Patent Application
20250215802
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 blade and stationary compressor vane. The combustion section includes a plurality of combustor. The turbine section includes multiple stages of rotating turbine blade and stationary turbine vane. The rotating compressor blade and the rotating turbine blade are arranged in rows axially spaced apart along a rotor disk and circumferentially attached to a periphery of the rotor disk.
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 that includes a first outer surface, a second side piece that includes a second outer surface, a mid-piece that is disposed between and in contact with the first side piece and the second side piece. The mid-piece includes a base and a head. The base has a dovetail shape that engages with the first side piece and the second side piece in an assembled arrangement. The head is flush with the first outer surface and the second outer surface in the assembled arrangement. A fastener is partially disposed within the mid-piece and in contact with a surface of the disk groove. The fastener is operable to move the mid-piece, the first side piece, and the second side piece to the assembled arrangement.
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 that includes a first outer surface and a first recess formed inward of the first outer surface, a second side piece that includes a second outer surface and a second recess formed inward of the second outer surface, a mid-piece that includes a base, a head, and a mid-body between the base and the head. The mid-piece, the first side piece, and the second side piece are movable between a pre-assembled arrangement in which the head is partially disposed into the first recess and the second recess and is completely below the first outer surface and the second outer surface and an assembled arrangement in which the head is flush with the first outer surface and the second outer surface. A fastener is partially disposed within the mid-piece and operable to move the mid-piece, the first side piece, and the second side piece between the pre-assembled arrangement and the assembled arrangement.
In one aspect, a method installs a locking spacer assembly into a final spacer slot in a disk groove between platforms of adjacent rotating blades in a gas turbine engine. The method includes holding a mid-piece between and in contact with a first side piece and a second side piece by positioning a head of the mid-piece partially into a first recess of the first side piece and a second recess of the second side piece defining a pre-assembled arrangement of the locking spacer assembly, placing the mid-piece, the first side piece, and the second side piece in the pre-assembled arrangement into the final spacer slot, moving the first side piece and the second side piece away from the mid-piece, engaging a fastener with the mid-piece, rotating the fastener to engage 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 a head of the mid-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.
To easily identify the discussion of any particular element or act, the most significant digit or digits in a reference number refer to the figure number in which that element is first introduced.
Before any embodiments of the invention are explained in detail, it is to be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in this description or illustrated in the following drawings. The invention is capable of other embodiments and of being practiced or of being 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.
Various technologies that pertain to systems and methods will now be described with reference to the drawings, where like reference numerals represent like elements throughout. The drawings discussed below, and the various embodiments used to describe the principles of the present disclosure in this patent document are by way of illustration only and should not be construed in any way to limit the scope of the disclosure. Those skilled in the art will understand that the principles of the present disclosure may be implemented in any suitably arranged apparatus. It is to be understood that functionality that is described as being carried out by certain system elements may be performed by multiple elements. Similarly, for instance, an element may be configured to perform functionality that is described as being carried out by multiple elements. The numerous innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.
Also, it should be understood that the words or phrases used herein should be construed broadly, unless expressly limited in some examples. For example, the terms “including”, “having”, and “comprising”, as well as derivatives thereof, mean inclusion without limitation. The singular forms “a”, “an”, and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, the term “and/or” as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive, meaning and/or, unless the context clearly indicates otherwise. The phrases “associated with” and “associated therewith” as well as derivatives thereof, may mean to include, be included within, interconnect with, contain, be contained within, connect to or with, couple to or with, be communicable with, cooperate with, interleave, juxtapose, be proximate to, be bound to or with, have, have a property of, or the like. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc. described with regard to one embodiment are equally applicable to other embodiments absent a specific statement to the contrary.
Also, although the terms “first”, “second”, “third” and so forth may be used herein to refer to various elements, information, functions, or acts, these elements, information, functions, or acts should not be limited by these terms. Rather these numeral adjectives are used to distinguish different elements, information, functions or acts from each other. For example, a first element, information, function, or act could be termed a second element, information, function, or act, and, similarly, a second element, information, function, or act could be termed a first element, information, function, or act, without departing from the scope of the present disclosure.
Also, in the description, the terms “axial” or “axially” refer to a direction along a longitudinal axis of a gas turbine engine. The terms “radial” or “radially” refer to a direction perpendicular to the longitudinal axis of the gas turbine engine. The terms “downstream” or “aft” refer to a direction along a flow direction. The terms “upstream” or “forward” refer to a direction against the flow direction.
In addition, the term “adjacent to” may mean that an element is relatively near to but not in contact with a further element, or that the element is in contact with the further portion, unless the context clearly indicates otherwise. Further, the phrase “based on” is intended to mean “based, at least in part, on” unless explicitly stated otherwise. Terms “about” or “substantially” or like terms are intended to cover variations in a value that are within normal industry manufacturing tolerances for that dimension. If no industry standard is available, a variation of twenty percent would fall within the meaning of these terms unless otherwise stated.
The compressor section 102 is in fluid communication with an 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 that air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102 with other arrangements and designs being possible.
In the illustrated construction, the combustion section 104 includes a plurality of separate combustor 120 that each operates to mix a flow of fuel with the compressed air from the compressor section 102 and to combust that air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gas 122. Of course, many other arrangements of the combustion section 104 are possible.
