Membrane riding damper for rotating components

Abstract

A damper assembly for a rotor. The damper assembly includes a body. The body includes a first surface forming a first diaphragm interface with the rotor and a second surface forming an interface with a stator. The damper assembly further includes a damper rigidly coupled to the body. The damper includes an enclosed housing. The enclosed housing includes a damping medium and a plunger within the housing.

Description

Technical Field

[0001] This disclosure generally relates to vibration dampers, and more specifically, to diaphragm riding dampers for rotating components. Background Technology

[0002] Gas turbine engines, such as turbofan engines, are used for aircraft propulsion. A turbofan engine typically comprises a bypass fan section and a turbine (e.g., a gas turbine engine) for driving the bypass fan. The turbine typically comprises a compressor section, a combustor section, and a turbine section arranged in series. The compressor and turbine sections are driven by one or more rotor shafts and typically include multiple rows or stages of rotor blades coupled to the rotor shafts. The rotor blade rows are axially spaced from subsequent rotor blade rows by corresponding stator or stationary blade rows. A radial clearance is formed between the inner surface of the stator blades and the outer surface of the rotor shaft. Attached Figure Description

[0003] Figure 1 This is a schematic cross-sectional view of an example high-bypass turbofan gas turbine engine on which the examples disclosed herein can be implemented.

[0004] Figure 2 It is feasible to implement Figure 1 A cross-sectional view of an example damper assembly in an example gas turbine engine.

[0005] Figure 3A It is along Figure 2 The line AA in the middle is intercepted Figure 2 A cross-sectional view of an example damper component segment.

[0006] Figure 3B This is a cross-sectional view of a second example damper segment, which includes multiple flexible conduits.

[0007] Figure 3C This is a cross-sectional view of the third example damper segment, which includes a garter spring.

[0008] Figure 4 yes Figure 3A A schematic diagram of the damper assembly segment and rotor 202.

[0009] Figure 5A yes Figure 3A A schematic diagram of the cross-section of the damper.

[0010] Figure 5B yes Figure 3A A schematic diagram of the top cross-section of the damper.

[0011] Figure 6 Is it possible to... Figure 2An example optional configuration of the damping housing and damping plunger used together with the damper assembly.

[0012] Figure 7 It is feasible to implement Figure 1 A cross-sectional view of another example damper in an example gas turbine engine and which can be implemented according to the teachings of this disclosure.

[0013] Typically, the same reference numbers are used in drawings and accompanying text descriptions to refer to the same or similar parts. The drawings are not necessarily drawn to scale. Instead, the thickness of layers or areas in the drawings may be enlarged. Although the lines and boundaries of layers and areas in the drawings are clear and well-defined, some or all lines and / or boundaries may be idealized. In reality, boundaries and / or lines may be unobservable, mixed, and / or irregular. Detailed Implementation

[0014] Conventional rotor damping systems, such as extruded diaphragm dampers, are limited to mounting at the rotor's bearing location. Integrating such dampers into the bearing involves a soft mounting of the bearing and limits the vibrations experienced by the damper, thereby reducing the damper's effectiveness. Examples disclosed herein include dampers that track the radial motion of the rotor by straddling a diaphragm interface formed with the rotor. Example dampers disclosed herein can be integrated into shaft seals and / or independent of shaft seals. Example dampers disclosed herein include hermetically sealed, fluid-filled dampers mounted on a sealing section, rigidly mounted on the damper body, and moving with the rotor's vibrations and radial oscillations. Example dampers disclosed herein include plungers within a rigid housing that move relative to the housing and dampen rotor motion. Example dampers disclosed herein are not limited to integration into bearing locations but can also be installed at rotor mid-span locations, where relatively large radial motion amplitudes are experienced. Some example hermetically sealed dampers disclosed herein do not require special handling procedures and / or static sealing.

[0015] In this document, “comprising” and “including” (and all forms and tenses thereof) are open-ended terms. Therefore, when a claim uses any form of “comprising” or “including” (e.g., including, comprising, having, etc.) in the preamble or statement of the claim, it should be understood that additional elements, terms, etc., may be present without going beyond the scope of the corresponding claim or statement. As used herein, the word “at least” is an open-ended term, such as in the preamble of the claim, just like the words “comprising” and “including”. The term “and / or” when used, for example, in the form of A, B and / or C, refers to any combination or subset of A, B, C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, or (7) A and B and C. In this document, when describing structures, components, items, objects, and / or things, the phrase “at least one of A and B” means that it includes any of the following implementations: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, in this document, when describing structures, components, items, objects, and / or things, the phrase “at least one of A or B” means that it includes any of the following implementations: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. In this document, when describing the execution or implementation of processes, instructions, actions, activities, etc., the phrase “at least one of A and B” means that it includes any of the following implementations: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, in this document, when describing the execution or implementation of processes, instructions, actions, activities, etc., the phrase “at least one of A or B” means that it includes any of the following implementations: (1) at least one A, (2) at least one B, or (3) at least one A and at least one B.

[0016] The singular references used herein (e.g., “a,” “an,” “first,” “second,” etc.) do not exclude plural references. The term “a” or “an” as used herein refers to one or more of that object. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, although listed separately, multiple means, elements, or actions may be performed by, for example, the same entity or object. Moreover, while individual features may be included in different examples or claims, these features may also be combined, and inclusion in different examples or claims does not imply that the combination of features is infeasible and / or disadvantageous.

[0017] Unless otherwise stated, the term "above" in this document is used to describe the relationship between two parts relative to the Earth. The first part is above the second part if the second part lies between the Earth and the first part by at least one other part. Similarly, in this document, the first part is below the second part when the first part is closer to the Earth than the second part. As stated above, the first part can be above or below the second part, where one or more of the following can occur between the first and second parts: there are other parts between them, there are no other parts between them, the first and second parts are in contact, or the first and second parts are not in direct contact with each other.

[0018] In this patent, whenever any part (e.g., layer, film, region, sheet or plate) is located on (e.g., positioned on, located, disposed on or formed on) another part in any way, it means that the part mentioned is in contact with the other part, or that the part mentioned is above the other part and there is one or more intermediate parts between the two.

[0019] As used herein, a connection reference (e.g., attachment, coupling, connection, and union) may include intermediate components between the elements referred to by the connection reference and / or relative movement between these elements, unless otherwise stated. Therefore, a connection reference does not necessarily imply that two elements are directly connected and / or that there is a fixed relationship between them. In this document, the statement that any part is “in contact” with another part means that there is no intermediate portion between the two parts.

[0020] Unless otherwise expressly stated, the descriptive terms such as “first,” “second,” and “third” as used herein do not imply or otherwise indicate priority, physical order, listing arrangement, and / or any sorting, but are merely used as labels and / or arbitrary names to distinguish elements and thus facilitate understanding of the disclosed examples. In some examples, the descriptor “first” may be used to refer to an element in the detailed description, while the same element may be referred to by different descriptors in the claims, such as “second” or “third.” In such cases, it should be understood that these descriptors are only used to clearly identify those elements in the context of the discussion (e.g., in the claims), while those elements may share the same name in other cases.

[0021] The terms “approximately” and “about” as used herein modify their subject matter / value to identify variations that may occur in real-world applications. For example, “approximately” and “about” may modify dimensions that may not be precise due to manufacturing tolerances and / or other real-world defects that a person skilled in the art would understand. For example, “approximately” and “about” may indicate that the tolerance range for such dimensions is + / - 10%, unless otherwise specified herein.

[0022] During operation, rotating components (referred to herein as "rotors"), such as the shaft of a gas turbine engine, experience vibration and radial oscillations. These oscillations cause the rotor to travel radially. At high levels of oscillation, the rotor may come into contact with and potentially damage other components positioned around it. The amplitude of these oscillations, especially when the rotor speed reaches or approaches its critical speed, depends on the rotor's damping. In this context, the "critical speed" of a rotating component refers to the angular velocity at which the rotating device resonates. That is, when the rotor rotates at or near its critical speed, the oscillations depend almost entirely on the rotor's damping. Conversely, at non-critical speeds, the amplitude of the oscillations depends more on the rotor's associated stiffness and / or inertia than on its damping. The amplitude of rotor oscillations is typically larger at critical speeds than at non-critical speeds.

