Vibration damping assembly for turbomachine exhaust diffuser
Patent Information
- Application Number
- JP2024105908
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-08-01
- Filing Date
- 2024-07-01
- Publication Date
- 2025-02-26
Smart Images
Figure 2025026820000001_ABST
Abstract
Description
[Technical field]
[0001] FIELD OF THE DISCLOSURE This disclosure relates generally to vibration mitigation in turbomachine exhaust diffusers. More specifically, this disclosure relates to an apparatus for mitigating frequency vibrations in turbomachine exhaust diffusers. [Background technology]
[0002] Turbomachines are used in various industries and applications for energy transfer. For example, a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and combusted in the combustion chamber to generate high-pressure, high-temperature combustion gases. The combustion gases enter the turbine section from the combustion section and expand to generate work. For example, the expansion of the combustion gases in the turbine section rotates a rotor shaft connected to, for example, a generator, generating electricity. The combustion gases are then exhausted from the turbine section through an exhaust diffuser located downstream of the turbine section.
[0003] Exhaust diffusers typically include an inner liner and an outer liner that is radially spaced from the inner liner to define the exhaust flowpath of the diffuser. One or more generally airfoil-shaped diffuser struts extend between the inner and outer liners in the exhaust flowpath and provide structural support to the outer liner and / or to an aft bearing that supports the shaft.
[0004] A typical power generating turbomachine is capable of enormous power output and is therefore often operated at part load to meet demand. However, operating at part load can cause frequency oscillations (i.e., pressure pulsations or pressure oscillations) in the exhaust diffuser that over time can cause damage and / or lead to unscheduled or premature shutdown of the turbomachine.
[0005] Accordingly, a vibration damping assembly that reduces or eliminates the mechanical vibrations experienced by exhaust diffusers is desirable and it is believed that such a vibration damping assembly would be appreciated in the art. Summary of the Invention
[0006] Aspects and advantages of the exhaust diffuser assembly and vibration damping assembly according to the present disclosure are described in part in the following detailed description, will be obvious from the detailed description, or may be learned by practice of the art.
[0007] According to one embodiment, an exhaust diffuser assembly for a turbomachine is provided, the exhaust diffuser including an inner liner, an outer liner spaced apart from the inner liner, the outer liner defining an exhaust flowpath between the inner liner and the outer liner, and a plurality of struts disposed in the exhaust flowpath, the plurality of struts extending between the inner liner and the outer liner. The exhaust diffuser assembly further includes one or more vibration damping assemblies attached to at least one of the inner liner, the outer liner, and one or more struts of the plurality of struts at the exhaust diffuser, each vibration damping assembly of the plurality of vibration damping assemblies includes at least one pin assembly coupled to the exhaust diffuser, the at least one pin assembly having a pin body and a disk coupled to the pin body. The at least one pin assembly further includes at least one plate disposed between the disk and the exhaust diffuser, the at least one plate surrounding the at least one pin. The at least one plate is movable relative to the pin body and relative to the exhaust diffuser between the disk and the exhaust diffuser.
[0008] According to another embodiment, there is provided a vibration damping assembly for mounting to a turbomachine component. The vibration damping assembly includes at least one pin assembly coupled to the turbomachine component. The at least one pin has a pin body and a disk coupled to the pin body. The vibration damping assembly further includes at least one plate disposed between the disk and the turbomachine component. The at least one plate surrounds the at least one pin. The at least one plate is movable relative to the at least one pin and relative to the turbomachine component between the disk and the turbomachine component to damp vibrations experienced by the turbomachine component.
[0009] These and other features, aspects and advantages of the exhaust diffuser assembly and vibration damping assembly of the present invention will be better understood with reference to the following detailed description and claims. The drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present technology and, together with the detailed description, serve to explain the principles of the technology. [Brief description of the drawings]
[0010] A full and enabling disclosure of the exhaust diffuser assembly and vibration damping assembly of the present invention, including the best mode, directed to one of ordinary skill in the art, of making and using the systems and methods of the present invention, is set forth in the specification, which makes reference to the following figures: [Figure 1] 1 is a schematic diagram of a turbomachine according to an embodiment of the present disclosure; [Diagram 2] 1 illustrates an enlarged cross-sectional view of an exhaust diffuser assembly according to an embodiment of the present disclosure. [Diagram 3] 3 illustrates a cross-sectional view of an exhaust diffuser assembly taken along line 3-3 shown in FIG. 2 in accordance with an embodiment of the present disclosure. [Figure 4]1 illustrates an isometric view of an exhaust diffuser assembly having an exhaust diffuser with multiple vibration damping assemblies coupled thereto in accordance with an embodiment of the present disclosure. [Diagram 5] 5 illustrates an enlarged top view of the exhaust diffuser assembly shown in FIG. 4 according to an embodiment of the present disclosure. [Figure 6] 6 illustrates a schematic cross-sectional view of an exhaust diffuser assembly 100 taken along line 6-6 shown in FIG. 5 in accordance with an embodiment of the present disclosure. [Figure 7] FIG. 2 is a cross-sectional view of an exhaust diffuser assembly showing details of a floating pin assembly according to an embodiment of the present disclosure. [Figure 8] FIG. 2 is a cross-sectional view of an exhaust diffuser assembly showing details of a locating pin assembly according to an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0011] Reference will now be made in detail to the embodiments of the exhaust diffuser assembly and vibration damping assembly of the present invention, one or more examples of which are illustrated in the drawings. Each example is provided for purposes of explanation, not limitation of the technology. Indeed, it will be apparent to those skilled in the art that modifications and variations of the technology can be made without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield still a further embodiment. Thus, it is intended that the present disclosure cover such modifications and variations as come within the scope of the claims and their equivalents.
[0012] The word "exemplary" is used herein to mean serving as an example, instance, or illustration. Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Moreover, unless otherwise specified, all embodiments described herein should be considered exemplary.
