Locking spacer assembly and method for installing locking spacer assembly
By designing a locking space assembly for gas turbine engines, the problem of difficulty in locking the space slot between rotary blades is solved, and the stability of the blade and engine performance are improved.
Patent Information
- Application Number
- CN202380032089.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2022-04-08
- Filing Date
- 2023-03-08
- Publication Date
- 2025-03-21
AI Technical Summary
Existing gas turbine engines are difficult to effectively lock and fill in the spacer grooves between rotating blades, resulting in unstable blades and affecting the engine's operating performance.
A locking spacer assembly is designed, including a first side member, a second side member and an intermediate member, which moves the intermediate member, the first side member and the second side member between the pre-assembled arrangement and the assembly arrangement to fill the final spacer groove in the disc groove by the operation of the fastener.
The spacer grooves between rotating blades are effectively locked, improving the stability of the blades and the running performance of the engine, and ensuring the correct installation and tightening of the blade components.
Smart Images
Figure CN119677935A_ABST
Abstract
Description
Background Art
[0001] A gas turbine engine generally includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and fixed compressor guide vanes. The combustion section includes multiple combustors. The turbine section includes multiple stages of rotating turbine blades and fixed turbine guide vanes. The rotating compressor blades and the rotating turbine blades are arranged in multiple rows spaced axially along a rotor disk and circumferentially attached to the periphery of the rotor disk. Summary of the invention
[0002] In one aspect, a locking spacer assembly is configured to fill a final spacing slot between platforms of adjacent rotating blades in a disk groove of a gas turbine engine. The locking spacer assembly includes: a first side member, the first side member includes a first outer surface; a second side member, the second side member includes a second outer surface; an intermediate member, the intermediate member is disposed between and in contact with the first side member and the second side member. The intermediate member includes a base and a head. The base has a dovetail shape, and in an assembled arrangement, the dovetail shape engages with the first side member and the second side member. In the assembled arrangement, the head is flush with the first outer surface and the second outer surface. A fastener is partially disposed in the intermediate member and contacts the surface of the disk groove. The fastener is operable to move the intermediate member, the first side member, and the second side member into the assembled arrangement.
[0003] In one aspect, a locking spacer assembly is configured to fill a final spacing slot between platforms of adjacent rotating blades in a disk groove of a gas turbine engine. The locking spacer assembly includes: a first side member, the first side member includes a first outer surface and a first recess formed on the inner side of the first outer surface; a second side member, the second side member includes a second outer surface and a second recess formed on the inner side of the second outer surface; an intermediate member, the intermediate member includes a base, a head, and an intermediate body located between the base and the head. The intermediate member, the first side member, and the second side member are movable between a pre-assembled arrangement and an assembled arrangement, in which the head is partially disposed in the first recess and the second recess and completely below the first outer surface and the second outer surface, and in which the head is flush with the first outer surface and the second outer surface. A fastener is partially disposed in the intermediate member and is operable to move the intermediate member, the first side member, and the second side member between the pre-assembled arrangement and the assembled arrangement.
[0004] In one aspect, a method installs a locking spacer assembly into a final spacing slot between platforms of adjacent rotating blades in a disk groove of a gas turbine engine. The method includes: holding an intermediate component between and in contact with a first side component and a second side component by partially positioning a head of the intermediate component in a first recess of the first side component and a second recess of the second side component, thereby defining a pre-assembled arrangement of the locking spacer assembly; placing the intermediate component, the first side component, and the second side component in the pre-assembled arrangement in the final spacing slot; moving the first side component and the second side component away from the intermediate component; engaging a fastener with the intermediate component; rotating the fastener to engage with a surface of the disk groove; further rotating the fastener to move the intermediate component away from the surface of the disk groove; and stopping rotating the fastener when the head of the intermediate component moves to a position flush with a first outer surface of the first side component and a second outer surface of the second side component. BRIEF DESCRIPTION OF THE DRAWINGS
[0005] To easily identify the discussion of any particular element or act, the first one or more digits in a reference number refers to the figure number that first introduces the element.
