Bearing damper assembly for a turbine engine

Abstract

A bearing damper assembly for a turbine engine includes a damper frame and a bearing housing disposed in the damper frame. The bearing housing includes a housing base, an outer rim, and an inner rim, the outer rim coupled to the housing base via a first plurality of integral springs such that a first plurality of annular gaps are formed between the outer rim and the housing base, the inner rim coupled to the housing base via a second plurality of integral springs such that a second plurality of annular gaps are formed between the inner rim and the housing base. The first plurality of annular gaps and the second plurality of annular gaps are configured to be filled with fluid via first and second fluid circuits, respectively, of the bearing damper assembly to dampen vibrations generated on a rotating component of the turbine engine.

Description

Technical Field

[0001] This disclosure generally relates to bearing damper assemblies for turbine engines. Background Technology

[0002] For example, a turbine engine used in an aircraft typically includes a fan section and a turbocharger that drives the fan section. A turbocharger engine typically includes a compressor section, a combustion section, and a turbine section arranged in a series flow pattern. One or more bearing damper assemblies can reduce vibrations of the rotating components of a turbocharger engine. Attached Figure Description

[0003] Features and advantages of this disclosure will become apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings, wherein similar reference numerals generally denote identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 This is a schematic cross-sectional view of a turbine engine taken along the longitudinal centerline axis of the turbine engine according to an embodiment of the present disclosure.

[0005] Figure 2 A turbine engine (such as) according to embodiments of this disclosure Figure 1 A schematic diagram of an exemplary bearing damper assembly for a turbine engine.

[0006] Figure 3 It is a turbine engine (such as) according to another embodiment of this disclosure. Figure 1 A schematic cross-sectional view of the bearing damper assembly of a turbine engine.

[0007] Figure 4 yes Figure 3 A magnified cross-sectional detailed view of the area marked "4".

[0008] Figure 5 yes Figure 3 and Figure 4 Front view of the bearing housing of the bearing damper assembly.

[0009] Figure 6 yes Figure 5 A magnified detailed view of the area marked "6".

[0010] Figure 7 yes Figure 5 A magnified detailed view of the area marked "7".

[0011] Figure 8 Based on this disclosure Figures 3 to 7 A schematic cross-sectional view of the first and second fluid circuits of the bearing damper assembly.

[0012] Figure 9 It is a turbine engine (such as) according to another embodiment of this disclosure. Figure 1 A schematic cross-sectional view of the bearing damper assembly of a turbine engine.

[0013] Figure 10 yes Figure 9 A magnified cross-sectional detailed view of the area marked "10".

[0014] Figure 11 This illustrates an embodiment of the present disclosure via a bearing damper assembly (such as...) Figures 3 to 8 A flowchart of a method for damping the vibration of rotating components of a turbine engine (bearing damper assembly). Detailed Implementation

[0015] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0016] Various embodiments of this disclosure are discussed in detail below. While specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from this disclosure.

[0017] As used herein, the terms “first,” “second,” “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0018] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0019] The terms "forward" and "rearward" refer to the relative positions within the turbine engine or launch vehicle, and are based on the normal operating attitude of the turbine engine or launch vehicle. More specifically, the forward and rearward references used herein are the direction of travel of the launch vehicle and the direction of propulsion of the turbine engine.

[0020] Unless otherwise specified herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features.

[0021] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0022] As used herein, the terms "axial" and "axially" refer to the direction and orientation extending substantially parallel to the longitudinal centerline axis of the turbine engine. Furthermore, the terms "radial" and "radially" refer to the direction and orientation extending substantially perpendicular to the longitudinal centerline axis of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to the direction and orientation extending in an arc around the longitudinal centerline axis of the turbine engine.

[0023] As used herein, the term "rotating component" refers to any part of a rotating machine (such as a turbine engine) that rotates about an axis of rotation. As an example, a rotating component may include the shaft or spindle of a turbine engine, such as a fan shaft, high-pressure shaft, low-pressure shaft, etc. Similarly, as used herein, the term "static component" refers to any stationary or non-rotating component of a turbine engine that has a coaxial configuration and arrangement with the rotating components of the turbine engine. A static component may be arranged radially inward or radially outward along a radial axis relative to at least a portion of the rotating component. Additionally or alternatively, a static component may be axially arranged adjacent to at least a portion of the rotating component.