[0013] In the detailed description, numerical and letter designations are used to refer to features in the drawings. Like or similar designations in the drawings and specification are used to represent like or similar parts of the invention. In this specification, the terms "first", "second" and "third" may be used interchangeably to distinguish between components and are not intended to imply a position or importance of the individual components.
[0014] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that two or more regions that define a flow path are coupled to one another such that a fluid can communicate between the designated regions.
[0015] As used herein, the terms "upstream" (or "forward") and "downstream" (or "aft") refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which a fluid flows, and "downstream" refers to the direction to which a fluid flows. However, as used herein, the terms "upstream" and "downstream" can also refer to electrical flow. The term "radial" refers to a relative direction that is substantially perpendicular to an axial centerline of a particular component, the term "axial" refers to a relative direction that is substantially parallel and / or coaxial to an axial centerline of a particular component, and the term "circumferential" refers to a relative direction that extends around an axial centerline of a particular component.
[0016] Approximate terms such as "approximately," "about," "generally," and "substantially" are not limited to the exact value specified. In at least some instances, approximation language may correspond to the precision of an instrument for measuring a value or to the precision of a method or machine for constructing or manufacturing a component and / or system. For example, approximation language may refer to within a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% for either an individual value, a range of values, and / or the end values defining the range of values. When used in the context of an angle or direction, such terms include values within a range of 10 degrees greater or less than the referenced angle or direction. For example, "approximately perpendicular" includes a direction within 10 degrees of any direction (e.g., clockwise or counterclockwise) from perpendicular.
[0017] Terms such as "coupled," "fixed," "attached," and the like, unless otherwise stated herein, refer to both directly coupled, directly fixed, or directly attached, and indirectly coupled, indirectly fixed, or indirectly attached through one or more intervening intermediate components or features. Terms such as "directly coupled," "directly fixed," "directly attached," and the like, mean that two components are attached so that they are in contact with each other and there are no intermediate components or features present.
[0018] As used herein, the terms "comprise," "comprising," "include," "including," "has," "having," or other variations of these terms are intended to be non-exclusive. For example, a process, method, article, or apparatus that includes a list of features is not necessarily limited to only those features, but may include other features not expressly listed or that are not inherent to such process, method, article, or apparatus. Furthermore, unless expressly stated to the contrary, "and / or" expresses a condition that is satisfied by any of "A is true (or present) and B is false (or absent)," "A is false (or absent) and B is true (or present)," and "both A and B are true (or present)."
[0019] Here, and throughout the specification and claims, range limiting portions are combinable and interchangeable, and such ranges are specified and include all subranges contained therein, unless the context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the end values of the ranges, and the end values can be independently combined with each other.
[0020] Referring now to the drawings, Figure 1 shows a schematic diagram of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine 10. Although an industrial or land-based gas turbine is illustrated and described herein, the present disclosure is not limited to land-based and / or industrial gas turbines, unless otherwise stated in the claims. For example, the invention described herein may be used with any type of turbomachine, such as, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.
[0021] As shown, the gas turbine engine 10 generally includes a compressor section 12. The compressor section 12 includes a compressor 14. The compressor section 12 includes an inlet section 16 disposed at an upstream end of the gas turbine engine 10. The gas turbine engine 10 further includes a combustion section 18 having one or more combustors 20 disposed downstream from the compressor section 12. The gas turbine engine 10 further includes a turbine section 22 downstream from the combustion section 18. A shaft 24 extends generally axially within the gas turbine engine 10.
[0022] The compressor section 12 may generally include a number of rotor disks 21 and a number of rotor blades 23 extending radially outward from and connected to each rotor disk 21. Each rotor disk 21 may be coupled to or may form a part of a shaft 24 that extends through the compressor section 12. The rotor blades 23 of the compressor section 12 may include turbomachine airfoils that define an airfoil shape (e.g., an airfoil having a leading edge, a trailing edge, and sidewalls extending between the leading and trailing edges). Additionally, the compressor section 12 may include stator vanes disposed between the rotor blades to define a series of compression stages. The stator vanes may extend from and be coupled to a compressor casing.
[0023] The turbine section 22 may generally include a number of rotor disks 27 and a number of rotor blades 28 extending radially outward from and interconnected to each rotor disk 27. Each rotor disk 27 may be coupled to or may form a portion of the shaft 24 that passes through the turbine section 22. The turbine section 22 further includes an outer casing 32 that circumferentially surrounds the portion of the shaft 24 and the rotor blades 28. The turbine section 22 may include static nozzles 26 extending radially inward from the outer casing 32. The rotor blades 28 and the static nozzles 26 may be alternately arranged to form stages along an axial centerline 30 of the gas turbine 10. The rotor blades 28 and the static nozzles 26 may include turbine machine airfoils (e.g., having a leading edge, a trailing edge, and sidewalls extending between the leading edge and the trailing edge) that define an airfoil shape.
[0024] In operation, ambient air 36 or other working fluid is drawn into the inlet section 16 of the compressor 14 and progressively compressed to provide compressed air 38 to the combustion section 18. The compressed air 38 enters the combustion section 18 and is mixed with fuel to form a combustible mixture. The combustible mixture is combusted in a combustion chamber 40 of the combustor 20, thereby generating combustion gases 42 which pass from the combustion chamber 40 to the turbine section 22. Energy (kinetic and / or thermal energy) is transferred from the combustion gases 42 to the rotor blades 28, which rotate the shaft 24 to produce mechanical work.
[0025] The gas turbine engine 10 may define a cylindrical coordinate system having an axial direction A extending along the axial centerline 30, a radial direction R perpendicular to the axial centerline 30, and a circumferential direction C extending about the axial centerline 30.
[0026] The combustion gases 42 exit the turbine section 22 and flow through the exhaust diffuser 34 across a number of struts 44 disposed within the exhaust diffuser 34. During various operating conditions of the gas turbine engine 10 (e.g., during part load operation), the combustion gases 42 entering the exhaust diffuser 34 from the turbine section 22 are imparted with a high level of swirling motion caused by the rotating turbine rotor blades 28. Such swirling may cause pressure fluctuations, frequency oscillations, or acoustic vibrations.