[0006] Figure 1 is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or central axis.
[0007] Figure 2 is a perspective view of a portion of a blade assembly showing the final spacing slots of the disc grooves, the blade assembly and Figure 1 Used together with gas turbine engines in.
[0008] Figure 3 Is used for filling Figure 2 Perspective view of the locked spacer assembly with the final spacer slot in place.
[0009] Figure 4 yes Figure 3 A perspective view of a first side member of a locking spacer assembly in FIG.
[0010] Figure 5 yes Figure 3 A perspective view of a second side member of a locking spacer assembly in FIG.
[0011] Figure 6 yes Figure 3 A perspective view of the intermediate component of the locking spacer assembly in FIG.
[0012] Figure 7 yes Figure 3 A perspective view of a fastener of a locking spacer assembly in FIG.
[0013] Figure 8 yes Figure 2 A cross-sectional view of the final spacing slot in the Figure 3 Steps for installing the locking spacer assembly into the final spacer slot.
[0014] Fig. 9 yes Figure 2 A cross-sectional view of the final spacing slot in the Figure 3 Another step to install the locking spacer assembly in the final spacer slot.
[0015] Fig.10 yes Figure 2 A cross-sectional view of the final spacing slot in the Figure 3 Another step in installing the locking spacer assembly in the final spacer groove.
[0016] Fig.11 yes Figure 3 The locking spacer components in the assembly are installed in an assembled arrangement Figure 2 Cross-sectional view of the final spacing slot in .
[0017] Fig.12 Yes Figure 3 The locking spacer assembly in the Figure 2 The final assembly method in the spacing groove. DETAILED DESCRIPTION
[0018] Before explaining any embodiment of the present invention in detail, it should be understood that the application of the present invention is not limited to the details of the construction and arrangement of the components set forth in this specification or shown in the following drawings. The present invention can have other embodiments and can be practiced or implemented in various ways. Moreover, it should be understood that the words and terms used herein are for descriptive purposes and should not be considered as limiting.
[0019] Various techniques related to systems and methods will now be described with reference to the accompanying drawings, wherein the same reference numerals represent the same elements throughout the text. The accompanying drawings discussed below and the various embodiments for describing the principles of the present invention in this patent document are intended to be illustrative only and should not be interpreted as limiting the scope of the present invention in any way. It will be appreciated by those skilled in the art that the principles of the present invention can be implemented in any suitably arranged device. It should be understood that the functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, an element can be configured to perform the functions described as being performed by multiple elements. Multiple innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.
[0020] Moreover, it should be understood that the words or phrases used in the present invention should be interpreted broadly, unless explicitly limited in some examples. For example, the terms "include", "have" and "include" and their derivatives are meant to include without limitation. The singular forms "one", "an" and "the" are also intended to include plural forms, unless the context clearly indicates otherwise. In addition, the term "and / or" used in the present invention refers to and covers any and all possible combinations of one or more items in the relevant listed items. The term "or" is inclusive, meaning "and / or", unless the context clearly indicates otherwise. The phrases "associated with..." and "associated with it" and their derivatives may mean including, included, interconnected with..., including, included, connected to... or connected with..., connected to... or connected with..., communicated with..., collaborated with..., interlaced, juxtaposed, close to, bound to or bound with..., have, have... characteristics, etc. In addition, although the present invention can describe multiple embodiments or configurations, any features, methods, steps, components, etc. described with reference to one embodiment are equally applicable to other embodiments without specific statements to the contrary.
[0021] In addition, although the present invention can use the terms "first", "second", "third" etc. to refer to various elements, information, functions or actions, these elements, information, functions or actions should not be limited by these terms. On the contrary, these digital adjectives are used to distinguish between different elements, information, functions or actions. For example, the first element, information, function or action can be referred to as the second element, information, function or action, and similarly, the second element, information, function or action can be referred to as the first element, information, function or action, without departing from the scope of the present invention.