The turbine section 106 includes a plurality of turbine stages 124 with each turbine stage 124 including a number of stationary turbine vanes 126 and a number of rotating turbine blades 128. The turbine stages 124 are arranged to receive the exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand that gas to convert thermal and pressure energy into rotating or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For gas turbine engines 100 used for power generation or as prime movers, the turbine section 106 is also connected to a generator, pump, or other devices to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are possible.
An exhaust portion 110 is positioned downstream of the turbine section 106 and is arranged to receive the expanded flow of exhaust gas 122 from the final turbine stage 124 in the turbine section 106. The exhaust portion 110 is arranged to efficiently direct the exhaust gas 122 away from the turbine section 106 to assure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust portion 110. As such, the illustrated exhaust portion 110 is but one example of those variations.
A control system 132 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and to control various operations of the gas turbine engine 100. In preferred constructions, the control system 132 is typically micro-processor 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, and the like which allow users to interface with the control system 132 to provide inputs or adjustments. In the example of a power generation system, a user may input a power output setpoint and the control system 132 may adjust the various control inputs to achieve that power output in an efficient manner.
The control system 132 can control various operating parameters including, but not limited to variable inlet guide vane positions, fuel flow rates and pressures, engine speed, valve positions, 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 assure that the gas turbine engine 100 is operating properly. Some parameters that are monitored may include inlet air temperature, compressor outlet temperature, and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, and the like. Many of these measurements are displayed for the user and are logged for later review should such a review be necessary.
The rotor disk 202 may be formed as a part of the rotor 134 or may be a separate part that is attached to the rotor 134. The rotor disk 202 defines a disk groove 208 for engaging the roots 206 of the rotating compressor blades 118. The rotating compressor blades 118 are inserted into the disk groove 208 one at a time during assembly. The platform 204 extends in the disk groove 208 along an axial direction A of the gas turbine engine 100. Once all the rotating compressor blades 118 are assembled in the disk groove 208, a final spacer slot 210 is defined in the disk groove 208 between the platform 204 of the rotating compressor blade 118 that is first installed and the platform 204 of the rotating compressor blade 118 that is last installed.
The locking spacer assembly 300 includes a first side piece 302, a second side piece 304, a mid-piece 306 disposed between the first side piece 302 and the second side piece 304, and a fastener 308 that is partially disposed within the mid-piece 306. The fastener 308 may include a screw, such as a set screw. The first side piece 302 may be positioned at a forward side with respect to the axial direction A. The second side piece 304 may be positioned at a rear side with respect to the axial direction A.
The first side piece 302 defines a first recess 412 in the first body 410. The first recess 412 is formed directly inward of the first outer surface 404. The first recess 412 may also be formed at any location between the first outer surface 404 and the first inner surface 402. The first recess 412 extends inward from the first inner side surface 406 toward the first outer side surface 408. The first recess 412 extends axially across the first body 410. The first recess 412 is formed at a radial position that is closer to the first outer surface 404 than to the first inner surface 402. The first recess 412 has a generally rectangular shape. Other shapes of the first recess 412 are also possible.
The first side piece 302 defines a first groove 414 that extends from the first inner surface 402 toward the first outer surface 404. The first groove 414 is defined in the first body 410 and inward of the first outer surface 404. The first groove 414 has an opening at the first inner side surface 406. The first groove 414 has a generally cylindrical shape. Other shapes of the first groove 414 are also possible.
The second side piece 304 includes a second inner surface 502 at the radially innermost position, a second outer surface 504 at the radially outermost position, a second inner side surface 506 at the axial inner side, a second outer side surface 508 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 with respect 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. Other orientations or shapes of the second inner surface 502, the second outer surface 504, the second inner side surface 506, and the second outer side surface 508 are also possible.
The second side piece 304 defines a second recess 512 in the second body 510. The second recess 512 is formed inward of the second outer surface 504. The second recess 512 may be formed directly inward of the second outer surface 504. The second outer surface 504 extends inward from the second inner side surface 506 toward the second outer side surface 508. The second outer surface 504 extends transversely across the second body 510. The second recess 512 is formed at a radial position that is closer to the second outer surface 504 than to the second inner surface 502. The second groove second recess 512 has a generally rectangular shape. Other shapes of the second recess 512 are also possible.
The second side piece 304 defines a second groove 514 that extends from the second inner surface 502 toward the second outer surface 504. The second groove 514 is defined in the second body 510 and inward of the second outer surface 504. The second groove 514 has an opening at the second inner side surface 506. The second groove 514 has a generally cylindrical shape. Other shapes of the second groove 514 are also possible.
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 the first surface 608 and the second surface 610.
The mid-piece 306 defines a hollow inside 614 that passes through the base 602, the mid-body 606, and the head 604. The hollow inside 614 incudes a threaded surface 1102 which is shown in
The mid-piece 306 has two staking dents 616 defined on the head 604. The two staking dents 616 are disposed on two opposite sides of an edge of the hollow inside 614 that intersects the head 604 with other locations and quantities being possible.
Although an exemplary embodiment of the present disclosure has been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements disclosed herein may be made without departing from the spirit and scope of the disclosure in its broadest form.
None of the descriptions in the present application should be read as implying that any particular element, step, act, or function is an essential element, which must be included in the claim scope. The scope of patented subject matter is defined only by the allowed claims. Moreover, none of these claims are intended to invoke a means plus function claim construction unless the exact words “means for” are followed by a participle.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2023/014787 | 3/8/2023 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63362695 | Apr 2022 | US |