[0023] Previous damping systems for rotors, such as squeezed-film dampers, were limited to integration into the rotor's bearing location. Because the rotor is constrained at the bearing, the amplitude of oscillations and / or vibrations at this location is relatively small, thus limiting the effectiveness of squeezed-film damping. Furthermore, integrating a squeezed-film damper into the bearing location requires the bearing to be softly mounted to the stationary portion (referred to herein as the "stator"). The term "rotor modal shape" as used herein refers to the profile of the rotor's deformation (e.g., oscillation, vibration, etc.) at critical speeds. For rotors with a modal shape characterized by large vibration amplitudes and distance from the bearing location, the encapsulation limitations of previous squeezed-film dampers cannot effectively dampen such rotors.

[0024] The examples disclosed herein overcome the aforementioned drawbacks, including diaphragm-riding dampers that engage directly with the rotor in a non-bearing location. The damper assemblies disclosed herein include a damper body that travels with the rotor's vibrations, and a damper rigidly coupled thereto. Some such damper assemblies disclosed herein include a hermetically sealed housing, a damping medium, and a plunger coupled to the housing via one or more springs. In some examples disclosed herein, the relative motion between the housing and the plunger dissipates the energy generated by the rotor's vibrations and provides damping force. Some example dampers disclosed herein are hermetically sealed, do not include elastomeric seals, and do not require complex operating procedures. Other example dampers disclosed herein include a body and a plunger rigidly coupled to and extending from the body into the damping medium of the damper. Some example damper assemblies disclosed herein are not limited to engagement in bearing locations but can also be coupled to the rotor in any spanwise location with high oscillation amplitudes, thereby improving the efficiency of the damper assemblies disclosed herein. Some example damper assemblies disclosed herein are diaphragm-riding seals, which reduce air leakage from them.

[0025] Referring now to the accompanying drawings, the same numbers in all figures represent the same elements. Figure 1This is a schematic cross-sectional view of an example high-bypass turbofan gas turbine engine 110 (“turbofan engine 110”). Although the illustrated example is a high-bypass turbofan engine, the principles of this disclosure are also applicable to other types of engines, such as low-bypass turbofan engines, turbojet engines, turboprop engines, propeller fans, etc. Figure 1 As shown, the gas turbine engine 110 defines a longitudinal or axial centerline axis 112 running through it for reference. Figure 1 It also includes annotations for the axial direction A, circumferential direction C, and radial direction R.

[0026] Typically, the gas turbine engine 110 includes a core turbine 114 located downstream of the fan section 116. The core turbine 114 includes a generally tubular outer casing 118 defining an annular inlet 120. The casing 118 may consist of a single casing or multiple casings. The casing 118 surrounds, in series flow relationships, a compressor section (having a turbocharger or low-pressure compressor 122 (“LP compressor 122”) and a high-pressure compressor 124 (“HP compressor 124”)), a combustion section 126, a turbine section (having a high-pressure turbine 128 (“HP turbine 128”) and a low-pressure turbine 130 (“LP turbine 130”)), and an exhaust section 132. A high-pressure shaft or spool 134 (“HP shaft 134”) drives the HP turbine 128 and HP compressor 124. A low-pressure shaft or spool 136 (“LP shaft 136”) drives the LP turbine 130 and LP compressor 122. The LP shaft 136 can also be coupled to the fan spool or shaft 138 of the fan section 116. In some examples, the LP shaft 136 is directly coupled to the fan shaft 138 (e.g., direct drive configuration). In alternative configurations, the LP shaft 136 may be coupled to the fan shaft 138 via a reduction gear 139 (e.g., indirect drive or gear drive configuration).

[0027] like Figure 1 As shown, fan section 116 includes a plurality of fan blades 140, which are coupled to and extend radially outward from fan shaft 138. An annular fan housing or nacelle 142 circumferentially surrounds at least a portion of fan section 116 and / or core turbine 114. Nacelle 142 may be supported relative to core turbine 114 by a plurality of circumferentially spaced outlet guide vanes 144 (e.g., partial support, etc.). Furthermore, downstream section 146 of nacelle 142 may surround an outer portion of core turbine 114, thereby defining a bypass airflow passage 148 therebetween.

[0028] like Figure 1As shown, air 150 enters its inlet section 152 during operation of the gas turbine engine 110. A first portion 154 of the air 150 flows into a bypass airflow passage 148, while a second portion 156 of the air 150 flows into the inlet 120 of the LP compressor 122. One or more successive stages of the LP compressor stator blades 170 and the LP compressor rotor blades 172 coupled to the LP shaft 136 progressively compress the second portion 156 of the air 150 flowing through the LP compressor 122 and toward the HP compressor 124. Next, one or more successive stages of the HP compressor stator blades 174 and the HP compressor rotor blades 176 coupled to the HP shaft 134 further compress the second portion 156 of the air 150 flowing through the HP compressor 124. This provides compressed air 158 to the combustion section 126, where it mixes with fuel and burns to produce combustion gases 160.

[0029] Combustion gas 160 flows through HP turbine 128, from which one or more successive stages of HP turbine stator blades 166 and HP turbine rotor blades 168 coupled to HP shaft 134 extract a first portion of kinetic and / or thermal energy. This energy extraction supports the operation of HP compressor 124. Combustion gas 160 then flows through LP turbine 130, from which one or more successive stages of LP turbine stator blades 162 and LP turbine rotor blades 164 coupled to LP shaft 136 extract a second portion of thermal and / or kinetic energy. This energy extraction causes LP shaft 136 to rotate, thereby supporting the operation of LP compressor 122 and / or the rotation of fan shaft 138. Combustion gas 160 then exits core turbine 114 through exhaust section 132 of core turbine 114. Turbine frame 161 with fairing assembly is located between HP turbine 128 and LP turbine 130. The turbine frame 161 serves as a supporting structure, connecting the rear bearing of the high-pressure shaft to the turbine housing and forming an aerodynamic transition duct between the HP turbine 128 and the LP turbine 130. The cowling forms a fluid passage between the high-pressure turbine and the low-pressure turbine and can be made of metal castings (e.g., nickel-based cast metal alloys).

[0030] Like the gas turbine engine 110, the core turbine 114 plays a similar role and is exposed to a similar environment in land-based gas turbines, turbojet engines (where the ratio of the first section 154 of air 150 to the second section 156 of air 150 is less than that in turbofan engines), and ductless fan engines (where the fan section 116 has no nacelle 142). In each of the turbofan engine, turbojet engine, and ductless engine, a reduction gear (e.g., reduction gear 139) may be included between any shaft and spool. For example, reduction gear 139 is disposed between the LP shaft 136 and the fan shaft 138 of the fan section 116.

[0031] As mentioned above Figure 1 The turbine frame 161 is located between the HP turbine 128 and the LP turbine 130, serving to connect the rear bearing of the high-pressure shaft to the turbine housing, and forming an aerodynamic transition duct between the HP turbine 128 and the LP turbine 130. Therefore, airflow passes through the turbine frame 161 between the HP turbine 128 and the LP turbine 130.

[0032] Figure 2 It is possible Figure 1 A cross-sectional view of an example damper assembly 200 implemented in an example gas turbine engine 110. Figure 2 In the example shown, the damper assembly 200 is positioned around the rotor 202. In some examples, the rotor 202 is an example shaft of the gas turbine engine 110 (e.g., Figure 1 LP axis 136 in Figure 1 Fan shaft 138 in Figure 1 (e.g., HP shaft 134 in the example). In other examples, rotor 202 can be implemented using different types of rotating components (e.g., the shaft of another carrier, the shaft of an industrial machine, the shaft of a pump, a camshaft, a rotary disk, a flywheel, etc.). That is, damper assembly 200 can be used with any device that includes rotating components. In some examples, damper assembly 200 acts as a seal. That is, damper assembly 200 can suppress the axial flow of gas along rotor 202 and define an axial pressure difference on damper section 204. In other examples, damper assembly 200 is not a seal, and damper assembly 200 does not define a pressure difference thereon.