[0022] In addition, in the specification, the term "axial" or "axially" refers to a direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to a direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to a direction along the flow direction. The term "upstream" or "forward" refers to a direction opposite to the flow direction.
[0023] In addition, the term "adjacent" may refer to an element being relatively close to another element but not in contact with the other element, or the element being in contact with another part, unless the context clearly indicates otherwise. In addition, the phrase "based on" is intended to mean "based at least in part on," unless otherwise clearly indicated. The term "about" or "substantially" or similar terms are intended to encompass variations in values within normal industrial manufacturing tolerances for the dimensions described. If no industry standard is available, a variation of 20% will fall within the meaning of these terms unless otherwise indicated.
[0024] Figure 1An example of a gas turbine engine 100 is shown, which includes a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes a plurality of compressor stages 114, each compressor stage 114 including a set of fixed compressor guide vanes 116 or adjustable guide vanes 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 one-piece rotor 134 extends the length of the gas turbine engine 100 and is supported for rotation at either end by bearings. In other configurations, the rotor 134 is assembled from several separate tube shafts that are attached to each other, or may include multiple disk segments attached by one or more bolts.
[0025] The compressor section 102 is in fluid communication with the inlet section 108 to allow the gas turbine engine 100 to draw atmospheric 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 compressor section 102 shown is an example of one compressor section 102, and other arrangements and designs are possible.
[0026] In the illustrated configuration, the combustion section 104 includes a plurality of individual combustors 120, each of which operates to mix a fuel stream with compressed air from the compressor section 102 and combust the air-fuel mixture to produce a high temperature, high pressure combustion gas or exhaust stream 122. Of course, the combustion section 104 may be of many other arrangements.
[0027] The turbine section 106 includes a plurality of turbine stages 124, each turbine stage 124 including a plurality of fixed turbine guide vanes 126 and a plurality of rotating turbine blades 128. The turbine stage 124 is arranged to receive the exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand the gas to convert the heat energy and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, a pump, or other device to be driven. Like the compressor section 102, the turbine section 106 can also be of other designs and arrangements.
[0028] The exhaust section 110 is positioned downstream of the turbine section 106 and is arranged to receive an expanded exhaust gas flow 122 from a final turbine stage 124 in the turbine section 106. The exhaust section 110 is arranged to effectively direct the exhaust gas 122 away from the turbine section 106 to ensure efficient operation of the turbine section 106. There may be many variations and design differences in the exhaust section 110. As such, the exhaust section 110 shown is only one example of such variations.
[0029] The control system 132 is coupled to the gas turbine engine 100 and operates 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 devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 132 provides output data to various devices, including monitors, printers, indicators, etc., which allow users to interact with the control system 132 to provide input or adjustments. In the example of a power generation system, a user can input a power output setpoint, and the control system 132 can adjust various control inputs to achieve the power output in an efficient manner.
[0030] The control system 132 can control various operating parameters, including but not limited to variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure that the gas turbine engine 100 operates properly. Some of the parameters monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for later inspection if such inspection is necessary.
[0031] Figure 2 A perspective view of a portion of a blade assembly 200 is shown. The blade assembly 200 may be used with Figure 1 The blade assembly 200 is arranged to define an axial direction A, a circumferential direction C and a radial direction R, such as Figure 2 As shown. The blade assembly 200 includes a plurality of rotating compressor blades 118 attached to a rotor disk 202. Each rotating compressor blade 118 includes a platform 204 and a root 206 extending inwardly from the platform 204 in a radial direction R of the gas turbine engine 100. Figure 2 A plurality of rotating compressor blades 118 are shown, but other configurations may be applied to any rotating blades, such as rotating turbine blades 128 .