[0024] As used in this article, the term "static structure" refers to any non-rotating structural part of a rotating machine, such as a turbine engine.

[0025] As used in this article, "redline speed" refers to the maximum expected rotational speed of the shaft or rotor during normal operation of a turbine engine. Redline speed can be expressed in revolutions per second (Hz), revolutions per minute (RPM), or as the linear velocity of the shaft's outer diameter in feet per second. For turbine engines with both high-speed and low-speed shafts, both the high-speed and low-speed shafts have redline speeds.

[0026] As used herein, "critical speed" refers to the rotational speed of a turbine engine shaft or rotor that is approximately the same as the fundamental or natural frequency of the shaft's first-order bending mode (e.g., the shaft rotates at 80 Hz and the first-order modal frequency is 80 Hz). When the shaft rotates at the critical speed, the shaft is expected to have maximum deflection due to the excitation of the shaft's first-order bending mode, thus introducing instability. The critical speed can be expressed in revolutions per second (RPM) in Hz or as a linear velocity of the shaft's outer diameter in feet per second.

[0027] As used in this article, “supercritical speed” refers to the rotational speed of a turbine engine shaft or rotor above the fundamental or natural frequency of the shaft’s first-order bending mode (e.g., the shaft rotates at 80 Hz while the first-order modal frequency is approximately 70 Hz). “Supercritical shaft” refers to a shaft having a redline speed above the shaft’s critical speed.

[0028] As used herein, the term "additive manufacturing" or "additive manufacturing technology or process" generally refers to a manufacturing process in which consecutive layers of material are laid on top of each other to "build" a three-dimensional part layer by layer. Consecutive layers are often fused together to form a monolithic part that can have various integral sub-components. Although additive manufacturing technology is described herein as capable of creating complex objects by building them point-by-point, layer-by-layer (typically in the vertical direction), other manufacturing methods are possible and within the scope of this subject matter. For example, although the discussion herein involves adding material to form consecutive layers, those skilled in the art will understand that the methods and structures disclosed herein can be practiced with any additive manufacturing technology or manufacturing technique. For example, embodiments of this disclosure may use layer-addition, layer-subtraction, or hybrid processes.

[0029] As used throughout this specification and claims, approximate language is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by terms such as “about” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct a component and / or system or manufacture a component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 10%, 15%, or 20% at the endpoints of a single value, a range of values, and / or a defined range of values.

[0030] Scope limitations are combined and interchanged herein and throughout the specification and claims. Unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0031] Typically, turbine engines (e.g., turbofan engines) facilitate energy transfer between a fluid and rotating components (e.g., rotors). For example, a turbofan engine's compressor can utilize rotating components to transfer energy to a fluid by compressing it. Furthermore, turbine engines can use rotating components to extract energy from a fluid flow. To facilitate energy transfer, tangential forces can actuate (e.g., rotate) the rotating components. However, the rotating components may exert axial and radial forces on the rest of the turbine engine. For example, rotation of the rotating components can cause mass imbalances, resulting in vibrations (e.g., radial forces) within the turbine engine. Additionally, the rotating components may exert radial (e.g., downward) forces due to gravity. Furthermore, when the turbine engine is operating, the rotating components may exert axial forces (e.g., thrust).

[0032] To help cope with these different forces exerted by rotating components, turbine engines typically include one or more bearing damper assemblies that engage with one or more rotating components of the turbine engine. For example, bearing damper assemblies can dissipate vibrations generated on the rotating components (e.g., dynamic radial forces), thereby reducing vibrations transmitted to the rest of the turbine engine. Additionally, bearing damper assemblies can support the rotating components against other radial and axial forces to facilitate actuation of the rotating components. However, in some cases, adjusting the bearing damper assembly to cope with other radial and axial forces may affect the bearing damper assembly's ability to dissipate vibrations.

