Locking spacer assembly in a gas turbine engine

Abstract

A locking spacer assembly for filling a final spacer slot in a disk groove between adjacent rotating blade platforms of a gas turbine engine includes a first side piece having a first outer surface, a second side piece having a second outer surface, and a mid-piece disposed between and in contact with the first and second side pieces. The mid-piece includes a base and a head. The base has a dovetail shape that engages the first and second side pieces. The head is flush with the first and second outer surfaces. A fastener is partially disposed within the mid-piece and abuts a surface of the disk groove.

Description

[Background technology]

[0001] A gas turbine engine typically includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and stationary compressor vanes. The combustion section includes multiple combustors. The turbine section includes multiple stages of rotating turbine blades and stationary turbine vanes. The rotating compressor blades and the rotating turbine blades are arranged in rows axially spaced apart along a rotor disk and are circumferentially mounted about the periphery of the rotor disk. Summary of the Invention

[0002] In one aspect, a locking spacer assembly is configured to fill a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine. The locking spacer assembly includes a first side piece including a first outer surface, a second side piece including a second outer surface, and a mid-piece disposed between and in contact with the first and second side pieces. The mid-piece includes a base and a head. The base has a dovetail shape that engages the first and second side pieces in an assembled state. The head is flush with the first and second outer surfaces in the assembled state. A fastener is partially disposed within the mid-piece and contacts a surface of the disk groove. The fastener is operable to move the mid-piece, the first and second side pieces to the assembled state.

[0003] In one aspect, a locking spacer assembly is configured to fill a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine. The locking spacer assembly includes a first side piece including a first outer surface and a first recess formed inwardly from the first outer surface, a second side piece including a second outer surface and a second recess formed inwardly from the second outer surface, and a mid-piece including a base, a head, and an intermediate body between the base and the head. The mid-piece, the first side piece, and the second side piece are operable between a pre-assembled state in which the head is partially located in the first recess and the second recess and completely below the first outer surface and the second outer surface, and an assembled state in which the head is flush with the first outer surface and the second outer surface. A fastener is partially disposed in the mid-piece and is operable to move the mid-piece, the first side piece, and the second side piece between the pre-assembled state and the assembled state.

[0004] In one aspect, a method for installing a locking spacer assembly in a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine includes holding a mid-piece in contact with the first and second side pieces with a head of the mid-piece partially located within a first recess of the first side piece and a second recess of the second side piece to define a pre-assembled state of the locking spacer assembly, positioning the pre-assembled mid-piece, first side piece, and second side piece in the final spacer slot, moving the first and second side pieces away from the mid-piece, engaging a fastener with the mid-piece, rotating the fastener into abutment with a surface of the disk groove, further rotating the fastener to move the mid-piece away from the surface of the disk groove, and ceasing rotation of the fastener when the head of the mid-piece moves to a position flush with the first outer surface of the first side piece and the second outer surface of the second side piece. [Brief description of the drawings]