[0032] The rotor disk 202 may be formed as part of the rotor 134 or may be a separate part attached to the rotor 134. The rotor disk 202 defines a disk groove 208 for engaging the root 206 of the rotary compressor blade 118. The rotary compressor blades 118 are inserted into the disk groove 208 one at a time during the assembly process. The platform 204 extends in the axial direction A of the gas turbine engine 100 in the disk groove 208. Once all the rotary compressor blades 118 are assembled in the disk groove 208, a final spacing slot 210 is defined in 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.
[0033] Figure 3 A perspective view of the locking spacer assembly 300 in an assembled arrangement is shown. The locking spacer assembly 300 is used to fill the final spacer slot 210 and to lock the rotating compressor blades 118 in the circumferential direction C.
[0034] The locking spacer assembly 300 includes a first side member 302, a second side member 304, an intermediate member 306 disposed between the first side member 302 and the second side member 304, and a fastener 308 partially disposed in the intermediate member 306. The fastener 308 may include a screw, such as a set screw. The first side member 302 may be positioned at a front side relative to the axial direction A. The second side member 304 may be positioned at a rear side relative to the axial direction A.
[0035] Figure 4 A perspective view of the first side member 302 of the locking spacer assembly 300 is shown. The first side member 302 includes a first inner surface 402, a first outer surface 404, a first inner side surface 406, a first outer side surface 408, and a first body 410. The first inner surface 402 has a generally rectangular shape, and when the first side member 302 is in the installed position, the first inner surface 402 is located at the radially innermost position of the first side member 302. The first inner surface 402 is obliquely angled relative to the radial direction R. The first outer surface 404 has a generally rectangular shape, and when the first side member 302 is in the installed position, the first outer surface 404 is located at the radially outermost position of the first side member 302. The first inner side surface 406 has a generally rectangular shape, and when the first side member 302 is in the installed position, it is located axially inward. The first outer side surface 408 is generally C-shaped, and when the first side member 302 is in the installed position, the first outer side surface 408 is located axially outward. The first body 410 is disposed between the first inner surface 402 and the first outer surface 404. The first inner surface 402 , the first outer surface 404 , the first inner side surface 406 , and the first outer side surface 408 may also have other orientations or shapes.
[0036] The first side member 302 defines a first recess 412 in the first body 410. The first recess 412 is formed directly inside the first outer surface 404. The first recess 412 may also be formed at any position between the first outer surface 404 and the first inner surface 402. The first recess 412 extends inwardly from the first inner surface 406 toward the first outer surface 408. The first recess 412 extends axially across the first body 410. The first recess 412 is formed at a radial position closer to the first outer surface 404 than to the first inner surface 402. The first recess 412 has a generally rectangular shape. The first recess 412 may also be other shapes.
[0037] The first side member 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 410 and is located inside the first outer surface 404. The first groove 414 has an opening at the first inner surface 406. The first groove 414 has a generally cylindrical shape. The first groove 414 may also have other shapes.
[0038] Figure 5 A perspective view of the second side member 304 of the locking spacer assembly 300 is shown. The second side member 304 is substantially similar to the first side member 302.
[0039] The second side member 304 includes a second inner surface 502 located at the radially innermost position, a second outer surface 504 located at the radially outermost position, a second inner side surface 506 located at the axial inner side, a second outer side surface 508 located at the axial outer side, and a second body 510 disposed between the second inner surface 502 and the second outer surface 504. The second inner surface 502 has a generally rectangular shape. The second inner surface 502 is obliquely angled relative to the radial direction R. The second outer surface 504 has a generally rectangular shape. The second inner side surface 506 has a generally rectangular shape. The second outer side surface 508 is generally C-shaped. The second inner surface 502, the second outer surface 504, the second inner side surface 506, and the second outer side surface 508 may also be in other orientations or shapes.