[0033] exist Figure 2 In the example shown, damper assembly 200 includes eight damper segments (e.g., damper segment 204, etc.) that are uniformly distributed circumferentially around rotor 202. In other examples, damper assembly 200 may contain a different number of damper segments (e.g., two segments, three segments, four segments, eight segments, ten segments, etc.). Additionally or alternatively, some or all of damper segments 204 may have different dimensions and / or shapes. In some such examples, damper segments 204 are not uniformly distributed circumferentially around rotor 202.

[0034] exist Figure 2In the example shown, adjacent segments of damper segment 204 include side surfaces 206, with a circumferential gap 208 defined between the side surfaces. Additionally or alternatively, adjacent segments of damper segment 204 may be joined together at one or more locations (e.g., edges, etc.) along the side surfaces 206 of damper segment 204. For example, damper segments 204 may be joined in a manner that allows damper segments 204 to move radially independently (e.g., in a manner that allows different segments of damper segment 204 to simultaneously generate different radial displacements from rotor 202, etc.). In some examples, each damper segment 204 may be arranged within a frame surrounding rotor 202.

[0035] exist Figure 2 In the example shown, the damper assembly 200 includes an inner surface 209 adjacent to the rotor 202 (e.g., each damper segment 204 defines a portion of the inner surface 209, etc.). Figure 2 In the example shown, the inner surface 209 of the damper assembly 200 is spaced apart from the rotor 202, forming a radial gap 210 between the rotor 202 and the damper assembly 200. Figure 2 In the example shown, the damper assembly 200 forms a first thin-film interface 212 (e.g., a thin film of pressurized gas) between the rotor 202 and the damper assembly 200. In some such examples, each damper segment 204 discharges pressurized air from its inner surface 209 into the radial gap 210.

[0036] The first thin-film interface 212 bears the radial force transmitted between the rotor 202 and the damper assembly 200, but does not bear the force transmitted in the axial and / or circumferential directions. Therefore, the first thin-film interface 212 does not inhibit the rotor 202 from rotating around the rotor. Figure 1 The centerline axis 112 (for example, in) Figure 2 Rotation in the axial direction C (extending outwards from the center of the page). In some examples, the damper assembly 200 may form an additional thin-film interface with other components (e.g., the stator). In some such examples, the additional thin-film interface can suppress axial translation of the damper assembly 200, thereby maintaining separation between the stator and the damper segment 204. Figure 2 In the example shown, the first thin-film interface 212 can maintain the separation between the rotor 202 and the damper section 204 to reduce friction between them, thereby reducing wear on the damper section 204 and / or the rotor 202 during operation of the gas turbine engine 110. (The following is in conjunction with...) Figure 3A The first thin film interface 212 will be described in more detail.

[0037] Figure 3A It is feasible. Figure 2 A cross-sectional view of an example damper segment 300 in damper segment 204. Figure 3AThe cross-sectional view is along Figure 2 It was taken from line AA in the image. Figure 3A In the example shown, rotor 202 includes rotor flange 301. In other examples, rotor flange 301 is not present. Figure 3A In the example shown, damper segment 300 includes damper body 302 (also referred to herein as "body"), interface plate 304, and member 306 extending therebetween. Figure 3A In the example shown, damper segment 300 is adjacent to stator 308.

[0038] exist Figure 3A In the example shown, the damper body 302 includes an arm 310 extending from the damper body 302, a damper flange 312 extending from the arm 310, and an internal conduit 314 formed within the damper body 302. As used herein, "internal conduit" refers to a flow path formed within the negative space of a rigid component (e.g., the damper body 302 and / or the stator 308). Figure 3A In the example shown, the damper segment 300 includes a groove 316 in the arm 310 and a piston rod 318 disposed therein. Figure 3A In the example shown, damper segment 300 is disposed between the first region 321A and the second region 321B. Figure 3A In the example shown, the damper body 302, interface plate 304, and component 306 are depicted as a single integral part. In some such examples, the damper segment 300 may be manufactured by additive manufacturing and / or subtractive manufacturing. In other examples, one or more of the damper body 302, interface plate 304, and component 306 may be manufactured as separate components and then assembled into the damper segment 300. Component 306 extends between the damper body 302 and the interface plate 304. Figure 3A In the example shown, member 306 is a rigid member, such that interface plate 304 is rigidly connected to damper body 302 (e.g., interface plate 304 travels radially together with damper body 302, etc.). As used herein, a member is considered “rigid” when it has a deformation-resistant geometry (e.g., the member is not configured as a spring, etc.) and is composed of a material with a relatively high modulus of elasticity (e.g., metals (e.g., aluminum, steel, titanium, nickel-based alloys, etc.), composite materials (e.g., reinforced plastics, ceramic composites, carbon composites, etc.) and similar materials). As used herein, two members are considered “rigidly connected” when there is no relative movement between them other than the strain of the members and any rigid members disposed therebetween. In some such examples, member 306 is configured to allow for bending of itself (e.g., member 306 is relatively thinner than damper body 302, etc.), thereby enabling relative movement between damper body 302 and interface plate 304.

[0039] Stator 308 is the stationary (e.g., non-rotating) part of the machine, which includes... Figure 2 Rotor 202 and Figure 2 The damper assembly 200 in the middle. For example, if the damper assembly 200 is set in Figure 1 Within the gas turbine engine 110, the stator 308 may be part of the housing of the gas turbine engine 110 that houses the rotor 202, a stationary disk, etc., disposed around the rotor 202. Alternatively or additionally, the stator 308 may be implemented using a sealed housing, a carrier, and / or other stationary structure. Figure 3A In the example shown, stator 308 is located near and partially surrounds damper section 300. Figure 3A In the example shown, stator 308 includes a first stator surface 320 adjacent to arm 310 and abutting against piston rod 318. In some examples, piston rod 318 and first film interface 212 form a seal (e.g., restricting fluid flow) between first region 321A and second region 321B (e.g., between damper body 302 and first stator surface 320, etc.). Piston rod 318 may be implemented by an elastomer, metal, and / or flexible member disposed within groove 316 via interface engagement.

[0040] exist Figure 3A In the example shown, stator 308 includes a second stator surface 322 opposite to the first stator surface 320. Figure 3A In the example shown, the second stator surface 322 is adjacent to (e.g., close to) the interface plate 304. Figure 3AIn the example shown, stator 308 includes second internal conduits 324 that extend through stator 308 and fluidly connect first region 321A and second region 321B. The second internal conduits 324 guide air through stator 308 and out through orifices on second stator surface 322. High-pressure air flowing through the second internal conduits 324 forms a second thin-film interface 326 between the second stator surface and interface plate surface 327. The second thin-film interface 326 counteracts axial forces to maintain separation between stator 308 and damper section 300, thereby reducing radial friction between them. The second thin-film interface 326 facilitates radial movement of damper body 302. In some examples, if damper section 300 is sealed and a pressure difference exists between first region 321A and second region 321B, air may be forced through the second internal conduits 324 by that pressure difference. In some such examples, forces related to the pressure difference between regions 321A and 321B and related to the second membrane interface 326 maintain the axial position of the damper section 300 and the rotor 202 (e.g., the second membrane interface 326 axially positions the damper section 300, etc.). In other examples, if the damper assembly 200 is not a seal, the second internal duct 324 may be coupled to a pressurized air source (e.g., bleed air from a gas turbine engine 110, compressor, etc.), thereby similarly generating the second membrane interface 326.