[0027] FIG. 2 illustrates a cross-sectional view of an exhaust diffuser assembly 100 (including the exhaust diffuser 34) according to an embodiment of the present disclosure, and FIG. 3 illustrates a cross-sectional view of the exhaust diffuser assembly 100 taken along line 3-3 shown in FIG. 2. As illustrated, the exhaust diffuser 34 generally includes an inner liner 46 and an outer liner 48 radially spaced from the inner liner 46. The inner liner 46 may extend generally axially along an axial centerline 50 of the exhaust diffuser 34. The axial centerline 50 of the exhaust diffuser 34 may be coaxial with the axial centerline 30 of the gas turbine engine 10. The inner liner 46 is generally annular and may at least partially surround a rotating component. For example, the inner liner 46 may surround a portion of or completely encase the shaft 24.
[0028] In many embodiments, the outer liner 48 is radially spaced from the inner liner 46 such that an exhaust flow path 52 is defined between the inner liner 46 and the outer liner 48. In certain embodiments, the inner liner 46 is disposed within the outer liner 48 concentrically and coaxially with respect to the axial centerline 50. In certain embodiments, the outer casing 56 may annularly surround the outer liner 48 such that a fluid plenum 58 is defined between the outer casing 56 and the outer liner 48. A flow of compressed air (or other working fluid) may flow within the fluid plenum 58 to cool various components of the exhaust diffuser 34 (such as the outer liner 48 and the struts 44). The present disclosure is not limited to a particular size, shape, material, or other physical characteristics of the inner liner 46, the outer liner 48, and / or the outer casing 56, except as recited in the claims.
[0029] Each of the diffuser struts 44 may extend between the inner liner 46 and the outer liner 48 and into an exhaust flow passage 52 defined between the liners. The diffuser struts 44 are spaced apart circumferentially about the inner liner 46, and the diffuser struts 44 may orient, align, or otherwise center the inner liner 46 within the outer liner 48. Additionally, the diffuser struts 44 may provide structural support between the inner liner 46 and the outer liner 48. As shown in FIG. 1, the diffuser struts 44 are positioned relative to a flow direction 60 of the spent combustion gases 42 flowing from the turbine section 22 of the gas turbine engine 10. As shown in FIG. 3, each diffuser strut 44 generally includes a root 62 connected to the inner liner 46 and a tip 64 radially spaced from the root 62 and connected to the outer liner 48.
[0030] 3, the exhaust diffuser assembly 100 may further include one or more vibration damping assemblies 200 attached to the exhaust diffuser 34 at at least one of the inner liner 46, the outer liner 48, and at least one strut 44 of the plurality of struts 44. In particular, as shown, multiple vibration damping assemblies 200 may be attached to the inner liner 46, multiple vibration damping assemblies 200 may be attached to the outer liner 48, and one or more vibration damping assemblies may be attached to each strut 44 of the plurality of struts 44. Each of the vibration damping assemblies 200 may be disposed outside of the exhaust flowpath 52.
[0031] In an exemplary embodiment, the one or more vibration damping assemblies 200 include a plurality of vibration damping assemblies 200 that are circumferentially spaced apart from one another and attached to at least one of the outer liner 48 and / or the inner liner 46 outside of the exhaust flowpath 52. For example, the one or more vibration damping assemblies 200 may be attached to a radially outer surface 49 of the outer liner 48 and disposed within the fluid plenum 58 (e.g., radially between the outer liner 48 and the outer casing 56). In this manner, the one or more vibration damping assemblies 200 attached to the outer liner 48 may be disposed between the outer liner 48 and the outer casing 56 (e.g., radially between the outer liner 48 and the outer casing 56). The one or more vibration damping assemblies 200 may be radially spaced apart from the outer casing 56 (the vibration damping assemblies 200 do not contact the outer casing 56).
[0032] Additionally or alternatively, one or more vibration damping assemblies 200 may be attached to a radially inner surface 47 of the inner liner 46. The one or more vibration damping assemblies 200 attached to the inner liner 46 may be disposed between the inner liner 46 and the shaft 24 (e.g., radially between the inner liner 46 and the shaft 24). The one or more vibration damping assemblies 200 attached to the inner liner 46 may be radially spaced away from the shaft 24 (the vibration damping assemblies 200 do not contact the shaft 24).
[0033] In some embodiments, as shown, one or more vibration damping assemblies 200 may be disposed within a strut 44. For example, the strut 44 may include a leading edge 81 ( FIG. 2 ), a trailing edge 83 ( FIG. 2 ), a first sidewall 82, and a second sidewall 84, which may collectively define an interior 86 of the strut 44. One or more vibration damping assemblies 200 may be disposed within the interior 86 of the strut 44. For example, the vibration damping assembly 200 may be coupled (or attached) to one of the first sidewall 82 and / or the second sidewall 84 within the interior 86.
[0034] 3 illustrates the vibration damping assembly 200 attached to the inner liner 46, the outer liner 48, and the struts 44, it should be understood that the vibration damping assembly 200 may be coupled to any component of the gas turbine engine 10 (i.e., a "turbomachine component") to dampen vibrations experienced by that component. In certain embodiments, the vibration damping assembly 200 may be coupled to a turbomachine airfoil, such as an airfoil of the compressor section 12 (e.g., a compressor rotor blade and / or stator vane airfoil), or an airfoil of the turbine section 22 (e.g., a turbine rotor blade and / or a turbine nozzle airfoil). However, in an exemplary embodiment, as shown in FIG. 3, the vibration damping assembly 200 may be coupled to various components of the exhaust diffuser 34 (e.g., the inner liner 46, the outer liner 48, and the struts 44) to dampen vibrations experienced by the exhaust diffuser 34.