[0040] The second side member 304 defines a second recess 512 in the second body 510. The second recess 512 is formed inboard of the second outer surface 504. The second recess 512 can be formed directly inboard of the second outer surface 504. The second outer surface 504 extends inwardly from the second inner surface 506 toward the second outer surface 508. The second outer surface 504 extends laterally across the second body 510. The second recess 512 is formed at a radial position closer to the second outer surface 504 than to the second inner surface 502. The second recess 512 has a generally rectangular shape. The second recess 512 can also be other shapes.
[0041] The second side member 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 510 and is located inside the second outer surface 504. The second groove 514 has an opening at the second inner surface 506. The second groove 514 has a generally cylindrical shape. The second groove 514 may also have other shapes.
[0042] Figure 6 A perspective view of the intermediate component 306 of the locking spacer assembly 300 is shown. The intermediate component 306 includes a base 602 located at a radially innermost position, a head 604 located 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, each of which is obliquely angled relative to a radial direction R. The first surface 608 and the second surface 610 extend from opposite sides of the intermediate body 606 in the axial direction A and extend downward in the radial direction R. The first surface 608 and the second surface 610 cooperate to define the dovetail shape. The head 604 has a generally rectangular shape. Other orientations or shapes of the base 602 and the head 604 are also possible.
[0043] The intermediate member 306 includes a strap 612 disposed between the base 602 and the head 604. The strap 612 is coupled to the intermediate body 606 and extends from opposite sides of the intermediate body 606. The strap 612 is disposed between the first surface 608 and the second surface 610.
[0044] The intermediate member 306 defines a hollow interior 614 that passes through the base 602, the intermediate body 606, and the head 604. The hollow interior 614 includes Fig.11 Threaded surface 1102 is shown. The intermediate body 606 has a generally cylindrical shape, although other shapes are possible.
[0045] The middle member 306 has two rivet indentations 616 defined on the head 604. The two rivet indentations 616 are disposed on opposite sides of the edge of the hollow interior 614 intersecting the head 604, but other locations and numbers are also possible.
[0046] Figure 7A perspective view of a fastener 308 of a locking spacer assembly 300 is shown. The fastener 308 includes a fastener head 702 located in a radially outermost position and a fastener body 704 extending from the fastener head 702. The fastener head 702 includes a plurality of indentations to be engaged with a fastener tool. The fastener body 704 has a generally cylindrical shape. The fastener body 704 has a threaded portion 706 that corresponds to the threaded surface 1102 of the intermediate component 306 to allow threaded engagement. The fastener body 704 can have several portions of different diameters. The fastener 308 can also be other orientations or shapes.
[0047] Figure 8 A cross-sectional view of the final spacing groove 210 is shown to illustrate the steps of installing the locking spacing assembly 300 into the final spacing groove 210. The disc groove 208 includes a surface 802 located at the radially innermost position, a first side surface 804, and a second side surface 806 opposite to the first side surface 804. In the steps, the arrangement of the first side member 302, the second side member 304, and the intermediate member 306 defines a pre-assembly arrangement. In the pre-assembly arrangement, the intermediate member 306 is held between and in contact with the first side member 302 and the second side member 304. The head 604 of the intermediate member 306 is partially disposed in the first recess 412 and the second recess 512 to hold the intermediate member 306. In the pre-assembly arrangement, the head 604 is completely located below the first outer surface 404 and the second outer surface 504. The intermediate body 606 is disposed in the first recess 414 of the first side member 302 and the second recess 514 of the second side member 304. The strap 612 of the middle member 306 is disposed between the first side member 302 and the second side member 304. The first side member 302, the second side member 304, and the middle member 306 in a pre-assembled arrangement are placed in the final spacing slot 210 of the disk recess 208, wherein the base 602 of the middle member 306 may rest on the surface 802 of the disk recess 208.