[0005] To easily identify the description of a particular element or act, the most significant digit or digits in a reference number refer to the number of the figure in which that element is first introduced. [Figure 1] 1 is a longitudinal cross-section of a gas turbine engine taken along a plane containing the longitudinal axis or central axis; [Diagram 2] FIG. 2 is a perspective view of a portion of a blade assembly showing a final spacer slot in the disk groove, the blade assembly being used in the gas turbine engine of FIG. 1; [Diagram 3] FIG. 3 is a perspective view of a locking spacer assembly filling the final spacer slot of FIG. 2; [Figure 4] 4 is a perspective view of a first side piece of the locking spacer assembly of FIG. 3; FIG. [Diagram 5] FIG. 4 is a perspective view of a second side piece of the locking spacer assembly of FIG. 3; [Figure 6] FIG. 4 is a perspective view of an intermediate piece of the locking spacer assembly of FIG. 3; [Figure 7] FIG. 4 is a perspective view of a fastener of the locking spacer assembly of FIG. 3; [Figure 8] 4 is a cross-sectional view of the final spacer slot of FIG. 2 illustrating the installation of the locking spacer assembly of FIG. 3 into the final spacer slot; [Figure 9] 2A is a cross-sectional view of the final spacer slot of FIG. 2, illustrating the next step in installing the locking spacer assembly of FIG. 3 into the final spacer slot; [Figure 10] 2A is a cross-sectional view of the final spacer slot of FIG. 2, illustrating a further step in installing the locking spacer assembly of FIG. 3 into the final spacer slot; [Figure 11] 4 is a cross-sectional view of the locking spacer assembly of FIG. 3 in an assembled state installed within the final spacer slot of FIG. 2; [Figure 12] 2. The method of assembly of the locking spacer assembly of FIG. 3 into the final spacer slot of FIG. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0006] Before describing each embodiment of the invention in detail, it is to be understood that the invention is not limited in scope to the details of construction and the arrangement of components described herein or illustrated in the drawings. The invention is capable of other embodiments and of being practiced or carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

[0007] Various technologies related to the system and method are described below with reference to the drawings, in which like reference numerals represent like elements throughout. The drawings detailed below and the various embodiments used to illustrate the principles of the disclosure herein are for illustrative purposes only and should not be construed as limiting the scope of the disclosure in any way. Those of ordinary skill in the art will appreciate that the principles of the disclosure may be implemented in any suitably arranged device. It goes without saying that the functions described as being performed by a particular system element may also be performed by multiple elements. Similarly, for example, one element may be configured to perform the functions described as being performed by multiple elements. The teachings including the numerous inventive ideas of the present application are described with reference to illustrative, non-limiting examples.

[0008] It is also to be understood that words and expressions used herein are to be interpreted broadly unless expressly limited in certain instances. For example, "including," "having," and "comprising," along with their derivatives, mean open-ended inclusion. The singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. Furthermore, as used herein, "and / or" refers to and / or any and all possible combinations of one or more of the associated listed items. "Or" includes the meaning "and / or" unless the context clearly indicates otherwise. "Associated with" and "associated therewith," along with their derivatives, can mean including, included in, interconnected with, containing, contained in, connected to, coupled to, in communication with, cooperate with, interleaved, juxtaposed, near, coupled to, having, having the property of, etc. Additionally, although multiple embodiments or configurations are described herein, any feature, method, step, component, etc. described with respect to one embodiment is equally applicable to other embodiments unless stated otherwise.

[0009] Also, although modifiers such as "first," "second," and "third" may be used herein to refer to various elements, information, functions, or acts, these elements, information, functions, or acts should not be limited by such modifiers. Rather, these numerical adjectives are used to distinguish different elements, information, functions, or acts from one another. For example, a first element, information, function, or act could also be referred to as a second element, information, function, or act, and similarly, a second element, information, function, or act could also be referred to as the first element, information, function, or act, without departing from the scope of the present disclosure.

[0010] In the description, "axial" or "axially" refers to a direction along the longitudinal axis of the gas turbine engine. "radial" or "radially" refers to a direction perpendicular to the longitudinal axis of the gas turbine engine. "downstream" or "aft" refers to a direction along the direction of flow. "upstream" or "forward" refers to a direction against the direction of flow.

[0011] Additionally, "adjacent to" can mean that an element is relatively close to, but not touching, another element, or that an element is in contact with another portion, unless the context clearly indicates otherwise. Additionally, "based on" shall mean "based at least in part on," unless otherwise specified. The terms "about" or "substantially" or similar are intended to cover variations in values ​​that are within normal industrial manufacturing tolerances for their dimensions. Where an industry standard is not available, a 20% variation is intended to fall within the meaning of these terms, unless otherwise specified.