[0035] 4 illustrates an isometric view of an exhaust diffuser assembly 100 having an exhaust diffuser 34 with a number of vibration attenuation assemblies 200 coupled thereto. As discussed above, the exhaust diffuser 34 may include an inner liner 46, an outer liner 48, and a number of struts 44 extending (e.g., radially) between the inner liner 46 and the outer liner 48. The exhaust diffuser 34 may include an upper half 70 and a lower half 72, which are joined to one another at a splitline 74. Additionally, the exhaust diffuser 34 may extend axially between a forward end 78 and an aft end 76.
[0036] As shown in FIG. 4, the vibration attenuation assemblies 200 mounted to the outer liner 48 may be arranged in a forward group 314, one or more intermediate groups 312 (one intermediate group 312 is shown in FIG. 4), and an aft group 310. The forward group 314, one or more intermediate groups 312, and the aft group 310 may be axially staggered (or offset) such that the groups 310, 312, 314 do not axially overlap. The forward group 314 may be located closest to the forward end 78 of the exhaust diffuser 34. The intermediate group or groups 312 may be axially positioned between the forward group 314 and the aft group 310. The aft group 310 may be located closest to the aft end 76. Similarly, as shown, the vibration attenuation assemblies 200 mounted to the inner liner 46 may be arranged in forward and aft groups.
[0037] As shown in FIGS. 3 and 4 , each strut 44 of the plurality of struts 44 defines an interior 86 that extends between an outer opening 88 defined in the outer liner 48 and an inner opening 90 defined in the inner liner 46. In such an embodiment, one or more vibration damping assemblies 200 attached to the outer liner 48 may be disposed between circumferentially adjacent outer openings 88. In particular, the aft group 310 and one or more middle groups 312 may be disposed circumferentially between two adjacent outer openings 88. The forward group 314 may be disposed forward of the outer openings 88. Similarly, one or more vibration damping assemblies 200 attached to the inner liner 46 may be disposed between circumferentially adjacent inner openings 90.
[0038] In many embodiments, the exhaust diffuser 34 may further include a plurality of support links 300 coupled to the outer surface 49 of the outer liner 48. The plurality of support links 300 may be circumferentially spaced from one another (e.g., equally spaced in some instances and / or unequally spaced in other instances). The plurality of support links 300 may be disposed forward of the aft group 310 of vibration damping assemblies 200 attached to the outer liner 48. For example, a single splitline support link 300 may be disposed between the splitline 74 and the outer opening 88, and the vibration damping assembly 200 may be sized to fit within the circumferential dimension between the outer opening 88 and the splitline 74. A group of equally spaced support links 300 (e.g., a group of three support links) may be disposed circumferentially between two outer openings 88. 5, each support link 300 may include a body portion 302 coupled (e.g., by one or more fasteners) to an outer surface 49 of the outer liner 48 and a flange portion 304 extending radially outward from the body portion 302. One or more vibration damping assemblies 200 may be disposed between the outer liner 48 and the one or more support links 300 (e.g., radially between the outer liner 48 and the one or more support links 300). For example, one or more support links 300 may axially overlap and be disposed radially outward relative to one or more of the vibration damping assemblies 200 of the middle group 312 and forward group 314.
[0039] 5 illustrates an enlarged plan view of an exhaust diffuser assembly 100 according to an embodiment of the present disclosure. As illustrated, the vibration damping assembly 200 can include at least one plate 202 and at least one pin assembly 204 that penetrates the at least one plate 202. For example, the at least one plate 202 can surround the at least one pin assembly 204. In particular, the vibration damping assembly 200 can include multiple pin assemblies 204 coupled to the exhaust diffuser 34 (e.g., coupled to one of the outer liner 48, the inner liner 46, or the struts 44), each pin assembly penetrating at least one plate 202. In various embodiments, the at least one plate 202 can be constructed of metal (e.g., sheet metal) or other suitable material.
[0040] As shown, the multiple pin assemblies 204 coupled to the plate 202 of each vibration damping assembly 200 may be arranged in an array. In other words, the multiple pin assemblies 204 may be arranged in an array (e.g., in a pattern) on the exhaust diffuser 34. The multiple pin assemblies 204 may be arranged in one or more rows, with each row arranged along a common axis (along a circumferential axis 206, an axial axis 208, a radial axis (not shown), or another axis that does not correspond to an axial, circumferential, or radial direction). Each pin assembly 204 may be spaced apart from adjacent pin assemblies 204 of the multiple pin assemblies 204.
[0041] In an exemplary embodiment, the plurality of pin assemblies 204 for each vibration damping assembly 200 may include at least one locating pin assembly 205. Each pin assembly 204, 205 includes a pin body 112 that fits into an opening in at least one plate 202 of the vibration damping assembly 200 and a disk 114 that secures the at least one plate 202 in position relative to a respective surface of the exhaust diffuser 34. As described in more detail below, the locating pin assembly 205 may ensure that the at least one plate 202 does not move in a direction perpendicular to the longitudinal axis of the pin body 112 (FIGS. 6 and 7) and may limit movement of the at least one plate 202 to movement parallel to the longitudinal axis of the pin body 112 between the disk 114 and the exhaust diffuser 34. In an exemplary embodiment, the locating pin 205 may be located toward the center of the plate 202.
[0042] As shown in Figure 5, at least one plate 202 can have a width 124, a length 126, and a thickness 128, 129 (Figures 7 and 8). The length 126 can be greater than the width 124 and the thickness 128, 129 (i.e., the length 126 is the longest dimension of the plate 202). The thickness 128, 129 can be less than the length 126 and the width 124 (i.e., the thickness 128, 129 is the smallest dimension of the plate 202). The surface area of the plate 202 can be calculated by multiplying the width 124 by the length 126. In exemplary embodiments, the at least one plate 202 is thin-walled and defines a ratio of the thickness 128, 129 of the at least one plate 202 to the width 124 of the at least one plate 202 of between about 1:100 and about 1:5000 (e.g., between about 1:500 and about 1:4500, between about 1:1000 and about 1:4000, between about 1:1500 and about 1:3500, or between about 1:2000 and about 1:3000). In many embodiments, the surface area of the at least one plate 202 is less than about 0.02 m. 2 and about 2m 2 Between (for example, about 0.12 m2 and about 1.9m 2 Between the two, approximately 0.22m 2 and about 1.8m 2 Between the two, approximately 0.32m 2 and about 1.7m 2 Between the two, approximately 0.42m 2 and about 1.6m 2 Between the two, approximately 0.52m 2 and about 1.5m 2 Between or about 0.82m 2 and about 1.2m 2 (between and ).