[0048] Fig. 9A cross-sectional view of the final spacing slot 210 is shown to illustrate a further step of installing the locking spacing assembly 300 into the final spacing slot 210. In the further step, the arrangement of the first side member 302, the second side member 304, and the intermediate member 306 defines a first transient assembly arrangement. In the first transient assembly arrangement, the first side member 302 moves away from the intermediate member 306 toward the first side surface 804 of the disk groove 208. The second side member 304 moves away from the intermediate member 306 toward the second side surface 806 of the disk groove 208. The intermediate body 606 of the intermediate member 306 is located between the first side member 302 and the second side member 304. The intermediate body 606 is partially positioned outside 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 side member 302 and the second side member 304 can be axially moved simultaneously or one after another.
[0049] Fig.10 A cross-sectional view of the final spacing slot 210 is shown, thereby showing another step of installing the locking spacing assembly 300 into the final spacing slot 210. In the further step, the arrangement of the first side member 302, the second side member 304, the intermediate member 306, and the fastener 308 defines a second transient assembly arrangement. In the second transient assembly arrangement, the fastener 308 is partially disposed within the intermediate member 306. The fastener 308 is placed in the hollow interior 614 of the intermediate member 306. The fastener 308 is rotated to engage the threaded portion 706 with the threaded surface 1102 of the intermediate member 306 and position one end of the fastener 308 in contact with the surface 802 of the disc groove 208. The fastener 308 is further rotated to move the intermediate member 306 away from the surface 802 of the disc groove 208. The first surface 608 and the second surface 610 of the intermediate member 306 are moved into engagement with the first inner surface 402 of the first side member 302 and the second inner surface 502 of the second side member 304. The first side member 302 and the second side member 304 move in response to the movement of the middle member 306. When the head 604 of the middle member 306 moves to a position where the head 604 is flush with the first outer surface 404 and the second outer surface 504, the rotation of the fastener 308 is stopped.
[0050] Fig.11 A cross-sectional view of the locking spacer assembly 300 in an assembled arrangement is shown installed in the final spacer slot 210. In the assembled arrangement, also refer to Figure 3, the head 604 of the intermediate member 306 is flush with the first outer surface 404 and the second outer surface 504, thereby defining a flat flow path. 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 member 306 is located between the first side member 302 and the second side member 304. The intermediate body 606 is partially positioned outside the first groove 414 and the second groove 514. The first surface 608 of the intermediate member 306 engages with the first inner surface 402. The second surface 610 of the base 602 engages with the second inner surface 502. The fastener 308 is partially disposed within the intermediate member 306. The fastener 308 contacts and rests on the surface 802 of the disc groove 208. At least a portion of the threaded portion 706 of the fastener 308 engages with the threaded surface 1102 of the intermediate member 306. The first side member 302, the second side member 304, and the middle member 306 are positioned in place in the final spacing groove 210 of the disc groove 208 by the fasteners 308. The fasteners 308 are fixed in the middle member 306 by riveting using the riveting indents 616. The final spacing groove 210 of the disc groove 208 is filled by the locking spacing assembly 300. The rotating compressor blades 118 are locked in the disc groove 208.
[0051] Fig.12 Yes Figures 8 to 11 The assembly method 1200 for installing the locking spacer assembly 300 into the final spacer slot 210 is shown. In frame 1202, the middle member 306 is held between and in contact with the first side member 302 and the second side member 304 by partially positioning the head 604 of the middle member 306 in the first recess 412 of the first side member 302 and the second recess 512 of the second side member 304, thereby defining a pre-assembly arrangement of the locking spacer assembly 300. In frame 1204, the middle member 306, the first side member 302, and the second side member 304 in the pre-assembly arrangement are placed into the final spacer slot 210. In frame 1206, the first side member 302 and the second side member 304 are moved away from the middle member 306. In frame 1208, the fastener 308 is engaged with the middle member 306. In frame 1210, the fastener 308 is rotated to engage with the surface 802 of the disc groove 208. In block 1212, the fastener 308 is further rotated to move the intermediate member 306 away from the surface 802 of the disc recess 208. In block 1214, the fastener 308 is stopped from rotating when the head 604 of the intermediate member 306 moves to a position flush with the first outer surface 404 of the first side member 302 and the second outer surface 504 of the second side member 304.