[0033] For example, one solution is a bearing damper assembly comprising a damper (i.e., a bearing housing) with multiple annular gaps (e.g., a segmented extruded membrane damper) and a bearing connecting the damper and a rotating component. Thus, forces applied to the rotating component can be transmitted to the damper via the bearing. For example, vibrations generated on the rotating component can propagate from the rotating component, through the bearing, and into the damper, where they can be dissipated by fluid in its annular gaps. The damping characteristics of the damper can be based at least in part on the pressure of the fluid in the annular gaps and the size of the annular gaps. For example, adjusting the fluid pressure and the annular gap size can affect the frequency of vibrations damped (e.g., dissipated) by the damper. Therefore, the fluid pressure and the annular gap size can be adjusted (e.g., tuned) to target the natural frequency of the turbine engine, which can help reduce the impact of vibrations on the rest of the turbine engine.

[0034] However, as mentioned above, rotating components may exert additional radial and axial forces on the bearing damper assembly. When insufficient counterbalancing occurs, these axial and radial forces can dynamically alter the fluid pressure and annular clearance size of the damper, thereby changing the target vibration frequency. For example, an axial force (thrust) may cause axial movement within the damper, potentially disrupting fluid flow through the axial clearance and thus disrupting the fluid pressure within the annular clearance. Additionally, radial forces (e.g., gravity) may cause radial movement within the damper, potentially decreasing the size of one annular clearance while increasing the size of the other. Therefore, to maintain the target damping characteristics (e.g., damped vibration frequency and damping capacity), the bearing assembly can counterbalance axial and radial forces to facilitate maintaining the annular clearance size and fluid pressure within the annular clearance.

[0035] Furthermore, some turbine engines may require certain rotating components (e.g., low-pressure or high-pressure shafts) to operate at supercritical speeds. Operating at supercritical speeds presents several challenges to rotor dynamics, including high-speed stability and synchronous response to rotor imbalances. Additionally, a supercritical rotor needs to traverse several rotor modes before reaching its redline operating speed. Therefore, there are optimal damping requirements for each mode and operating speed. For example, an excessively large damping force coefficient can lead to reduced stability margins and high dynamic bearing loads, and a sufficiently low damping value will have the same effect. In other words, each operating mode requires optimal damping characteristics that can be varied relative to other operating modes. However, as discussed above, conventional extruded diaphragm dampers for bearing damper assemblies are typically designed for a single target damping characteristic (e.g., with a specific integral spring stiffness, annular gap size, etc.) and do not have the ability to change the damping characteristics as needed.

[0036] Therefore, this disclosure provides an improved bearing damper assembly for a turbine engine, which can operate in multiple variable damping modes under various operating modes of the turbine engine. Specifically, embodiments of this disclosure can provide a bearing damper assembly having a first plurality of annular gaps and a second plurality of annular gaps, the second plurality of annular gaps being radially inside the first plurality of annular gaps, the first plurality of annular gaps and the second plurality of annular gaps being independently activated to provide various damping characteristics of the bearing damper assembly, which can improve the operating performance and durability of the bearing damper assembly and the turbine engine in a range of operating modes.

[0037] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 10 taken along the longitudinal centerline axis 12 of the turbine engine 10 according to an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 for reference) and a radial direction R perpendicular to the axial direction A. Generally, the turbine engine 10 includes a fan section 14 and a turbocharger engine 16 disposed downstream of the fan section 14.