[0012] 1 illustrates an example of a gas turbine engine 100 including a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes multiple compressor stages 114, each of which includes a set of stationary compressor vanes (or adjustable guide vanes) 116 and a set of rotating compressor blades 118. A rotor 134 supports the rotating compressor blades 118 for rotation about the central axis 112 during operation. In some configurations, a single unitary rotor 134 extends the entire length of the gas turbine engine 100 and is supported for rotation by bearings at both ends. In other configurations, the rotor 134 may be assembled from several separate spools that are assembled together or may include multiple disk sections that are assembled by one or more bolts.

[0013] The compressor section 102 is in flow communication with the intake section 108, allowing the gas turbine engine 100 to draw air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses the air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102 and other configurations and designs are possible.

[0014] In the depicted configuration, the combustion section 104 includes a plurality of individual combustors 120. Each of the combustors 120 is operable to mix compressed air from the compressor section 102 with a fuel flow and combust the air-fuel mixture to generate a flow of hot, high pressure combustion gases or exhaust gases 122. Of course, many other arrangements of the combustion section 104 are possible.

[0015] The turbine section 106 includes a number of turbine stages 124, each of which includes a number of stationary turbine vanes 126 and a number of rotating turbine blades 128. The turbine stages 124 are configured to receive exhaust gases 122 from the combustion section 104 at a turbine inlet 130 and expand the gases to convert heat and pressure energy into rotational or mechanical work. The turbine section 106 is connected to and drives the compressor section 102. In the case of a gas turbine engine 100 used to generate electricity or as a prime mover, the turbine section 106 is in turn connected to a generator, pump, or other device to be driven. As with the compressor section 102, other designs and configurations of the turbine section 106 are possible.

[0016] The exhaust section 110 is disposed downstream of the turbine section 106 and is configured to receive an expanded flow of exhaust gases 122 from a final turbine stage 124 within the turbine section 106. The exhaust section 110 is configured to efficiently channel the exhaust gases 122 exiting the turbine section 106 to ensure efficient operation of the turbine section 106. Many variations and design differences are possible for the exhaust section 110; thus, the illustrated exhaust section 110 is but one example among many.

[0017] A control system 132 is coupled to the gas turbine engine 100 and configured to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 132 is typically microprocessor-based and includes memory and data storage devices for collecting, analyzing, and storing data. Additionally, the control system 132 provides output data to various devices, including monitors, printers, indicators, etc., that allow a user to interface with the control system 132 to provide input or adjustments. In the example of a power generation system, a user inputs a power output set point and the control system 132 adjusts various control inputs to achieve that power output in an efficient manner.

[0018] The control system 132 may control various operating parameters including, by way of non-limiting example, variable inlet guide vane position, fuel flow and pressure, engine speed, valve position, generator load, and generator excitation. Of course, in other applications, there may be fewer or more controllable devices. The control system 132 also monitors various parameters to ensure that the gas turbine engine 100 is operating properly. Examples of monitored parameters include inlet air temperature, compressor discharge temperature and pressure, combustor discharge temperature, fuel flow, generator power, bearing temperature, etc. Most of these measurements are displayed to the user and are recorded for later review when such review is required.

[0019] FIG 2 illustrates a perspective view of a portion of a blade assembly 200. The blade assembly 200 may be used with the gas turbine engine 100 of FIG 1. The blade assembly 200 is arranged to define an axial direction A, a circumferential direction C, and a radial direction R, as illustrated in FIG 2. The blade assembly 200 includes a plurality of rotary compressor blades 118 mounted to a rotor disk 202. Each of the rotary compressor blades 118 includes a platform 204 and a root 206 that extends inwardly from the platform 204 in the radial direction R of the gas turbine engine 100. Although FIG 2 illustrates a plurality of rotary compressor blades 118, other configurations may be applied to any of the rotary blades, such as the rotary turbine blades 128.