[0052] Although the exemplary embodiments of the present invention have been described in detail, those skilled in the art will understand that they may make various changes, substitutions, alterations, and modifications herein without departing from the spirit and scope of the invention in its broadest form.
[0053] Nothing in the description of this application should be read as implying that any particular element, step, action, or function is an essential element that must be included within the scope of the claims. The scope of the subject matter of this patent is limited only by the issued claims. Furthermore, unless the exact words "means for..." are followed by a participle, none of the claims are intended to invoke a means-plus-function claim construction.
[0054] Reference numerals
[0055] 100: Gas turbine engine
[0056] 102: Compressor section
[0057] 104: Combustion section
[0058] 106: Turbine section
[0059] 108: Entrance section
[0060] 110: Exhaust
[0061] 112: Central axis
[0062] 114: Compressor stage
[0063] 116:Fix the compressor guide vane
[0064] 118: Rotary compressor blades
[0065] 120: Burner
[0066] 122: Exhaust
[0067] 124: Turbine stage
[0068] 126: Fixed turbine guide vane
[0069] 128: Rotating turbine blades
[0070] 130: Turbine inlet
[0071] 132: Control System
[0072] 134: Rotor
[0073] 200: Blade assembly
[0074] 202: Rotor disc
[0075] 204: Platform
[0076] 206: Root
[0077] 208: disc groove
[0078] 210: Final spacing slot
[0079] 300: Locking spacer assembly
[0080] 302: first side member
[0081] 304: Second side member
[0082] 306: Middle part
[0083] 308: Fasteners
[0084] 402: first inner surface
[0085] 404: first outer surface
[0086] 406: first inner surface
[0087] 408: first outer surface
[0088] 410: First Subject
[0089] 412: First concave part
[0090] 414: First groove
[0091] 502: second inner surface
[0092] 504: second outer surface
[0093] 506: second inner surface
[0094] 508: second outer surface
[0095] 510: Second Subject
[0096] 512: Second recess
[0097] 514: Second groove
[0098] 602: Base
[0099] 604: Head
[0100] 606: Intermediate Subject
[0101] 608: first surface
[0102] 610: Second surface
[0103] 612: With plate
[0104] 614: Hollow interior
[0105] 616: Riveted indentation
[0106] 702: Fastener head
[0107] 704: Fastener body
[0108] 706: threaded part
[0109] 802: Surface
[0110] 804: first side surface
[0111] 806: second side surface
[0112] 1102: thread surface
[0113] 1200: Assembly method
Claims
1. A locking spacer assembly configured to fill a final spacing slot between platforms of adjacent rotating blades in a disc groove of a gas turbine engine, the locking spacer assembly comprising: a first side member, the first side member comprising a first outer surface; a second side member, the second side member comprising a second outer surface; an intermediate member disposed between and in contact with the first side member and the second side member, the intermediate member comprising a base and a head, the base having a dovetail shape that engages with the first side member and the second side member in an assembled arrangement, the head being flush with the first outer surface and the second outer surface in the assembled arrangement; as well as A fastener is partially disposed within the intermediate member and contacts a surface of the disc recess, the fastener being operable to move the intermediate member, the first side member, and the second side member into the assembled arrangement.
2. The locking spacer assembly of claim 1, wherein: The intermediate component includes an intermediate body disposed between the base and the head.
3. The locking spacer assembly of claim 2, wherein: The intermediate member defines a hollow interior through the base, the intermediate body, and the head, and wherein the fastener is partially disposed within the hollow interior.
4. The locking spacer assembly of claim 1, wherein: The base includes a first surface angled relative to a radial direction and a second surface angled relative to the radial direction, and wherein the first surface and the second surface cooperate to define the dovetail shape.
5. The locking spacer assembly of claim 1, wherein: The first side member includes a first inner surface angled relative to a radial direction, wherein the second side member includes a second inner surface angled relative to the radial direction, and wherein the first inner surface and the second inner surface engage the base.