[0038] The turbocharged engine 16 comprises a compressor section 21, a combustion section 26, and a turbine section 27 in a series flow relationship. The turbocharged engine 16 is substantially enclosed within a housing 18, which is substantially tubular and defines a core inlet 20 that is annular about a longitudinal centerline axis 12. Figure 1As schematically shown, compressor section 21 includes a turbocharger or low-pressure (LP) compressor 22, followed downstream by a high-pressure (HP) compressor 24. Combustion section 26 is downstream of compressor section 21. Turbine section 27 is downstream of combustion section 26 and includes a high-pressure (HP) turbine 28, followed downstream by a low-pressure (LP) turbine 30. The turbocharged engine 16 also includes an injection exhaust nozzle section 32 downstream of turbine section 27, a high-pressure (HP) shaft 34 or spool, and a low-pressure (LP) shaft 36. HP shaft 34 drivesly connects HP turbine 28 to HP compressor 24. HP turbine 28 and HP compressor 24 rotate synchronously via HP shaft 34. LP shaft 36 drivesly connects LP turbine 30 to LP compressor 22. LP turbine 30 and LP compressor 22 rotate synchronously via LP shaft 36. Compressor section 21, combustion section 26, turbine section 27, and injection exhaust nozzle section 32 together define the core airflow path.

[0039] for Figure 1 In the embodiment depicted, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 extend outward from disk 42 generally in the radial direction R. In the case of a variable pitch fan, multiple fan blades 40 are operably coupled to an actuation member 44 by means of the fan blades 40, which can rotate relative to disk 42 about a pitch axis P. The actuation member 44 is configured to collectively and uniformly change the pitch of the fan blades 40. The fan blades 40, disk 42, and actuation member 44 can rotate together via a fan shaft 45 about a longitudinal centerline axis 12, which is powered by an LP shaft 36 across a power gearbox (also referred to as gearbox assembly 46). In this way, fan 38 is drivenly coupled to and powered by turbocharger 16, and turbocharger 10 is an indirect drive engine. Gearbox assembly 46 is in Figure 1 The diagram is shown schematically. Gearbox assembly 46 is a reduction gearbox assembly used to adjust the rotational speed of fan shaft 45 as power is transmitted from LP shaft 36 to fan shaft 45, and thus adjust the rotational speed of fan 38 relative to LP shaft 36.

[0040] Still referencing Figure 1In an exemplary embodiment, the disk 42 is covered by a fan hub 48, which is aerodynamically shaped to facilitate airflow through a plurality of fan blades 40. Furthermore, the fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 38 and the turbocharged engine 16. The nacelle 50 is supported relative to the turbocharged engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced around the nacelle 50 and the turbocharged engine 16. Additionally, a downstream section 54 of the nacelle 50 extends over the outer portion of the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 56 therebetween.

[0041] During operation of the turbine engine 10, a certain amount of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the fan section 14. As the air 58 passes through the fan blades 40, a first portion of the air (also referred to as bypass air 62) is directed into the bypass airflow passage 56, and a second portion of the air (also referred to as core air 64) is directed into the upstream section of the core air flow path through the core inlet 20 of the LP compressor 22. The ratio between bypass air 62 and core air 64 is commonly referred to as the bypass ratio. The pressure of the core air 64 then increases, generating compressed air 65. The compressed air 65 is directed through the HP compressor 24 and into the combustion section 26, where it is mixed with fuel 67 and ignited to generate combustion gases 66.

[0042] Combustion gas 66 is directed into and expands through HP turbine 28, where a portion of the thermal or kinetic energy from combustion gas 66 is extracted via one or more stages of HP turbine rotor blades 70 and HP turbine stator blades 68 connected to HP shaft 34. This causes HP shaft 34 to rotate, thereby supporting the operation of HP compressor 24 (e.g., self-sustaining cycle). In this way, combustion gas 66 performs work on HP turbine 28. Combustion gas 66 is then directed into and expands through LP turbine 30. Here, a second portion of thermal or kinetic energy is extracted from combustion gas 66 via one or more stages of LP turbine rotor blades 74 and LP turbine stator blades 72 connected to LP shaft 36. This causes LP shaft 36 to rotate, thereby supporting the operation of LP compressor 22 (e.g., self-sustaining cycle) and the rotation of fan 38 via gearbox assembly 46. In this way, combustion gas 66 performs work on LP turbine 30.

[0043] Combustion gases 66 are then directed through the injector nozzle section 32 of the turbocharged engine 16 to provide propulsive thrust. Simultaneously, bypass air 62 is directed through bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of the turbocharged engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injector nozzle section 32 at least partially define a hot gas path 78 for directing combustion gases 66 through the turbocharged engine 16.