[0041] Figure 3B This is a cross-sectional view of an example second damper segment 360, including a first pressurized air source 362A and a second pressurized air source 362B. Figure 3B The second damper segment 360 in the middle and Figure 3A The damper section 300 is similar, unless otherwise stated. Figure 3A and Figure 3B The same reference label in the text corresponds to the same or similar parts. Figure 3B In the example shown, a first compressed air source 362A feeds (e.g., provides pressurized air to) a first tube 364 (e.g., a first feed tube, a first flexible tube). The first tube 364 is fluidly connected to a second internal conduit 324 via a first connector 366. Figure 3B In the example shown, the second compressed air source 362B feeds (e.g., provides pressurized air to) the second tube 368 (e.g., a second feed tube, a second flexible tube). The second tube 368 is fluidly connected to the first internal conduit 314 via a second connector 370. In some examples, the first compressed air source 362A and the second compressed air source 362B may correspond to the same or different sources (e.g., Figure 1 (The bleed air from the gas turbine engine 110, independent compressor, etc.). Figure 3BIn the example shown, the first region 321A and the second region 321B are at substantially the same pressure (e.g., a first pressure, etc.). In some such examples, the second pressure of the first compressed air source 362A and the third pressure of the second compressed air source 362B are greater than the first pressure of regions 321A and 321B.

[0042] Back Figure 3A The first thin-film interface 212 and the second thin-film interface 326 are substantially orthogonal (e.g., the first thin-film interface 212 is parallel to the axial axis, the second thin-film interface 326 is parallel to the radial axis, etc.). In some examples, the second internal conduit 324 and the second thin-film interface 326 may not be present. In some examples, the interface between the interface plate surface 327 of the interface plate 304 and the second stator surface 322 can be achieved by one or more flexible members (e.g., elastomers, springs, etc.). In some such examples, the stator 308 and the damper segment 300 may include additional interfaces for axially positioning the damper segment 300.

[0043] exist Figure 3A In the example shown, stator 308 includes a stator flange 328 extending from a second stator surface 322. The stator flange 328 extends parallel to the damper flange 312 of the damper segment 300 toward the arm 310. Figure 3A In the example shown, damper section 300 also includes a spring 329 extending between damper flange 312 of damper section 300 and stator flange 328 of stator 308. Spring 329 supports damper section 300 and elastically connects damper section 300 to stator 308. Spring 329 applies a radial force to stator 308 and damper section 300, thereby radially positioning damper section 300 and maintaining radial clearance 210 between damper body 302 and rotor 202. In some examples, spring 329 is a coil spring that applies a positive radial force to damper section 300 and biases damper section 300 away from rotor 202. In some such examples, spring 329 may be radially arranged inside stator flange 328. In other examples, in addition to Figure 3A In addition to or as a substitute for spring 329, one or more different types of springs (e.g., locking springs, etc.) may be used.

[0044] Figure 3C This is a cross-sectional view of an example third damper segment 380, including a clamping spring 382. Figure 3C The third damper section 380 in the middle and Figure 3A The damper section 300 is similar, unless otherwise stated. Figure 3A and Figure 3C The same reference label in the text corresponds to the same or similar parts. Figure 3CIn the example shown, the third damper segment 380 includes an example damper body 384 that includes a recess 386 (e.g., a spring retainer recess) for receiving and / or allowing a spring retainer 382 to be in place. In some examples, the spring retainer 382 may extend into... Figure 2 Between multiple damper segments 204 of the damper assembly 200 (e.g., in the circumferential direction C, etc.), to pull and / or bias the multiple damper segments radially inward toward the rotor 202. Figure 3A The intermediate spring 329 connects the damper body 302 (e.g., via damper flange 312) and the stator 308 (e.g., via stator flange 328) differently. Figure 3C In the example shown, the clamping spring 382 connects to an adjacent segment of the damper segment 204 (e.g., in the circumferential direction C). Figure 3C In the example shown, the clamping spring 382 does not apply a spring force connection between the third damper section 380 and the stator 308.

[0045] Back Figure 3A The first internal conduit 314 guides air through the damper body 302 and out through a hole on the inner surface 209. It should be noted that the first internal conduit 314 of the damper body 302 includes additional flow paths extending to the inner surface 209, these flow paths... Figure 3A It is not visible in the cross-section. High-pressure air flows through the first internal duct 314 to form... Figure 2 The first thin-film interface 212 in the damper section 300 allows radial force to be transmitted between the damper body 302 and the rotor 202, and maintains the radial clearance 210 between them. That is, the first thin-film interface 212 allows the damper body 302 of the damper section 300 to travel with the radial movement of the rotor 202 (e.g., due to vibration of the rotor 202), preventing direct contact between the damper section 300 and the rotor 202, and not inhibiting the rotation of the rotor 202. In some examples, if the damper assembly 200 is a seal and there is a pressure difference between the first region 321A and the second region 321B, air is forced through the first internal conduit 314 via this pressure difference. In other examples, if the damper assembly 200 is not a seal, the first internal conduit 314 can be connected via a flexible conduit (e.g., an elastomer tube, a bellows, a ribbon-wound tube, etc.) to a pressurized air source (e.g., the bleed airflow from a gas turbine engine 110, a compressor, etc.) (e.g., as described above). Figure 3B (as described above). In some such examples, the flexible conduit facilitates the radial travel of the damper segment 300.

[0046] Rotor 202 may vibrate and / or travel radially during operation. For example, when rotor 202 rotates in the circumferential direction C, rotor 202 may expand (e.g., in the radial direction R) due to centrifugal growth and / or temperature changes in rotor 202. Additionally or alternatively, the radial dimension of rotor 202 may change in the circumferential direction C (e.g., due to manufacturing tolerances and / or misalignment between components of gas turbine engine 110), which may cause rotor 202 to vibrate during operation. Additionally or alternatively, if rotor 202 is a component of gas turbine engine 110, changes in gas flow through gas turbine engine 110 may similarly cause rotor 202 to vibrate. In some examples, rotor 202 may vibrate due to rotational weight imbalance about the axial direction A. The first thin-film interface 212 and spring 329 enable the damper body 302 of damper section 300 to follow and / or ride on the surface of rotor 202 and transmit vibrations of rotor 202 to damper section 300.

[0047] To dampen vibrations transmitted from rotor 202, damper section 300 includes an example damper 330 implemented according to the teachings of this disclosure. Figure 3A In the example shown, the damper 330 includes a housing 332 that defines a chamber 334, a plunger 336, a member 338, and a plurality of damper springs 340. Figure 3A In the example shown, chamber 334 is filled with damping medium 342. Figure 3A In the example shown, a gap 343 is defined between the plunger 336 and the housing 332. Figure 3A In the example shown, chamber 334 includes a first inner surface 344A (e.g., a bottom inner surface, a radially inward inner surface, etc.), a second inner surface 344B (e.g., a top inner surface, a radially outward inner surface, etc.), a third inner surface 344C (e.g., a first axial inner surface, etc.) and a fourth inner surface 344D (e.g., a second axial inner surface, etc.).

[0048] exist Figure 3A In the example shown, chamber 334 is defined by the inner surface of housing 332 (e.g., inner surfaces 344A, 344B, 344C, 344D, etc.) and filled with damping medium 342. Figure 3AIn the examples shown, the housing is closed (e.g., all surfaces are closed, etc.). In some examples, housing 332 is hermetically sealed. That is, air from the environment surrounding damper 330 (e.g., air from the second region 321B, etc.) cannot enter chamber 334, nor can damping medium 342 escape from chamber 334. In some examples, housing 332 is a single integral part (e.g., manufactured via additive manufacturing, etc.), in which plunger 336, damping medium 342, and damper spring 340 are arranged during the manufacturing process. In other examples, housing 332 may be a multi-part assembly including one or more seals to prevent air from flowing into chamber 334 and / or damping medium 342 from flowing out of chamber 334. In other examples, housing 332 may include one or more openings that allow fluid communication between chamber 334 and the second region 321B.