[0043] FIG. 6 illustrates a cross-sectional view of the exhaust diffuser assembly 100 along line 6-6 shown in FIG. 5 in accordance with an embodiment of the present disclosure. As illustrated, each pin of the plurality of pins 204 may include a pin body portion 112 and a disk 114 coupled to the pin body portion 112. The pin body portion 112 may extend from the exhaust diffuser 34. For example, in FIG. 5, the pin body portion may extend from the outer surface 49 of the outer liner 48. In an exemplary embodiment, as illustrated, the at least one plate 202 may include two or more plates 202 disposed between the disk 114 and the exhaust diffuser 34. In such an embodiment, the at least one plate 202 may include an outer plate 210 (e.g., a radially outer plate) and an inner plate 212 (e.g., a radially inner plate). The inner plate 212 may be radially disposed between the exhaust diffuser 34 and the outer plate 210. The outer plate 210 may be radially disposed between the inner plate 212 and the disk 114. At least one plate 202, including an inner plate 212 and an outer plate 210, may move relative to at least one pin 204 and relative to the exhaust diffuser 34 to damp vibrations experienced by the exhaust diffuser 34 during operation of the gas turbine engine 10.
[0044] As shown in FIGS. 6-8, each plate 202 can define a plurality of openings 122, and the plurality of openings 122 can be concentrically aligned with one another, with the entirety of the openings 122 of each plate 202 defining a passageway. Each pin body 112 of at least one pin assembly 204, 205 can pass through a respective opening 122 of the plurality of openings 122. In particular, the pin body 112 of each pin assembly 204, 205 can pass through the opening 122 of the inner plate 212 and the opening 122 of the outer plate 212 (thereby passing through the passageway). The diameter of the disk 114 can be longer than the diameter of the openings 122 to prevent the plate 202 from falling off the pin body 112 during installation or operation. Similarly, the diameter of the pin body 112 can be smaller than the diameter of the opening 122 so that the pin body 112 can pass through the opening 122.
[0045] The pin body portion 112 of each pin assembly 204, 205 may extend along a longitudinal axis 250 (extending generally perpendicularly from the exhaust diffuser 34), and at least one plate 202 may be restricted to movement along the longitudinal axis 250 to dampen vibrations experienced by the exhaust diffuser. This restricted movement is provided by a locating pin assembly 205, which may have a different structure than the other pin assemblies 204 (described below), and which may contact one or more plates 202 to restrict movement of the plates in one direction. In the embodiment shown in FIG. 6, the vibration damping assembly 200 may include one or more outer locating pin assemblies 214 and one or more inner locating pin assemblies 216. For each outer locating pin assembly 214, the opening 122 in the outer plate 210 through which the outer locating pin body 112 passes can be sized such that the outer plate 210 forms frictional contact with the outer locating pin body 112 around the pin body, thereby limiting movement of the outer plate 210 in a direction parallel to the longitudinal axis 250. Similarly, for each inner locating pin assembly 216, the opening 122 in the inner plate 212 through which the inner locating pin body 112 passes can be sized such that the inner plate 212 forms frictional contact with the inner locating pin body 112 around the pin body, thereby limiting movement of the inner plate in a direction parallel to the longitudinal axis 250.
[0046] In many embodiments, the outer plate 210 can be offset (e.g., axially offset and / or circumferentially offset) from the inner plate 212 such that the inner plate 212 and the outer plate 210 partially overlap. In an exemplary embodiment, the outer plate 210 can be circumferentially offset from the inner plate 212 such that the inner plate 212 and the outer plate 210 partially overlap. In such an embodiment, a portion of the inner plate 212 can extend circumferentially beyond a terminal end of the outer plate 210 on a first side of the vibration damping assembly 200, and a portion of the outer plate 210 can extend circumferentially beyond a terminal end of the inner plate on a second side of the vibration damping assembly 200 (the second side being opposite the first side).
[0047] As shown in FIG. 6, the plurality of vibration damping assemblies 200 may include a first vibration damping assembly 200A and a second vibration damping assembly 200B adjacent to each other (e.g., circumferentially adjacent to each other). The first vibration damping assembly 200A includes a first outer plate 210A and a first inner plate 212A, and the second vibration damping assembly 200B includes a second outer plate 210B and a second inner plate 212B. The first inner plate 212A may be offset from the first outer plate 210A and contact the first outer plate 210A and the second outer plate 210B. The first inner plate 212A may extend from a first end 220 that overlaps (contacts) the first outer plate 210A to a second end 222 that overlaps (contacts) the second outer plate 210B.
[0048] 7 is a cross-sectional view of the exhaust diffuser assembly 100 illustrating details of a pin assembly 204 (e.g., a floating pin assembly) according to an embodiment of the present disclosure. As illustrated, the pin assembly 204 includes a pin body portion 112 coupled to a surface 35 of the exhaust diffuser 34. The surface 35 of the exhaust diffuser 34 may be a radially inner surface of the inner liner 46 or a radially outer surface of the outer liner 48. For example, the pin body portion 112 may extend along a longitudinal centerline 250 from a base portion 130 coupled to the surface 35 of the exhaust diffuser 34 to a tip portion 132. The pin body portion 112 may be generally cylindrical in shape, and the pin body portion 112 may terminate at the tip portion 132. The base 130 of the pin body 112 may be fixedly coupled to the surface 35 by welding, with a weld seam or fillet 134 formed annularly around the base 130 of the pin body 112, thereby joining the pin body 112 to the surface 35.