[0020] The rotor disk 202 may be formed as part of the rotor 134 or may be a separate component attached to the rotor 134. The rotor disk 202 defines a disk groove 208 that engages with the roots 206 of the rotary compressor blades 118. The rotary compressor blades 118 are inserted into the disk groove 208 one at a time during assembly. The platforms 204 extend within the disk groove 208 along the axial direction A of the gas turbine engine 100. When all of the rotary compressor blades 118 are assembled within the disk groove 208, a final spacer slot 210 is defined within the disk groove 208 between the platform 204 of the first installed rotary compressor blade 118 and the platform 204 of the last installed rotary compressor blade 118.

[0021] 3 shows a perspective view of an assembled locking spacer assembly 300. The locking spacer assembly 300 is used to fill the final spacer slot 210 and lock (secure) the rotating compressor blades 118 in the circumferential direction C.

[0022] The locking spacer assembly 300 includes a first side piece 302, a second side piece 304, a middle piece 306 disposed between the first side piece 302 and the second side piece 304, and a fastener 308 disposed partially within the middle piece 306. The fastener 308 includes a thread such as a set screw. The first side piece 302 is located on the front side with respect to the axial direction A. The second side piece 304 is located on the rear side with respect to the axial direction A.

[0023] FIG. 4 shows a perspective view of the first side piece 302 of the locking spacer assembly 300. The first side piece 302 includes a first inner surface 402, a first outer surface 404, a first inner surface 406, a first outer surface 408, and a first body portion 410. The first inner surface 402 is substantially rectangular and is located at the radially innermost position of the first side piece 302 when the first side piece 302 is in the installed position. The first inner surface 402 is inclined obliquely with respect to the radial direction R. The first outer surface 404 is substantially rectangular and is located at the radially outermost position of the first side piece 302 when the first side piece 302 is in the installed position. The first inner surface 406 is substantially rectangular and is located axially inward when the first side piece 302 is in the installed position. The first outer surface 408 is generally C-shaped and is axially outwardly disposed when the first sidepiece 302 is in the installed position. The first body portion 410 is disposed between the first inner surface 402 and the first outer surface 404. Other orientations or shapes of the first inner surface 402, first outer surface 404, first inner surface 406, and first outer surface 408 are possible.

[0024] The first side piece 302 defines a first recess 412 in the first body portion 410. The first recess 412 is formed immediately below and inward from the first outer surface 404. The first recess 412 may be formed anywhere between the first outer surface 404 and the first inner surface 402. The first recess 412 extends recessed from the first inner surface 406 toward the first outer surface 408. The first recess 412 extends axially across the first body portion 410. The first recess 412 is formed radially closer to the first outer surface 404 than the first inner surface 402. The first recess 412 is generally rectangular. Other shapes of the first recess 412 are possible.

[0025] The first side piece 302 defines a first groove 414 extending from the first inner surface 402 toward the first outer surface 404. The first groove 414 is defined in the first body portion 410 inwardly of the first outer surface 404. The first groove 414 opens at the first inner surface 406. The first groove 414 is generally cylindrical. Other shapes for the first groove 414 are possible.

[0026] 5 illustrates a perspective view of the second side piece 304 of the locking spacer assembly 300. The second side piece 304 is substantially similar to the first side piece 302.

[0027] The second side piece 304 includes a second inner surface 502 at a radially innermost position, a second outer surface 504 at a radially outermost position, a second inner surface 506 at an axially inner side, a second outer surface 508 at an axially outer side, and a second body portion 510 disposed between the second inner surface 502 and the second outer surface 504. The second inner surface 502 is generally rectangular. The second inner surface 502 is inclined obliquely with respect to the radial direction R. The second outer surface 504 is generally rectangular. The second inner surface 506 is generally rectangular. The second outer surface 508 is generally C-shaped. Other orientations or shapes of the second inner surface 502, second outer surface 504, second inner surface 506, and second outer surface 508 are also possible.