[0049] exist Figure 3A In the example shown, damping medium 342 is disposed within housing 332. Damping medium 342 resists the relative movement of plunger 336 and housing 332 and dissipates the energy generated therefrom. In some examples, damping medium 342 is a liquid (e.g., oil, water, silicon-based damping fluid, etc.). In other examples, damping medium 342 can be a gas (e.g., ambient air, pressurized gas, etc.), oil, hydraulic fluid, aerogel, and / or particulate solid (e.g., powder, etc.).

[0050] The plunger 336 is a generally planar member configured to move within the chamber 334. During operation and movement of the housing 332, a damper spring 340 transfers energy to the plunger 336, causing the plunger 336 to move within the housing 332. The plunger 336 is disposed within the chamber 334. Figure 3A In the example shown, plunger 336 has the same shape as housing 332 and chamber 334 (e.g., rectangular, etc.). In other examples, plunger 336 may have a different shape than housing 332 and / or chamber 334. For example, the edges of plunger 336 may be rounded, chamfered, and / or otherwise smoothed. Additionally or alternatively, the surface of plunger 336 may also be treated (e.g., smoothed, roughened, etc.) to alter the friction associated with the flow of damping medium 342 on plunger 336. Figure 3A In the example shown, the position of plunger 336 within chamber 334 forms a gap 343 between the third inner surface 344C and the fourth inner surface 344D. In some examples, one or both gaps 343 are absent (e.g., plunger 336 abuts or nearly abuts one or both of the inner surfaces 344C, 344D, etc.). In some such examples, plunger 336 may include one or more openings (e.g., through-holes, etc.) to allow the damping medium 342 to flow through.

[0051] Component 338 is a rigid member (e.g., an arm, rod, etc.) that extends between the damper flange 312 and the outer surface 348 of the housing 332. Component 338 rigidly connects the damper flange 312 to the housing 332. The rigid connection between the damper body 302 and the housing 332 via component 338 allows the housing 332 to travel with the radial movement of the damper body 302 and the rotor 202 (e.g., radial vibrations are transmitted from the rotor 202 to the damper body 302 via the first thin-film interface 212, etc.). In some examples, component 338 is integrally formed with the housing 332 and / or with the damper flange 312. In some such examples, component 338 may be connected to the housing 332 and / or the damper flange 312 via one or more welds, one or more fasteners, and / or one or more interference fits. In other examples, housing 332, damper body 302, and component 338 are a single integral part (e.g., manufactured via additive manufacturing or the like).

[0052] The damper spring 340 connects the plunger 336 to the housing 332 and transmits radial forces from the housing 332 to the plunger 336. The non-rigid connection between the plunger 336 and the housing 332 (e.g., via the damper spring 340, etc.) causes the radial movement of the plunger 336 to differ from the radial movement of the housing 332. That is, the damper spring 340 causes the plunger 336 to move radially relative to the housing 332 (e.g., the movement of the plunger 336 lags behind the movement of other components of the damper section 300, etc.). Figure 3A In the example shown, the damper spring 340 is a coil spring. In other examples, one or more damper springs 340 may be implemented by different types of springs (e.g., coil springs, leaf springs, disc springs, leaf springs, etc.). Figure 3A In the example shown, the damper spring 340 extends from the first inner surface 344A to the plunger 336. In other examples, one or both of the damper springs 340 extend from the second inner surface 344B to the plunger 336. Figure 3A In the example shown, damper 330 includes two springs (e.g., damper spring 340, etc.) extending from the first inner surface 344A. In other examples, damper 330 includes one and / or more springs extending from one or both of the inner surfaces 344A, 344B to the plunger 336. Although Figure 3A The diagram depicts an example internal configuration of the damper 330 (e.g., the geometry of the housing 332, plunger 336, damper spring 340, and clearance 343, etc.), but it should be understood that the damper 330 can have other internal configurations. The following section combines... Figure 6 Another example of the internal configuration of damper 330 is described.

[0053] The rigid radial connection between the housing 332 and the damper body 302 allows the housing 332 to move radially together with the damper body 302 and the rotor 202. Thus, vibrations of the rotor 202 are transmitted to the housing 332 through the damper body 302. Since the plunger 336 is not rigidly connected to the housing 332, the movement of the housing 332 relative to the plunger 336 forces the damping medium 342 around the plunger 336 and through the gap 343. Furthermore, the damper spring 340 extends and / or contracts accordingly, thereby applying a spring force to the plunger 336 to prevent the plunger 336 from contacting the first inner surface 344A and the second inner surface 344B. Frictional forces and / or resistances associated with the relative flow of the damping medium 342 around the plunger 336 (e.g., the movement of the plunger 336 within the damping medium 342, etc.) and the spring force associated with the damper spring 340 cause a phase difference (e.g., hysteresis, slight delay, etc.) between the radial movement of the plunger 336 (e.g., vibration, etc.) and the radial movement of the rotor 202. The compression of the damping medium 342 and the associated phase hysteresis of the plunger 336 dissipate energy from the radial vibration of the rotor 202 and suppress its radial vibration, thereby reducing the total radial travel of the rotor 202. (The following is in conjunction with...) Figure 4 The damping characteristics of damper 330 are described in more detail.

[0054] exist Figure 3A In the example shown, the damper section 300 also serves as a seal between the first region 321A and the second region 321B. That is, the damper section 300 restricts fluid flow and / or leakage (e.g., from a high-pressure region to a low-pressure region, etc.) between the first region 321A and the second region 321B. Figure 3A In the example shown, the damper segment 300 includes a lip 349 (e.g., a tooth, seal, etc.) extending radially inward from the damper body 302 and defining a gap 350 between the damper body 302 and the rotor 202. Figure 3A In the example shown, the lip 349 is integral with the damper body 302. In other examples, the lip 349 is a separate component connected to the damper body 302 via one or more fasteners, one or more welds, and / or one or more interference fits. During operation of the rotor 202 and damper section 300, flow between the first region 321A and the second region 321B is restricted by the gap 350, resulting in a lower pressure in the interior 354 between the rotor 202 and the damper body 302 compared to the pressure in the second region 321B. The relatively lower pressure in the interior 354 and the second region 321B compared to the first region 321A facilitates airflow through the first internal conduit 314 and the formation of the first thin-film interface 212. The first thin-film interface 212 and the piston rod 318 restrict (e.g., prevent, etc.) airflow through the damper section 300, enabling the damper section 300 to function as a seal.

[0055] In other examples, damper section 300 suppresses vibrations of rotor 202 and does not seal the second region 321B from the first region 321A. For example, regions 321A and 321B may have approximately the same pressure (e.g., no pressure difference between regions 321A and 321B, etc.). In these examples, damper section 300 (and Figure 2 The entire damper assembly 200 (e.g., does not restrict (e.g., block, inhibit, etc.) airflow between regions 321A, 321B. In some such examples, damper section 300 does not include piston rod 318, lip 349 and / or other features (e.g., such as...). Figure 3B (As shown in the diagram). In some examples, the damper segment 300 includes one or more flexible conduits coupled to the internal conduits 314, 324 (e.g., Figure 3B (e.g., tubes 364, 368, etc.), thereby facilitating the generation of thin film interfaces 212, 326. In other examples, the second thin film interface 326 is absent, and the damper segment 300 can be axially positioned via one or more other features (e.g., fasteners, surfaces, etc.).