[0049] The pin assembly 204 may further include a disk 114 annularly surrounding the pin body 112. The disk 114 may be coupled to the pin body 112 between the base 130 and the tip 132. In various embodiments, the disk 114 may be fixedly coupled to the pin body 112 by welding, with a weld seam or fillet 136 formed annularly around the pin body 112, thereby coupling the pin body 112 to the disk 114. Alternatively, the pin body 112 may include a threaded tip 132, with the disk 114 threaded to the tip 132, and optionally further secured by welding or brazing.
[0050] In an exemplary embodiment, the at least one plate 202 can be at least two plates 202 disposed between the disk 202 and the surface 35, as shown in Figure 7. Although Figures 7 and 8 show an embodiment having two plates 202, it should be understood that the vibration damping assembly 200 can include any number of plates 202 and should not be limited to a particular number of plates unless specifically recited in the claims. The at least two plates 202 can include an inner plate 212 and an outer plate 210.
[0051] As shown in FIG. 7, each plate 202 of the plurality of at least two plates 202 may define an opening 122, and the openings of the plates may be concentrically aligned with one another, with the entirety of the openings 122 of each plate 202 defining a passageway. The pin body 112 may pass through each opening 122 (thereby penetrating the passageway). The diameter of the disk 114 may be longer than the diameter of the opening 122 to prevent the plate 202 from falling off the pin body 112 during installation or operation. Similarly, the diameter of the pin body 112 may be smaller than the diameter of the opening 122 so that the pin body 112 may pass through the opening 122.
[0052] In an exemplary embodiment, the plates 202 can include a first plate (e.g., inner plate 212) having a first thickness 128 and a second plate (e.g., outer plate 210) having a second thickness 129. The second thickness 129 can be thicker than the first thickness 128. For example, the second thickness 129 can be between about 20% and about 80% thicker than the first thickness 128 (e.g., between about 30% and about 70% thicker than the first thickness 128, between about 40% and about 60% thicker than the first thickness 128). In many embodiments, the total thickness (e.g., the sum of the first thickness 128 and the second thickness 129) of the one or more panels 202 can be between about 20% and about 100% of the wall thickness of the wall (e.g., the inner liner 46 or the outer liner 48) to which the vibration damping assembly 200 is attached. In an exemplary embodiment, the combined thickness of the one or more panels 202 may be between about 40% and about 60% of the wall thickness of the wall to which the vibration damping assembly 200 is mounted, which has the advantage of providing the greatest damping effect for the wall to which the vibration damping assembly 200 is mounted.
[0053] In an exemplary embodiment, each of the two or more plates 202 can be movable between the disk 114 and the surface 35 relative to the pin body 112, the disk 114, the exhaust diffuser 34, and relative to the other plates of the two or more plates 202 to damp vibrations experienced by the exhaust diffuser 34. For example, each of the plates 202 can be limited to movement in a direction parallel to the longitudinal axis 250 of the pin body 112 between the disk 114 and the surface 35. In various embodiments, a gap (not shown) can be defined between the disk 114 and the plurality of plates 202, and the plurality of plates 202 can move into the gap. For example, the distance between the inner surface of the disk 114 and the surface 35 can be slightly longer (e.g., 0.01% to about 5% longer) than the sum of the first thickness 128 and the second thickness 129, and a micro-gap can be defined between the disk 114 and the outer plate 210. In this manner, the two or more plates 202 can move in a direction parallel to the longitudinal centerline 250 of the pin body 112 between the disk 114 and the surface 35 so as to damp vibrations of the exhaust diffuser 34.
[0054] FIG. 8 is a cross-sectional view of the exhaust diffuser assembly 100, showing details of a locating pin assembly 205 according to an embodiment of the present disclosure. As shown, the locating pin assembly 205 can include an annular wall 140 extending from the disk 114 toward the surface 35 of the exhaust diffuser 34. The annular wall 140 can extend from the disk 114 of the locating pin assembly 205 toward the surface 35 of the exhaust diffuser 34 to a free end 224. The free end 224 can be spaced apart from the surface 35 of the exhaust diffuser 34. In this manner, the annular wall 140 can be cantilevered away from the disk 114. The free end 224 can be spaced apart from the surface 35 of the exhaust diffuser 34 such that a gap is defined between the free end 224 and the surface 35 (i.e., the free end 224 does not contact the surface 35), which can advantageously prevent wear and increase the life of the locating pin 205. Although the annular wall 140 is illustrated (e.g., by hatching in FIG. 8) as a separate element from the disk 114, it should be understood that the annular wall 140 and the disk 114 may be integrally formed.
[0055] At least one plate 202 can contact the annular wall 140 of the locating pin 205. For example, the diameter of the opening 122 can be within about 5% of the outer diameter of the annular wall 140 such that the boundary defining the opening 122 is in sliding contact with the outside of the annular wall 140. In this manner, the annular wall 140 can restrict the plurality of plates 202 to movement in a direction parallel to the longitudinal centerline 250 of the pin body 112. Additionally, the annular wall 140 prevents lateral movement of the plates 202 (e.g., circumferential movement) that would otherwise subject the base 130 of the pin body 112 to stress and fatigue life caused by repeated contact with the moving plates 202.
[0056] During operation, the plates 202 may move relative to the disk 114 and the exhaust diffuser 34, which creates micro-impacts (or "bumping") between the plates 202. These micro-impacts may counteract vibrations experienced by the component to which the vibration-damping assembly 200 is attached, thereby advantageously increasing the hardware life of that component.
[0057] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention (e.g., make and use any devices or systems, and perform any methods incorporating the same). The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they contain structural elements that do not differ from the literal language of the claims, or if they contain equivalent structural elements that are not substantially different from the literal language of the claims.