[0028] The second side piece 304 defines a second recess 512 in the second body portion 510. The second recess 512 is formed inwardly from the second outer surface 504. The second recess 512 may be formed just inwardly below the second outer surface 504. The second recess 512 extends recessed from the second inner surface 506 toward the second outer surface 508. The second recess 512 extends across the second body portion 510. The second recess 512 is formed at a radial location closer to the second outer surface 504 than the second inner surface 502. The second recess 512 is generally rectangular. Other shapes of the second recess 512 are possible.

[0029] The second side piece 304 defines a second groove 514 extending from the second inner surface 502 toward the second outer surface 504. The second groove 514 is defined in the second body portion 510 inwardly of the second outer surface 504. The second groove 514 opens at the second inner surface 506. The second groove 514 is generally cylindrical. Other shapes for the second groove 514 are possible.

[0030] 6 shows a perspective view of the intermediate piece 306 of the locking spacer assembly 300. The intermediate piece 306 includes a base 602 at a radially innermost position, a head 604 at a radially outermost position, and an intermediate body 606 disposed between the base 602 and the head 604. The base 602 has a dovetail shape defined by a first surface 608 and a second surface 610 that are inclined obliquely with respect to the radial direction R. The first surface 608 and the second surface 610 extend downward in the radial direction R from two opposite positions of the intermediate body 606 in the axial direction A. The first surface 608 and the second surface 610 cooperate to define the dovetail shape. The head 604 is generally rectangular. Other orientations or shapes of the base 602 and the head 604 are possible.

[0031] The mid-piece 306 includes a strip plate 612 disposed between the base 602 and the head 604. The strip plate 612 is coupled to the mid-body 606 and extends from two opposite sides of the mid-body 606. The strip plate 612 is disposed between a first surface 608 and a second surface 610.

[0032] The mid-piece 306 defines a hollow interior 614 that extends through the base 602, the mid-body 606, and the head 604. The hollow interior 614 includes a threaded surface 1102, shown in Figure 11. The mid-body 606 is generally cylindrical, although other shapes are possible.

[0033] The midpiece 306 has two crimping recesses 616 defined in the head 604. The two crimping recesses 616 are located on two opposite sides of the edge of the hollow interior 614 that intersects with the head 604, although other locations and quantities are possible.

[0034] 7 shows a perspective view of the fastener 308 of the locking spacer assembly 300. The fastener 308 includes a fastener head 702 at a radially outermost position and a fastener body 704 extending from the fastener head 702. The fastener head 702 includes a number of recesses for engaging a fastener tool. The fastener body 704 is generally cylindrical. The fastener body 704 has a threaded portion 706 that corresponds to the threaded surface 1102 of the mid-piece 306 to allow for threaded engagement. The fastener body 704 may have several portions with different diameters. Other orientations or shapes of the fastener 308 are possible.

[0035] FIG. 8 shows a cross-sectional view of the final spacer slot 210 illustrating the process of installing the locking spacer assembly 300 into the final spacer slot 210. The disk groove 208 has a radially innermost surface 802, a first side 804, and a second side 806 opposite the first side 804. The arrangement of the first side piece 302, the second side piece 304, and the intermediate piece 306 in this process defines a pre-assembled state. In the pre-assembled state, the intermediate piece 306 is held between and in contact with the first side piece 302 and the second side piece 304. The head 604 of the intermediate piece 306 is partially disposed within the first recess 412 and the second recess 512 to hold the intermediate piece 306. The head 604 is completely below the first outer surface 404 and the second outer surface 504 in the pre-assembled state. The mid-body 606 is positioned in the first groove 414 of the first side piece 302 and the second groove 514 of the second side piece 304. The strip plate 612 of the mid-piece 306 is located between the first side piece 302 and the second side piece 304. The first side piece 302, the second side piece 304 and the mid-piece 306 in a pre-assembled state are positioned in the final spacer slot 210 of the disc groove 208 with the base 602 of the mid-piece 306 resting on the surface 802 of the disc groove 208.