[0044] Figure 1 The depicted turbine engine 10 is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 38 may be configured in any other suitable manner (e.g., as a fixed-pitch fan) and may also be supported using any other suitable fan frame configuration. The turbine engine 10 may also be a direct-drive engine without a power gearbox. For a direct-drive engine, the fan speed is the same as the LP shaft speed. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In still other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable turbine engine (e.g., a turbofan engine, propfan engine, turbojet engine, turboprop engine, or turboshaft engine).

[0045] Figure 2 This is a schematic diagram of an exemplary bearing damper assembly 100 for a turbine engine 10, taken along the longitudinal centerline axis 12 of the turbine engine 10 according to this disclosure. The bearing damper assembly 100 can be used to engage a rotating component 120 of the turbine engine 10. However, the bearing damper assembly 100 can be used to engage any rotating component of the turbine engine 10, or any rotating component of another turbine engine. In particular, the rotating component 120 can be a turbine engine 10 ( Figure 1 Any rotating component of the turbocharged engine 16 (e.g., LP shaft 36 or HP shaft 34). As an example, Figure 1 The circles (bearing damper assembly (BDA)) provide example locations where the bearing damper assembly 100 of this disclosure can be incorporated into the turbine engine 10. In some embodiments, the turbine engine 10 may include two or more bearing damper assemblies 100 at two or more suitable locations as indicated by the circles BDA.

[0046] like Figure 2As shown, the bearing damper assembly 100 includes a damper frame 102, a bearing housing 104, an end seal plate 106, and a bearing 108. In the illustrated embodiment, the outer surface (e.g., the outer edge) of the bearing housing 104 is coupled to the inner surface of the damper frame 102. In some embodiments, the outer edge of the bearing housing 104 may be fixedly coupled to the damper frame 102 (e.g., via screws, nuts, or other suitable fastening mechanisms). In such embodiments, movement of the outer edge of the bearing housing 104 relative to the damper frame 102 may be restricted.

[0047] Bearing 108 is coupled to the inner surface (e.g., inner edge) of bearing housing 104 and defines an annular region 112 that can support rotating component 120. As described above, bearing 108 can facilitate rotation of rotating component 120, for example, by reducing friction that resists rotation. In the illustrated embodiment, bearing 108 is a ball bearing. In some embodiments, bearing 108 can be, for example, a journal bearing (i.e., a porous bearing pad that delivers gas into the annular region 112).

[0048] The rotating component 120 can apply forces to the bearing housing 104 via the bearing 108. For example, gravity may pull the rotating component 120 downwards, causing it to exert a radial force on the bearing housing 104. Additionally, the thrust from the movement of the turbine engine 10 may cause the rotating component 120 to exert an axial force on the bearing housing 104. Furthermore, during operation of the turbine engine 10, vibrations may occur on the rotating component 120 (e.g., due to mass imbalance), and these vibrations may propagate into the bearing housing 104. In some cases, the vibrations of the rotating component 120 may affect the operation of the turbine engine 10, for example, by interfering with or displacing other components. Therefore, the bearing housing 104 can be used to dampen (e.g., dissipate) the vibrations of the rotating component 120, thereby reducing the likelihood that the vibrations will affect the operation of the turbine engine 10.

[0049] Various types of dampers can be used in the bearing damper assembly 100 to dampen vibrations of the rotating component 120. For example, in the illustrated embodiment, the bearing housing 104 of the bearing damper assembly 100 is a squeeze-film damper utilizing fluid in an annular gap formed between the outer and inner edges of the bearing housing 104. In this way, the damping characteristics of the bearing housing 104 (e.g., target frequency or target damping value) can depend at least in part on the pressure of the fluid in the annular gap. To facilitate control of the fluid pressure, as depicted, end seal plates 106 are coupled to the two axial side surfaces of the bearing housing 104.

