades from a turbomachinery turbine, A step of attaching an apparatus to a part of a turbomachinery when the upper half-joint casing of the turbomachinery has been removed, the apparatus comprising: an operating head configured to engage with the axial side wall of the turbine blade base; an actuator configured to selectively engage with the axial side wall of the turbine blade base and move the operating head to apply an axial force to the turbine blade base; and a support gantry configured to position the actuator and the operating head substantially vertically above the turbine blades, The steps of mechanically acting the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via an operating head including an arm extending from an actuator, so that the turbine blade base moves in or out of the rotor wheel of the first stage of the turbine blade, The steps include performing a first rotation of the actuator to rotate the arm from a first operating position adjacent to the rotor wheel of the first stage of the turbine blade to a position radially outward of the turbine blade, The steps include moving the actuator axially along a support member extending axially from the support gantry to a non-operating position where the arm is radially outward and axially on another second stage of the turbine blade of the turbomachine, The steps include performing a second rotation of the actuator so as to rotate the arm from a non-operating position to a second operating position adjacent to a different second-stage turbine blade, The process involves repeatedly mechanically acting the turbine blade base relative to the turbomachine by applying an axial force to the turbine blade base via an operating head so that the turbine blade base moves into or out of the rotor wheel of a different second stage turbine blade, A method that includes this.

14. The method according to claim 13, wherein the installation includes the step of attaching a support gantry to a plurality of opposing sides of the lower half-joint casing in which the turbine is located and to an exhaust hood adjacent to the turbine in the turbomachinery.

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