[0036] 9 shows a cross-sectional view of the final spacer slot 210 and illustrates the next step of installing the locking spacer assembly 300 therein. In this step, the arrangement of the first side piece 302, the second side piece 304, and the intermediate piece 306 defines a first intermediate assembly state. In the first intermediate assembly state, the first side piece 302 is moved away from the intermediate piece 306 toward the first side 804 of the disc groove 208. The second side piece 304 is moved away from the intermediate piece 306 toward the second side 806 of the disc groove 208. The intermediate body 606 of the intermediate piece 306 is disposed between the first side piece 302 and the second side piece 304. The intermediate body 606 is partially out of the first groove 414 and the second groove 514. The head 604 is completely below the first outer surface 404 and the second outer surface 504. The first sidepiece 302 and the second sidepiece 304 are moved axially either simultaneously or one after the other.

[0037] 10 shows a cross-sectional view of the final spacer slot 210 illustrating a further step in installing the locking spacer assembly 300 therein. In this step, the arrangement of the first side piece 302, the second side piece 304, the mid-piece 306, and the fastener 308 defines a second mid-assembly state. In the second mid-assembly state, the fastener 308 is partially disposed within the mid-piece 306. The fastener 308 is located within the hollow interior 614 of the mid-piece 306. The fastener 308 is turned to threadably engage the threaded portion 706 with the threaded surface 1102 of the mid-piece 306 and bring an end of the fastener 308 into contact with the surface 802 of the disc groove 208. The fastener 308 is further rotated to move the mid-piece 306 away from the surface 802 of the disc groove 208. The first surface 608 and the second surface 610 of the middle piece 306 move into abutment with the first inner surface 402 of the first side piece 302 and the second inner surface 502 of the second side piece 304. The first side piece 302 and the second side piece 304 move in response to the movement of the middle piece 306. Rotation of the fastener 308 is stopped when the head 604 of the middle piece 306 moves to a position where it is flush with the first outer surface 404 and the second outer surface 504.

[0038] FIG. 11 shows a cross-sectional view of the locking spacer assembly 300 in an assembled state installed in the final spacer slot 210. In the assembled state, referring also to FIG. 3, the head 604 of the intermediate piece 306 is flush with the first outer surface 404 and the second outer surface 504 to define a flat flow passage. A first gap may exist between the first outer surface 404 and the head 604. A second gap may exist between the second outer surface 504 and the head 604. The intermediate body 606 of the intermediate piece 306 is disposed between the first side piece 302 and the second side piece 304. The intermediate body 606 is located partially out of the first groove 414 and the second groove 514. The first surface 608 of the intermediate piece 306 abuts the first inner surface 402. The second surface 610 of the base 602 abuts the second inner surface 502. The fastener 308 is partially located within the mid-piece 306. The fastener 308 contacts and rests against the surface 802 of the disk groove 208. At least a portion of the threaded portion 706 of the fastener 308 is in threaded engagement with the threaded surface 1102 of the mid-piece 306. The first side piece 302, the second side piece 304, and the mid-piece 306 are held in place in the final spacer slot 210 of the disk groove 208 by the fastener 308. The fastener 308 is secured to the mid-piece 306 by staking using the staking recess 616. The final spacer slot 210 of the disk groove 208 is filled by the locking spacer assembly 300. The rotary compressor blade 118 is locked into the disk groove 208.