[0058] Further aspects of the invention are provided by the subject matter of the following embodiments. [Embodiment 1] An exhaust diffuser assembly for a turbomachine, the exhaust diffuser assembly including an exhaust diffuser including an inner liner, an outer liner spaced apart from the inner liner, the outer liner defining an exhaust flowpath between the inner liner and the outer liner, and a plurality of struts disposed in the exhaust flowpath, the plurality of struts extending between the inner liner and the outer liner; and one or more vibration damping assemblies attached to at least one of the inner liner, the outer liner, and one or more struts of the plurality of struts in the exhaust diffuser, the plurality of vibration damping assemblies being arranged to dampen the plurality of vibration damping assemblies. Each vibration damping assembly of the dynamic damping assembly includes at least one pin assembly coupled to the exhaust diffuser, the at least one pin assembly having a pin body portion and a disk coupled to the pin body portion, and at least one plate arranged between the disk and the exhaust diffuser, the at least one plate surrounding the at least one pin, the at least one plate being movable relative to the pin body portion and relative to the exhaust diffuser, between the disk and the exhaust diffuser, to damp vibrations experienced by the exhaust diffuser. [Embodiment 2] An exhaust diffuser assembly as described in embodiment 1, wherein the one or more vibration damping assemblies include a plurality of vibration damping assemblies circumferentially spaced from one another and attached to at least one of the outer liner and the inner liner outside of the exhaust flow path. [Embodiment 3] An exhaust diffuser assembly as described in embodiment 1 or 2, wherein each strut of the plurality of struts defines an interior extending between an outer opening defined in the outer liner and an inner opening defined in the inner liner, at least one vibration damping assembly is attached to the outer liner and disposed between circumferentially adjacent outer openings, and at least one vibration damping assembly is attached to the inner liner and disposed between circumferentially adjacent inner openings. [Embodiment 4] The exhaust diffuser assembly of any one of embodiments 1 to 3, wherein the at least one plate includes an outer plate and an inner plate. [Embodiment 5] An exhaust diffuser assembly as described in any one of embodiments 1 to 4, wherein the outer plate is offset from the inner plate such that the inner plate and the outer plate partially overlap. [Embodiment 6] An exhaust diffuser assembly as described in any one of embodiments 1 to 5, wherein the plurality of vibration damping assemblies include a first vibration damping assembly and a second vibration damping assembly adjacent to each other, the first vibration damping assembly including a first outer plate and a first inner plate, the second vibration damping assembly including a second outer plate and a second inner plate, and the first inner plate is offset from the first outer plate and contacts the first outer plate and the second outer plate. [Embodiment 7] An exhaust diffuser assembly as described in any one of embodiments 1 to 6, wherein the at least one plate is thin-walled and the at least one plate defines a ratio of a thickness of the at least one plate to a width of the at least one plate of between about 1:100 and 1:5000. [Embodiment 8] An exhaust diffuser assembly as described in any one of embodiments 1 to 7, wherein the at least one plate includes two or more plates disposed between the disk and the exhaust diffuser. [Embodiment 9] The exhaust diffuser assembly of any one of embodiments 1 to 8, wherein the at least one plate includes a first plate having a first thickness and a second plate having a second thickness, the second thickness being greater than the first thickness. [Embodiment 10] An exhaust diffuser assembly as described in any one of embodiments 1 to 9, wherein the at least one pin assembly includes a plurality of pin assemblies arranged in an array on the exhaust diffuser, and the plurality of pin assemblies includes at least one positioning pin assembly. [Embodiment 11] An exhaust diffuser assembly as described in any one of embodiments 1 to 10, wherein the locating pin assembly includes an annular wall extending from a disk of the locating pin assembly toward the exhaust diffuser to a free end, the free end being spaced apart from the exhaust diffuser, and the at least one plate contacting the annular wall of the locating pin. [Embodiment 12] 1. A vibration damping assembly attached to a turbomachine component, the vibration damping assembly including: at least one pin assembly coupled to the turbomachine component, the at least one pin assembly having a pin body portion and a disk coupled to the pin body portion; and at least one plate disposed between the disk and the turbomachine component, the at least one plate surrounding at least one pin, the at least one plate being movable between the disk and the turbomachine component with respect to the at least one pin and with respect to the turbomachine component to damp vibrations experienced by the turbomachine component. [Embodiment 13] 13. A vibration damping assembly as described in embodiment 12, wherein the at least one plate is thin-walled and defines a ratio of the thickness of the at least one plate to the width of the at least one plate of between about 1:100 and 1:5000. [Embodiment 14] 14. A vibration damping assembly as described in embodiment 12 or 13, wherein the at least one plate includes two or more plates disposed between the disk and the turbomachine component. [Embodiment 15] A vibration damping assembly as described in any one of embodiments 12 to 14, wherein the at least one plate includes a first plate having a first thickness and a second plate having a second thickness, the second thickness being thicker than the first thickness. [Embodiment 16] A vibration damping assembly described in any one of embodiments 12 to 15, wherein the at least one plate defines a plurality of openings, and each pin assembly of the at least one pin assembly passes through a respective opening of the plurality of openings. [Embodiment 17] A vibration damping assembly as described in any one of embodiments 12 to 16, wherein the at least one pin assembly includes a plurality of pin assemblies arranged in an array on the turbomachine component. [Embodiment 18] A vibration damping assembly according to any one of embodiments 12 to 17, wherein the plurality of pin assemblies includes at least one positioning pin assembly. [Embodiment 19] A vibration damping assembly as described in any of embodiments 12 to 18, wherein the positioning pin assembly includes an annular wall extending from a disk of the positioning pin assembly toward the turbomachinery component to a free end, the free end being spaced apart from the turbomachinery component, and the at least one plate contacting the annular wall of the positioning pin assembly. [Embodiment 20] A vibration damping assembly as described in any one of embodiments 12 to 19, wherein the turbomachinery component is an exhaust diffuser having an inner liner, an outer liner, and a plurality of struts, and the vibration damping assembly is attached to at least one of the inner liner and the outer liner. [Explanation of symbols]