[0056] Figure 4 yes Figure 2 The damper assembly 200 and Figure 2 A schematic diagram of rotor 202. Figure 4 In the example shown, the damper assembly 200 is positioned at mid-span 400 on the rotor 202. Figure 4 In the example shown, rotor 202 is supported by a first bearing 402A and a second bearing 402B. Figure 4 In the example shown, a first bearing 402A and a second bearing 402B are respectively disposed at a first end 404A and a second end 404B of the rotor 202. Bearings 402A and 402B support the rotor 202 and transmit radial forces associated with the rotor 202 (e.g., radial forces related to the imbalance of the rotor 202, the weight of the rotor 202, etc.) to stationary components (e.g., the ground, etc.). Figure 1 (The casing of the gas turbine engine 110, etc.). Figure 4 In the example shown, the mid-span position 400 is axially located between the first bearing 402A and the second bearing 402B. That is, unlike previous dampers, the damper assembly 200 is not limited to being integrated into bearings 402A and 402B. Therefore, the damper assembly 200 can be placed at the mid-span position 400 on the rotor 202 (e.g., a non-bearing position, etc.). Figure 4In the example shown, the mid-span position 400 is located at the intermediate position (e.g., axial center, midpoint, etc.) between bearings 402A, 402B and ends 404A, 404B. That is, the mid-span position 400 is equidistant from bearings 402A, 402B and ends 404A, 404B. In other examples, the mid-span position 400 can be located at any other position on the rotor 202. In some such examples, because the radial travel amplitude at the mid-span on the rotor 202 is generally greater than that at the ends 404A, 404B, placing the damper assembly 200 at the mid-span position 400 provides a greater damping effect than a damper (e.g., a squeeze-film damper, etc.) previously incorporated into the bearing positions of bearings 402A, 402B.

[0057] Figure 5A yes Figure 3A A simplified cross-sectional view of the intermediate damper 330. Figure 5A yes Figure 3A Medium damper 330 along Figure 5A A simplified cross-sectional view of the BB line. Figure 5A and Figure 5B In the example shown, damper 330 includes Figure 3A 332 of the shell Figure 3A plunger 336, Figure 3A Damper spring 340 and Figure 3A The damping medium is 342. Figure 5B In the example shown, the damper 330 has a vertical center 502. Figure 5B In the example shown, the top surface 504 of the plunger 336 has an area 506 (A), the plunger 336 has a first radius 508 (r1), and the housing 332 has a second radius 510 (e.g., inner radius) (r2). Figure 5A In the example shown, plunger 336 has a thickness of 512 (L). Figure 5A In the example shown, the radial position of plunger 336 is defined by the first function 514. Figure 5A In the example shown, housing 332 and other parts rigidly connected to it (e.g., Figure 3A The radial position of the damper assembly 200 and other components is defined by the second function 516.

[0058] The damping coefficient of damper 330 and damper assembly 200 (e.g., comprising multiple segments, each segment having damper 330, etc.) depends on the material properties of damping medium 342 (e.g., the dynamic viscosity of damping medium 342, etc.) and the geometry of the damper segments (e.g., the area 506 of plunger 336, the thickness 512 of plunger 336, the first radius 508 of plunger 336, and the second radius 510 of housing 332, etc.). For example, the damping coefficient associated with damper 330 is given by the following equation:

[0059] (1),

[0060] Where c is the damping coefficient, A is the area 506 of the plunger 336, μ is the dynamic viscosity of the damping medium 342, L is the thickness 512 of the plunger 336, r1 is the first radius 508, and r2 is the second radius 510.

[0061] The motion of damper 330 is defined by the following equation:

[0062] = (2),

[0063] in, z is the mass of plunger 336, and z is the position of plunger 336 as a function of time (e.g., the first function 514, etc.). It is the radial velocity of the plunger 336 as a function of time (e.g., the first derivative of the first function 514, etc.). is the radial acceleration of plunger 336 as a function of time (e.g., the second derivative of the first function 514, etc.), and c is the damping coefficient of damper 330. y is the spring constant of the damper spring 340, and y is the position of the housing 332 as a function of time (e.g., a second function 516, etc.). It is the radial velocity of the shell 332 as a function of time (e.g., the first derivative of the second function 516, etc.). Figure 5A In this equation, since the housing 332 is rigidly connected to the damper body 302, y also represents the position of the damper body 302. The motion of the damper body 302 is defined by the following equation:

[0064] = (3),

[0065] in, It is the mass of the casing 332. It is the radial acceleration of the damper body 302 as a function of time (e.g., the second derivative of the second function 516, etc.). F(t) is the spring constant of spring 329, and F(t) is the force exerted by the first thin film interface 212 on the rotor 202 and the damper body 302.

[0066] exist Figure 5B In the example shown, housing 332 and plunger 336 have circular cross-sections. In other examples, housing 332 and plunger 336 may have other cross-sectional geometries (e.g., oval, polygonal, etc.). Additionally or alternatively, damper 330 may comprise damper springs 340 in different configurations. It should be understood that equations (1), (2), and (3) depend on the geometry of housing 332 and plunger 336, if the geometry of housing 332 and plunger 336 is different from that of housing 332 and plunger 336. Figure 5A and Figure 5B If the geometric shape is different, then equations (1), (2) and (3) will change.

[0067] Figure 6 yes Figure 3A An example of the intermediate damper 330 replaces the internal configuration 600. Figure 6 In the example shown, the alternative internal configuration 600 is set with Figure 3A The housing 332 includes Figure 3A First inner surface 344A, Figure 3A The second inner surface 344B Figure 3A The third inner surface 344C and Figure 3A The fourth inner surface 344D. In Figure 6 In the example shown, the alternative internal configuration 600 includes a plunger 602. Figure 6 In the example shown, plunger 602 is connected to damper spring 340. Figure 3A The first inner surface 344A. In other examples, the plunger 602 may be coupled to one or more of the inner surfaces 344A, 344B, 344C, and 344D via different spring combinations. Figure 6 In the example shown, plunger 602 includes a first hole 604A and a second hole 604B. Holes 604A and 604B are through holes extending through plunger 602. Figure 6 In the example shown, plunger 602 includes two holes (e.g., holes 604A, 604B, etc.). In other examples, plunger 602 may have additional holes (e.g., holes axially aligned with holes 604A, 604B, holes arranged at different circumferential positions than holes 604A, 604B, etc.).

[0068] Figure 7 This is a cross-sectional view of another example damper segment 700, which can be implemented. Figure 2 One of the damper segments 204, and implemented in accordance with the teachings of this disclosure. Unless otherwise stated, damper segment 700 and Figure 3A Similar to damper section 300 in the above. Similar to damper section 300, Figure 2 Damper section 204 and Figure 7 The implementation of the damper section 700 in the middle makes Figure 2 The damper assembly 200 can be positioned at the mid-span of the rotor 202 (e.g., not at the bearing location, etc.). Figure 7 In the example shown, damper segment 700 is via Figure 2 and Figure 3A The first thin film interface 212 and Figure 2 The rotor 202 is engaged and set in Figure 3A Between the first region 321A (e.g., a high-pressure region, etc.) and the second region 321B (e.g., a low-pressure region, etc.). Figure 7 In the example shown, damper segment 700 engages with the first stator 701A and the second stator 701B. Figure 3A Similar to stator 308, one or both of stators 701A and 701B are part of the housing of the gas turbine engine 110 that houses rotor 202, or a stationary disk, etc., arranged around rotor 202. Additionally or alternatively, one or both of stators 701A and 701B may also be implemented by means of a sealed housing, carrier, and / or other stationary structure. Figure 7 In the example shown, stators 701A and 701B are discrete, separate components. In other examples, stators 701A and 701B are a single, integral component.

[0069] exist Figure 7 In the example shown, damper section 700 seals (e.g., restricts, blocks, etc.) the airflow between regions 321A and 321B. That is, damper section 700 is also a sealed section. In other examples, damper section 700 does not act as a seal (e.g., it does not restrict airflow between regions 321A, 321B, etc.), but only dampes the radial vibration of rotor 202 and / or damper body 702. Figure 7 In the example shown, damper segment 700 includes a damper body 702, which includes a first body portion 704A, a second body portion 704B, a third body portion 704C, and a fourth body portion 704D. Figure 7In the example shown, the damper body 702 is a single integral (e.g., monolithic) component (e.g., body portions 704A, 704B, 704C, 704D are part of a single monolithic component, etc.). In other examples, the damper body 702 is an assembly composed of multiple discrete components. For example, each of body portions 704A, 704B, 704C, 704D may be a separately manufactured discrete component, joined via one or more welds, one or more fasteners, one or more interference fits, etc. Additionally or alternatively, the damper body 702 may contain any number of suitable components (e.g., some or all of body portions 704A, 704B, 704C, 704D may be composed of multiple discrete components, etc.).