[0039] FIG. 12 illustrates a method 1200 for installing the locking spacer assembly 300 shown in FIGS. 8-11 into the final spacer slot 210. In block (step) 1202, the middle piece 306 is held between and in contact with the first and second side pieces 302, 304 such that the head 604 of the middle piece 306 is partially within the first recess 412 of the first side piece 302 and the second recess 512 of the second side piece 304, thereby defining a pre-assembled state of the locking spacer assembly 300. In block (step) 1204, the pre-assembled middle piece 306, first side piece 302, and second side piece 304 are positioned into the final spacer slot 210. In block (step) 1206, the first and second side pieces 302, 304 are actuated away from the middle piece 306. At block (step) 1208, the fastener 308 is threaded into the mid-piece 306. At block (step) 1210, the fastener 308 is rotated into abutment with the surface 802 of the disc groove 208. At block (step) 1212, the fastener 308 is further rotated to move the mid-piece 306 away from the surface 802 of the disc groove 208. At block (step) 1214, the rotation of the fastener 308 is stopped when the head 604 of the mid-piece 306 moves to a position flush with the first outer surface 404 of the first side piece 302 and the second outer surface 504 of the second side piece 304.

[0040] Although embodiments of the present disclosure have been described in detail, it will be understood by those having ordinary skill in the art that various changes, substitutions, derivations, and improvements of the present disclosure may be made thereto without departing from the spirit and scope of the present disclosure in its broadest form.

[0041] Nothing in this application should be construed as suggesting that any particular element, step, act, or function is an essential element that must be included in the scope of a claim. The scope of patented subject matter is defined only by the scope of the allowed claims. Further, none of the claims herein are intended to use a means-plus-function claim format, except for the special phrase "means for" following a participle. [Explanation of symbols]

[0042] 100: Gas Turbine Engine 102: Compressor section 104: Combustion Section 106: Turbine section 108: Intake section 110: Exhaust section 112: Central axis 114: Compressor stage 116: Stationary compressor vane 118: Rotary compressor blades 120: Combustor 122: Exhaust gas (combustion gas) 124: Turbine stage 126: Stationary turbine vanes 128: Rotating turbine blades 130: Turbine inlet 132: Control Systems 134: Rota 200: Blade Assembly 202: Rotor disc 204: Platform 206: Route 208: Disc groove 210: Final spacer slot 300: Locking spacer assembly 302: First Side Piece 304: Second Side Piece 306: Intermediate piece 308: Zipper 402: First Interior 404: First exterior 406: First inner surface 408: First outer surface 410: First body section 412: First recess 414: First Groove 502: Second Inner Self 504: Second exterior 506: Second inner surface 508: Second outer surface 510: Second body section 512: Second recess 514: The Second Groove 602: Bass 604: Head 606: Intermediate fuselage 608: First Surface 610: Second Surface 612: Strip Plate 614: Hollow interior 616: Caulking recess 702: Fastener head 704: Fastener body 706: Screw part 802: Surface 804: First aspect 806: The Second Side 1102: Thread surface 1200: Assembly Instructions

Claims

1. 1. A locking spacer assembly configured to fill a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine, comprising: a first side piece including a first outer surface; a second side piece including a second outer surface; an intermediate piece disposed between the first side piece and the second side piece and in contact with the side pieces; a fastener disposed partially within the intermediate piece and contacting a surface of the disk groove; The present invention relates to a method for manufacturing a computer-implemented ... the intermediate piece includes a base and a head, the base having a dovetail shape that abuts the first side piece and the second side piece in an assembled state, the head being flush with the first outer surface and the second outer surface in the assembled state; the fastener is operable to move the intermediate piece, the first side piece, and the second side piece to the assembled state. Locking spacer assembly.

2. The locking spacer assembly of claim 1 , wherein the midpiece includes a mid-body disposed between the base and the head.

3. the midpiece defines a hollow interior extending through the base, the mid-body, and the head; the fastener is partially disposed within the hollow interior.

3. The locking spacer assembly of claim 2.

4. the base includes a first surface inclined relative to a radial direction and a second surface inclined relative to the radial direction; the first surface and the second surface cooperate to define the dovetail shape; The locking spacer assembly of claim 1 .

5. The first side piece includes a first inner surface inclined relative to a radial direction, the second side piece includes a second inner surface inclined relative to the radial direction; the first inner surface and the second inner surface abut against the base; The locking spacer assembly of claim 1 .