[0059] 10. Gas Turbine Engine 12 Compressor section 14 Compressor 16 Entrance 18 Combustion section 20 Combustor 21 Rotor disk 22 Turbine section 23 Rotor Blades 24 Shaft 26 Stationary Nozzle 27 Rotor disc 28 Rotor Blades 30 Axial centerline 32 Outer casing 34 Exhaust diffuser 35 Surface 36 Ambient air 38 Compressed Air 40 Combustion chamber 42 Combustion Gas 44 Strut 46 Inner liner 47 Surface 48 Outer liner 49 Surface 50 Axial centerline 52 Exhaust passage 56 Outer casing 58 Fluid Plenum 60 directions 62 Root 64 Tip 70 Upper half 72 Lower half 74 Partition Line 76 Rear end 78 Front end 81 Leading Edge 82 First side wall 83 Relationship 84 Second Side Wall 86 Internal 88 Outer opening 90 Inner opening 100 Exhaust diffuser assembly 112 Pin body 114 Disk 122 Opening 124 Width 126 Length 130 base 132 Tip 134 Fillet 136 Fillet 140 Circular Wall 200 Vibration Damping Assembly 200A First Vibration Damping Assembly 200B Second vibration damping assembly 202 Plate 206 Circumferential axis 208 Axial axis 210 Outer Plate 210A First Outer Plate 210B Second outer plate 212 Inner plate 212A First Inner Plate 212B Second inner plate 214 Outer Locating Pin Assembly 216 Inner Locating Pin Assembly 220 First end 222 Second End 224 Free end 300 Support Links 302 Main body 304 Flange part 310 Rear Group 312 Middle Group 314 Front Group
Claims
1. A vibration damping assembly (200) for attachment to a turbomachinery component (34), the vibration damping assembly (200) comprising: at least one pin assembly (204) coupled to the turbomachine component (34), the at least one pin assembly (204) having a pin body portion (112) and a disk (114) coupled to the pin body portion (112); and at least one plate (202) disposed between said disk (114) and said turbomachine component (34), said at least one plate (202) defining at least one opening (122) through which a pin body portion (112) of said at least one pin assembly (204) extends; Including, The at least one plate (202) is movable relative to the at least one pin assembly (204) and relative to the turbomachinery component (34) between the disk (114) and the turbomachinery component (34) to damp vibrations experienced by the turbomachinery component (34).
2. 2. The vibration damping assembly of claim 1, wherein the turbomachine component is an exhaust diffuser having an inner liner, an outer liner, and a plurality of struts extending between the inner liner and the outer liner, and the vibration damping assembly is attached to the inner liner, the outer liner, and at least one of one or more struts of the plurality of struts.
3. The vibration damping assembly (200) of claim 1, wherein the at least one plate (202) comprises an outer plate (210) and an inner plate (212).
4. The vibration damping assembly (200) of claim 3, wherein the outer plate (210) is offset from the inner plate (212) such that the inner plate (212) and the outer plate (210) partially overlap.
5. 2. The vibration damping assembly of claim 1, wherein the vibration damping assembly is a first vibration damping assembly and further comprises a second vibration damping assembly adjacent to the first vibration damping assembly, the first vibration damping assembly comprising a first outer plate and a first inner plate, the second vibration damping assembly comprising a second outer plate and a second inner plate, the first inner plate being offset from the first outer plate and in contact with the first outer plate and the second outer plate.
6. The vibration damping assembly (200) of any one of claims 1 to 5, wherein the at least one plate (202) is thin-walled and defines a ratio of a thickness of the at least one plate (202) to a width of the at least one plate (202) of between about 1:100 and 1:5000.
7. The vibration damping assembly (200) of any of the preceding claims, wherein the at least one plate (202) comprises two or more plates (210, 212) disposed between the disk (114) and the turbomachine component (34).
8. 2. The vibration damping assembly (200) of claim 1, wherein the at least one plate (202) includes a first plate (212) having a first thickness (128) and a second plate (210) having a second thickness (129), the second thickness (129) being greater than the first thickness (128).
9. A vibration damping assembly (200) as described in any one of claims 1 to 8, wherein the at least one opening (122) is a plurality of openings (122), and each pin assembly (204) of the at least one pin assembly (204) passes through a respective opening (122) of the plurality of openings (122).
10. The vibration damping assembly (200) of any of the preceding claims, wherein the at least one pin assembly (204) comprises a plurality of pin assemblies (204) arranged in an array on the turbomachinery component (34).
11. The vibration damping assembly (200) of claim 10, wherein the plurality of pin assemblies (204) includes at least one locating pin assembly (205).
12. 12. The vibration damping assembly (200) of claim 11, wherein the locating pin assembly (205) includes an annular wall (140) extending from a disk (114) of the locating pin assembly (205) toward the turbomachinery component (34) to a free end (224), the free end (224) being spaced apart from the turbomachinery component (34), and the at least one plate (202) contacting the annular wall (140) of the locating pin assembly (205).
13. 13. An exhaust diffuser assembly (100) for a turbomachine, the exhaust diffuser assembly (100) including: an inner liner (46); an outer liner (48) spaced apart from the inner liner (46), the outer liner defining an exhaust flowpath (52) therebetween; and a plurality of struts (44) disposed in the exhaust flowpath (52), the plurality of struts (44) extending between the inner liner (46) and the outer liner (48), wherein a vibration damping assembly (200) according to any one of claims 1 to 12 is attached to at least one of the inner liner (46), the outer liner (48), and one or more struts (44) of the plurality of struts (44).
14. 14. The exhaust diffuser assembly (100) of claim 13, wherein the one or more vibration damping assemblies (200) include a plurality of vibration damping assemblies (200) circumferentially spaced from one another and attached to at least one of the outer liner (48) and the inner liner (46) outside of the exhaust flowpath (52).
15. 15. The exhaust diffuser assembly (100) of claim 14, wherein each strut (44) of the plurality of struts (44) defines an interior (86) extending between an outer opening (88) defined in the outer liner (48) and an inner opening (90) defined in the inner liner (46), at least one vibration damping assembly (200) attached to the outer liner (48) and disposed between circumferentially adjacent outer openings (88), and at least one vibration damping assembly (200) attached to the inner liner (46) and disposed between circumferentially adjacent inner openings (90).