[0070] exist Figure 7 In the example shown, the first body portion 704A is adjacent to the rotor 202 and includes Figure 3A The first internal conduit 314. In Figure 7 In the example shown, the first body portion 704A is radially located inside the second body portion 704B and the fourth body portion 704D. Figure 3A Similar to the damper section 300, the first thin-film interface 212 is generated by pressurized air flowing through the first internal conduit 314 and exiting from the opening in the first body portion 704A onto the rotor 202. Figure 7 In the example shown, the damper segment 700 includes a lip 706 (e.g., a tooth) that extends radially inward from the first body portion 704A and forms a gap 708 between the damper body 702 and the rotor 202. The lip 706 and... Figure 3A The lip 349 is similar, unless otherwise stated. During operation of the rotor 202 and damper section 700, flow between the first region 321A and the second region 321B is restricted by the gap 708, resulting in a lower pressure in the interior 709 between the rotor 202 and the first body portion 704A of the damper body 702 compared to the pressure in the second region 321B. The relatively lower pressure in the interior 709 and the second region 321B compared to the first region 321A facilitates airflow through the first internal duct 314 and the formation of the first thin-film interface 212. In these examples, pressurized airflow is induced through the first internal duct 314 via the pressure difference between the first region 321A and the second region 321B. In other examples, pressurized airflow is induced through the first internal duct 314 via a flexible duct coupled to the first internal duct 314 and a compressed air source (e.g., bleed air from a gas turbine engine 110, compressor, etc.). Figure 7 In the example shown, rotor 202 does not include Figure 3AThe rotor flange 301 is in the rotor body. In other examples, the rotor 202 includes the rotor flange 301, and the shape of the first body portion 704A of the damper body 702 is similar to the shape of the damper body 302 (e.g., the shape is adapted to the rotor flange 301, etc.).

[0071] The second body portion 704B extends radially between the first body portion 704A and the fourth body portion 704D. Figure 7 In the example shown, the second body portion 704B is radially located between the first body portion 704A and the fourth body portion 704D. The second body portion 704B connects the first body portion 704A and the third body portion 704C. Figure 7 In the example shown, the second body portion 704B includes Figure 3A The piston rod 318, which is set in Figure 3A In slot 316. Figure 7 In the example shown, piston rod 318 contacts (e.g., abuts, engages, etc.) the second stator 701B. Piston rod 318, in conjunction with the first thin-film interface 212, fluidly seals the first region 321A and the second region 321B. In some examples, friction between piston rod 318 and the second stator 701B suppresses (e.g., via frictional damping, etc.) the damper section 700 and the rotor 202 during the radial travel of the damper section 700.

[0072] The third body section 704C axial support damper section 700. In Figure 7 In the example shown, the third body portion 704C is adjacent to (e.g., close to) the first stator 701A. Figure 7 In the example shown, the first stator 701A includes a second internal conduit 710. In Figure 7 In the example shown, the second internal conduit 710 extends through the first stator 701A and fluidly connects the first region 321A and the second region 321B. The second internal conduit 710 guides air through the first stator 701A and out through its orifices. The high-pressure air flowing through the second internal conduit 710 forms a second thin-film interface 711 between the surface of the second stator and the body surface 713 of the third body portion 704C. The second thin-film interface 711 counteracts axial forces to maintain separation between the first stator 701A and the damper body 702 (e.g., axially positioning the damper body 702, etc.), thereby reducing radial friction between them. The second thin-film interface 711 facilitates radial movement of the damper body 702. In some examples, if the damper section 700 is a seal and there is a pressure difference between the first region 321A and the second region 321B, air may be forced through the second internal conduit 710 via the pressure difference therebetween. In other examples, air may be transmitted via a flexible conduit (e.g., similar to...). Figure 3BThe flexible conduits (such as tubes 364 and 368) are guided into the second internal conduit 710.

[0073] In some examples, the second thin-film interface 711 is absent. In some such examples, the body surface 713 of the third body portion 704C and the first stator 701A may be coupled to and / or abut against the body surface 713 and the first stator 701A. In some such examples, the abutment of the third body portion 704C with the first stator 701A and the abutment of the second body portion 704B with the second stator 701B axially positions (e.g., constrains, etc.) the damper segment 700. Figure 7 In the example shown, the third body portion 704C is supported by another portion of the damper body 702 and extends circumferentially (e.g., outward from the page) from that other portion of the damper body 702. In other examples, the third body portion 704C may be via a rigid member (e.g., similar to...). Figure 3A The components 306, etc. are connected to the first body part 704A.

[0074] The fourth body portion 704D is located radially outside the first body portion 704A and the second body portion 704B. Figure 7 In the example shown, the fourth body portion 704D is a flange extending axially from the second body portion 704B. Figure 7 In the example shown, the fourth body portion 704D is connected to member 712, which extends radially inward from the fourth body portion 704D toward the rotor 202. Figure 7 In the example shown, member 712 extends between the fourth body portion 704D and the plunger 714. Member 712 rigidly connects the plunger 714 to the fourth body portion 704D of the damper body 702. Figure 7 In the example shown, component 712, plunger 714, and fourth body portion 704D are a single, integral part. In other examples, component 712 may be rigidly connected to plunger 714 and / or fourth body portion 704D via one or more fasteners, one or more welds, one or more interference fits, etc. Figure 7 In the example shown, the first stator 701A includes a second internal conduit 710 and a housing 718. Figure 7 In the example shown, housing 718 is coupled to cover 720, and cover 720 includes seal 722. Figure 7 In the example shown, housing 718 and cover 720 define chamber 724. Figure 7 In the example shown, the housing 718 is closed (e.g., all surfaces are closed, etc.). Figure 3AIn the example shown, chamber 724 is filled with a damping medium 726. In some examples, the damping medium 726 includes pressurized air, oil, hydraulic fluid, powder, and / or aerogel. To suppress vibrations transmitted from rotor 202, damper section 700 includes an example damper 727 implemented according to the teachings of this disclosure. Figure 7 In the example shown, the damper 727 includes a component 712, a plunger 714, a second internal conduit 710, a housing 718, and a chamber 724. The damper 727 is related to... Figure 3A The damper 330 is similar, unless otherwise stated.

[0075] exist Figure 7 In the example shown, member 712 extends from the fourth body portion 704D, passes through cover 720 and seal 722, and enters chamber 724. In some examples, seal 722 is an elastomeric seal (e.g., O-ring, etc.) that allows radial translation of member 712 (e.g., with radial translation of rotor 202 and damper body 702, etc.) and restricts (e.g., blocks, reduces, etc.) damper fluid flow through cover 720. Figure 7 In the example shown, chamber 724 is sealed by housing 718 and seal 722. That is, the damping medium 726 of damper 727 cannot enter the second region 321B. Figure 7 In the example shown, housing 718 is a single integral component (e.g., integrally formed with the first stator 701A). In other examples, housing 718 may be multiple discrete components assembled together. In some such examples, chamber 724 may include one or more additional seals to prevent air from flowing into chamber 724 and / or damping medium 726 from flowing out of chamber 724.

[0076] The plunger 714 is disposed within the chamber 724. Figure 3A Unlike plunger 336, plunger 714 is not connected to the housing 718 of the chamber (e.g., excluding...). Figures 3A-3C Instead of the damper spring 340 in the above, it is rigidly connected to the damper body 702 via component 712. That is, the plunger 714 travels in the same phase as the radial travel of the damper body 702. Figure 7 In the example shown, plunger 714 and chamber 724 have the same shape (e.g., rectangular, etc.). In other examples, the shape of plunger 714 may differ from that of chamber 724. For example, the edges of plunger 714 may be rounded, chamfered, and / or otherwise smoothed, and / or the surface of plunger 714 may be treated (e.g., smoothed, roughened, etc.) to alter the friction associated with the flow of damping medium 726 on plunger 714. Figure 7In the example shown, plunger 714 includes example openings 728 that extend through plunger 714 (e.g., openings 728 are through holes, etc.). Additionally or alternatively, the position of plunger 714 within chamber 724 forms a gap with housing 718 (e.g., similar to...). Figure 3A (Gap 343, etc.).