[0050] In some embodiments, the fluid pressure in the bearing housing 104 can be actively controlled (e.g., actively controlled in real time during operation of the turbine engine 10) by pumping fluid through the annular gap of the bearing housing 104, which flows out through the end seal plate 106. In other embodiments, the annular gap of the bearing housing 104 can be hermetically sealed, so the fluid pressure can be passively controlled (e.g., offline before the bearing housing 104 is deployed). Additionally, in some embodiments, the bearing housing 104 may include at least three circumferentially constrained annular gaps between the outer and inner edges (i.e., segmented extruded film dampers), which can facilitate improved damping performance. For example, a segmented extruded film damper can have a higher damping value compared to a "double-pi" extruded film damper (i.e., a bearing housing with only two annular gaps opposite each other in the radial direction), which can reduce the likelihood of conditions affecting damping characteristics, such as cavitation and air intake.

[0051] Figure 3 This illustrates a turbine engine 10 according to another embodiment ( Figure 1 A schematic cross-sectional view of another exemplary bearing damper assembly 200. The bearing damper assembly 200 is related to... Figure 2 The bearing damper assembly 100 is basically similar. The same or similar reference figures will be used for the bearing damper assembly 200 as described above. Figure 2 The components discussed in the bearing damper assembly 100 are the same as or similar to the components discussed in the bearing damper assembly 100. The above description of such components of the bearing damper assembly 100 also applies to these components of the bearing damper assembly 200, and detailed descriptions of these components are omitted here.

[0052] like Figure 3 As shown, the bearing damper assembly 200 includes a damper frame 202, a bearing housing 204 disposed in the damper frame 202 (e.g., connected to the damper frame 202), an end sealing plate 206 connected to the bearing housing 204, and a bearing 208. Figure 3 (Only one is shown in the diagram) and an outer spring 210. In the illustrated embodiment, the damper frame 202, bearing housing 204, end seal 206, and outer spring 210 are annular, such that the bearing damper assembly 200 defines a bearing damper centerline axis 214. The radial direction R extends perpendicular to the bearing damper centerline axis 214, and the circumferential direction C extends about the bearing damper centerline axis 214. In some embodiments, one or more of the damper frame 202, bearing housing 204, end seal 206, or outer spring 210 may not be annular.

[0053] The bearing housing 204 is coupled to the damper frame 202, and the end seal plate 206 is coupled to the bearing housing 204. For example, in the illustrated embodiment, a plurality of housing fasteners 211 ( Figure 3 (Only one shown) A bearing housing 204 is connected to a damper frame 202, and an end seal plate 206 is connected to the bearing housing 204. The damper frame 202 may be connected to a static component or static structure (e.g., a frame) of the turbine engine 10. The bearing 208 is supported by the bearing housing 204, extends radially inward from the damper frame 202, and defines an annular region that may support rotating components, such as... Figure 2 Rotating component 120.

[0054] The outer spring 210 includes a plurality of spring fingers 216 that together define at least a portion of an annular region about the axis 214 of the bearing damper centerline. Figure 3 Only one is shown in the image. Figure 3 As shown, the spring finger 216 has a first end 218 and a second end 222 extending from the first end 218. The first end 218 of the spring finger 216 is fixedly coupled to a static component or static structure of the turbine engine 10, such as its frame. In some embodiments, the first ends 218 of a plurality of spring fingers 216 may be fixedly coupled (e.g., fastened) to a damper frame 202. The second end 222 of the spring finger 216 is coupled to a bearing housing 204 to limit movement of the bearing housing 204 relative to an external spring 210. Specifically, in the illustrated embodiment, the outer wall 219 of the second end 222 of the spring finger 216 is received within a flange portion 224 of the damper frame 202, and at least a portion of the bearing housing 204 is received within a finger groove 226 defined by the outer wall 219 and inner wall 221 of the second end 222 of the spring finger 216, the inner wall 221 being radially inward of the outer wall 219. In this way, the second end 222 of the spring finger 216 and at least a portion of the bearing housing 204 are movable relative to the stationary damper frame 202 in at least the radial direction R. Furthermore, in the illustrated embodiment, the bearing 208 is directly coupled to the inner wall 221 of the second end 222 of the plurality of spring fingers 216. In some embodiments, the bearing 208 may be directly coupled to the bearing housing 204. For example, in some such embodiments, the second end 222 of the spring finger 216 may be fixedly coupled to a portion of the bearing housing 204 or the end seal plate 206.