6. the first side piece includes a first groove extending from a first inner surface toward the first outer surface; the second side piece includes a second groove extending from a second inner surface toward the second outer surface; The intermediate body of the intermediate piece is disposed between the first groove and the second groove.

3. The locking spacer assembly of claim 2.

7. the first side piece defines a first recess formed inwardly from the first outer surface; The second side piece defines a second recess formed inwardly from the second outer surface. The locking spacer assembly of claim 1 .

8. The locking spacer assembly of claim 1 , wherein said intermediate piece includes a strip plate extending between said base and said head.

9. 1. A locking spacer assembly configured to fill a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine, comprising: a first side piece including a first outer surface and a first recess formed inwardly from the first outer surface; a second side piece including a second outer surface and a second recess formed inwardly from the second outer surface; a mid-piece including a base, a head, and a mid-body between the base and the head; a fastener disposed partially within the intermediate piece; The present invention relates to a method for manufacturing a computer-implemented ... the intermediate piece, the first side piece, and the second side piece are movable between a pre-assembled state in which the head is located partially within the first recess and the second recess and completely below the first outer surface and the second outer surface, and an assembled state in which the head is flush with the first outer surface and the second outer surface; the fastener is operable to move the intermediate piece, the first side piece, and the second side piece between the pre-assembled state and the assembled state. Locking spacer assembly.

10. the midpiece defines a hollow interior extending through the base, the mid-body, and the head; the fastener is partially disposed within the hollow interior.

10. The locking spacer assembly of claim 9.

11. 10. The locking spacer assembly of claim 9, wherein said base has a dovetail shape including a first surface inclined relative to a radial direction and a second surface inclined relative to said radial direction.

12. the first side piece includes a first inner surface inclined relative to the radial direction; the second side piece includes a second inner surface inclined relative to the radial direction; the first inner surface abuts the first surface in the assembled state; the second inner surface abuts the second surface in the assembled state; The locking spacer assembly of claim 11.

13. the first side piece includes a first groove extending from a first inner surface toward the first outer surface; the second side piece includes a second groove extending from a second inner surface toward the second outer surface; the mid-fuselage is disposed within the first groove and the second groove in the pre-assembled state; The locking spacer assembly of claim 11.

14. 10. The locking spacer assembly of claim 9, wherein the midpiece includes a strip plate that couples to the mid-body and extends between the base and the head.

15. The locking spacer assembly of claim 9 , wherein the fastener abuts a surface of the disk groove in the assembled state.

16. The locking spacer assembly of claim 9 , wherein said head of said mid-piece defines two crimping recesses.

17. 1. A method of installing a locking spacer assembly in a last spacer slot in a disk groove between adjacent rotating blade platforms in a gas turbine engine, comprising: holding the intermediate piece in contact with the first side piece and the second side piece with a head of the intermediate piece partially positioned within a first recess of the first side piece and within a second recess of the second side piece to define a pre-assembled state of the locking spacer assembly; placing the preassembled intermediate piece, the first side piece, and the second side piece into the final spacer slot; moving the first side piece and the second side piece away from the intermediate piece; engaging a fastener with the intermediate piece; rotating the fastener into abutment with a surface of the disc groove; further rotating the fastener to move the intermediate piece away from the surface of the disc groove; stopping rotation of the fastener when the head of the intermediate piece moves to a position where it is flush with a first outer surface of the first side piece and a second outer surface of the second side piece; The method includes:

18. 20. The method of claim 17, further comprising engaging the intermediate piece with the first side piece and the second side piece.

19. 20. The method of claim 17, further comprising moving the first sidepiece and the second sidepiece in response to movement of the intermediate piece.

20. The method of claim 17 further comprising crimping the fastener within the mid-piece at two crimping recesses defined in the head of the mid-piece.

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