[0077] The rigid radial connection between plunger 714 and damper body 702 allows plunger 714 to move radially together with damper body 702. Vibrations of rotor 202 are transmitted through member 712 through damper body 702 to plunger 714. Vibrations cause plunger 714 to move radially relative to first stator 701A, thereby forcing damping medium 726 through opening 714. Friction associated with the movement of damping medium 726 on plunger 714 and through opening 728 heats damping medium 726 and dissipates energy from vibrations of damper body 702 and rotor 202. Energy dissipation associated with damper 727 suppresses vibrations of damper body 702 and rotor 202, thereby reducing the total radial travel of rotor 202 (e.g., the amplitude of rotor 202 oscillations).

[0078] As will be understood from the above, several example systems, apparatuses, articles, and methods have been disclosed that can reduce (e.g., suppress, dissipate) vibrations of the rotor in a mechanical device (e.g., a gas turbine engine). Examples disclosed herein include a diaphragm-riding damper assembly with multiple damper segments, which reduces the amplitude of rotor oscillations and prevents potential damage to components associated with rotor oscillations. The example dampers disclosed herein are not limited to those incorporated into bearings but can also be positioned at the mid-span of the rotor. Therefore, the dampers disclosed herein can be located at locations on the rotor where high oscillation amplitudes occur. Arranging the damper at the mid-span position can enhance the damping effect provided by the damper assembly. Therefore, the disclosed systems, apparatuses, articles, and methods are intended for one or more improvements in the operation of machines and / or mechanical devices.

[0079] Further aspects of this disclosure are provided by the subject matter of the following clauses:

[0080] A damper assembly for a rotor, the damper assembly comprising: a body including: a first surface forming a first thin film interface with the rotor; a second surface forming an interface with a stator; and a damper rigidly coupled to the body, the damper including: a closed housing including a damping medium; and a plunger located within the housing.

[0081] According to any of the preceding clauses, the damper assembly wherein the housing is hermetically sealed.

[0082] The damper assembly according to any of the foregoing clauses further includes a first spring extending between the plunger and the inner surface of the housing.

[0083] The damper assembly according to any of the foregoing clauses further includes a second spring extending between the body and the stator.

[0084] The damper assembly according to any of the foregoing clauses, wherein the damper assembly is configured to be disposed between a high-pressure region and a low-pressure region, and the body further includes an internal conduit extending between the first surface and the high-pressure region.

[0085] The damper assembly according to any of the foregoing clauses further includes: an internal conduit extending from the first surface; and a flexible conduit coupled to the internal conduit.

[0086] The damper assembly according to any of the foregoing clauses, wherein the first surface and the second surface are substantially orthogonal.

[0087] The damper assembly according to any of the foregoing clauses further includes a member that rigidly connects the damper to the body, the member extending between the outer surface of the housing and the body.

[0088] The damper assembly according to any of the foregoing clauses further includes a member that rigidly connects the damper to the body, the member extending between the plunger and the body, and the member extending through the housing.

[0089] According to any of the preceding clauses, the damper assembly wherein the plunger is spaced apart from the inner surface of the housing.

[0090] A gas turbine engine includes: a shaft; and a damper assembly, the damper assembly including: a body, the body including: a first surface forming a first thin film interface with the shaft; and a second surface forming an interface with a stator; and a damper rigidly coupled to the body, the damper including: a closed housing including a damping medium; and a plunger located within the housing.

[0091] The gas turbine engine according to any of the preceding clauses further includes: a first bearing for supporting the shaft at a first end; and a second bearing for supporting the shaft at a second end, the damper being disposed at a mid-span position of the shaft located between the first bearing and the second bearing.

[0092] In any of the preceding clauses, the gas turbine engine wherein the housing is hermetically sealed.

[0093] The gas turbine engine according to any of the foregoing clauses further includes a first spring extending between the plunger and the inner surface of the housing.

[0094] The gas turbine engine according to any of the foregoing clauses further includes a second spring for biasing the damper assembly toward the shaft.

[0095] The gas turbine engine according to any of the foregoing clauses, wherein the first surface and the second surface are substantially orthogonal.

[0096] The gas turbine engine according to any of the foregoing clauses further includes a component that rigidly connects the damper to the body, the component extending between the outer surface of the housing and the body.

[0097] The gas turbine engine according to any of the foregoing clauses further includes a component that rigidly connects the damper to the body, the component extending between the plunger and the body, and the component extending through the housing.

[0098] In any of the preceding clauses of the gas turbine engine, the plunger includes a through hole.

[0099] According to any of the preceding clauses, the gas turbine engine wherein the damper assembly is configured to be disposed between a high-pressure region and a low-pressure region, and the body further includes an internal duct extending between the first surface and the high-pressure region.

[0100] According to any of the preceding clauses, the damper assembly wherein the plunger has a surface area (A) and a thickness (L), the damping medium has a dynamic viscosity (μ), the plunger is separated from the vertical center of the damper by a first distance (r1), the housing is provided with a second distance (r2), and the damping coefficient (c) of the damper is defined by the following equation: .

[0101] According to any of the foregoing clauses, the damper assembly, wherein the damper has a first mass ( The damper has a radial position (z) and a radial velocity (z). ) and radial acceleration ( The second spring has a first spring constant ( The plunger has a radial position (y) and a radial velocity (y). Furthermore, the motion of the damper is defined by the following equation: = .

[0102] According to any of the preceding clauses, the damper assembly wherein the housing has a second mass ( The plunger has radial acceleration ( The first spring has a second spring constant ( The first thin-film interface applies a first force (F(t)) to the damper, and the motion of the body is defined by the following equation: = .

[0103] The following claims are incorporated herein by reference. While some exemplary systems, devices, articles of manufacture, and methods are disclosed herein, the scope of protection of this patent is not limited thereto. Rather, this patent covers all systems, devices, articles of manufacture, and methods that fall fully within the scope of the claims of this patent.

Claims

1. A damper assembly for a rotor, characterized in that, The damper assembly includes: The body, the body comprising: A first surface, the first surface forming a first thin film interface with the rotor; and A second surface, the second surface forming an interface with the stator; and A damper, rigidly connected to the body, the damper comprising: Enclosed housing, the enclosed housing comprising a damping medium; and A plunger located within the housing.

2. The damper assembly according to claim 1, characterized in that, in, The housing is airtight.

3. The damper assembly according to claim 1, characterized in that, It further includes a first spring that extends between the plunger and the inner surface of the housing.

4. The damper assembly according to claim 3, characterized in that, It further includes a second spring that extends between the body and the stator.

5. The damper assembly according to claim 1, characterized in that, in, The damper assembly is disposed between the high-pressure region and the low-pressure region, and the body further includes an internal conduit extending between the first surface and the high-pressure region.

6. The damper assembly according to claim 1, characterized in that, Further includes: An internal conduit extending from the first surface; and A flexible catheter, which is connected to the internal catheter.

7. The damper assembly according to claim 1, characterized in that, in, The first surface and the second surface are substantially orthogonal.

8. The damper assembly according to claim 1, characterized in that, The device further includes a component that rigidly connects the damper to the body, the component extending between the outer surface of the housing and the body.

9. The damper assembly according to claim 1, characterized in that, The device further includes a component that rigidly connects the damper to the body, the component extending between the plunger and the body, and the component extending through the housing.

10. The damper assembly according to claim 1, characterized in that, in, The plunger is spaced apart from the inner surface of the housing.

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