6. The locking spacer assembly of claim 2, wherein: The first side member includes a first groove extending from a first inner surface toward the first outer surface, wherein the second side member includes a second groove extending from a second inner surface toward the second outer surface, and wherein the intermediate body of the intermediate member is disposed between the first groove and the second groove.
7. The locking spacer assembly of claim 1, wherein: The first side member defines a first recess formed on an inner side of the first outer surface, and wherein the second side member defines a second recess formed on an inner side of the second outer surface.
8. The locking spacer assembly of claim 1, wherein: The intermediate member includes a strap extending between the base and the head.
9. A locking spacer assembly configured to fill a final spacing slot between platforms of adjacent rotating blades in a disk groove of a gas turbine engine, the locking spacer assembly comprising: a first side member, the first side member comprising a first outer surface and a first recess formed on an inner side of the first outer surface; a second side member, the second side member comprising a second outer surface and a second recess formed on an inner side of the second outer surface; an intermediate component, the intermediate component including a base, a head, and an intermediate body located between the base and the head, the intermediate component, the first side component, and the second side component being movable between a pre-assembled arrangement in which the head is partially disposed in the first and second recesses and completely below the first and second outer surfaces, and an assembled arrangement in which the head is flush with the first and second outer surfaces; as well as A fastener is partially disposed within the intermediate member and is operable to move the intermediate member, the first side member, and the second side member between the pre-assembled arrangement and the assembled arrangement.
10. The locking spacer assembly of claim 9, wherein: The intermediate member defines a hollow interior through the base, the intermediate body, and the head, and wherein the fastener is partially disposed within the hollow interior.
11. The locking spacer assembly of claim 9, wherein: The base has a dovetail shape including a first surface angled relative to a radial direction and a second surface angled relative to the radial direction.
12. The locking spacer assembly of claim 11, wherein: The first side member comprises a first inner surface angled relative to the radial direction, wherein the second side member comprises a second inner surface angled relative to the radial direction, wherein in the assembled arrangement the first inner surface engages the first surface, and wherein in the assembled arrangement the second inner surface engages the second surface.
13. The locking spacer assembly of claim 11, wherein: The first side member comprises a first groove extending from a first inner surface to the first outer surface, wherein the second side member comprises a second groove extending from a second inner surface to the second outer surface, and wherein, in the pre-assembled arrangement, the intermediate body is disposed within the first groove and the second groove.
14. The locking spacer assembly of claim 9, wherein: The intermediate component includes a strap coupled to the intermediate body and extending between the base and the head.
15. The locking spacer assembly of claim 9, wherein: In the assembled arrangement, the fastener engages a surface of the disc groove.
16. The locking spacer assembly of claim 9, wherein: The head of the intermediate part defines two riveting indentations.
17. A method for installing a locking spacer assembly into a final spacing slot between platforms of adjacent rotating blades in a disk groove of a gas turbine engine, the method comprising: retaining the intermediate member between and in contact with the first and second side members by positioning a head of the intermediate member partially within a first recess of the first side member and a second recess of the second side member to define a pre-assembled arrangement of the locking spacer assembly; placing the intermediate member, the first side member, and the second side member in the pre-assembled arrangement within the final spacing slot; moving the first side member and the second side member away from the middle member; engaging a fastener with the intermediate member; rotating the fastener to engage a surface of the disc recess; further rotating the fastener to move the intermediate member away from the surface of the disc groove; as well as When the head of the intermediate member moves to a position flush with the first outer surface of the first side member and the second outer surface of the second side member, the rotation of the fastener is stopped.
18. The method of claim 17, further comprising engaging the intermediate member with the first side member and the second side member.
19. The method of claim 17, further comprising moving the first side member and the second side member in response to movement of the intermediate member.
20. The method of claim 17, further comprising riveting the fastener in the intermediate component via two rivet indentations defined on the head of the intermediate component.