[0055] Figure 4 yes Figure 3 A magnified cross-sectional detailed view of the area marked "4". Figure 5 This is a front view of the bearing housing 204 of the bearing damper assembly 200. (See image.) Figure 4 and Figure 5As shown, the bearing housing 204 has an outer edge 240, relative to the radial direction R ( Figure 5 The housing base 242 is located on the radially inner side of the outer edge 240, and relative to the radial direction R ( Figure 5 The inner edge 244 is disposed radially inside the housing base 242. In the illustrated embodiment, the outer edge 240, housing base 242, and inner edge 244 of the bearing housing 204 are annular about the bearing damper centerline axis 214. In some embodiments, one or more of the outer edge 240, housing base 242, or inner edge 244 of the bearing housing 204 may not be annular. For example, in some such embodiments, at least the outer edge 240 of the bearing housing 204 may not be annular.

[0056] The bearing housing 204 has a housing base 242 that is fixedly connected to the damper frame 202. Specifically, in the illustrated embodiment, the bearing housing 204 defines a plurality of housing openings 248 extending through the housing base 242 and receiving a plurality of housing fasteners 211. Figure 4 (Only one is shown in the diagram), multiple housing fasteners 211 securely connect the housing base 242 to the damper frame 202. In the illustrated embodiment, the outer edge 240 and inner edge 244 of the bearing housing 204 are not directly connected to the damper frame 202.

[0057] like Figure 5 As shown, the bearing housing 204 defines a first plurality of annular gaps 254 between the outer edge 240 and the housing base 242, and a second plurality of annular gaps 260 between the inner edge 244 and the housing base 242. In the illustrated embodiment, the first plurality of annular gaps 254 and the second plurality of annular gaps 260 extend into a first axial side 256 of the bearing housing 204 and pass through a second axial side 258 (…). Figure 4 The bearing housing 204 further defines a first plurality of integral springs 250 connecting the outer edge 240 to the housing base 242 and a second plurality of integral springs 252 connecting the inner edge 244 to the housing base 242. In other words, in the illustrated embodiment, the stationary housing base 242 is connected to the outer edge 240 and the inner edge 244 via the first plurality of integral springs 250 and the second plurality of integral springs 252, respectively. In this way, the outer edge 240 and the inner edge 244 of the bearing housing 204 (and the second end 222 of the spring finger 216) Figure 4 ()) can be relative to the stationary shell base 242 (and damper frame 202 () Figure 4 It moves at least in the radial direction R.

[0058] Each of the first plurality of annular gaps 254 is constrained in the circumferential direction C by two integral springs from the first plurality of integral springs 250. In other words, one integral spring from the first plurality of integral springs 250 is disposed at any circumferential end of each of the first plurality of annular gaps 254. Similarly, each of the second plurality of annular gaps 260 is constrained in the circumferential direction C by two integral springs from the second plurality of integral springs 252. In other words, one integral spring from the second plurality of integral springs 252 is disposed at any circumferential end of each of the second plurality of annular gaps 260.

[0059] In the illustrated embodiment, the first plurality of annular gaps 254 include at least four annular gaps, the first plurality of integral springs 250 include at least eight integral springs, the second plurality of annular gaps 260 include at least four annular gaps, and the second plurality of integral springs 252 include at least eight integral springs. However, the number and arrangement of the first plurality of integral springs 250, the second plurality of integral springs 252, the first plurality of annular gaps 254, and the second plurality of annular gaps 260 of the bearing housing 204 are not limited to any particular number or arrangement, and can be based on the components to be provided (e.g., rotating parts). Figure 2 The number and arrangement of the rotating components (120) are selected based on their desired damping characteristics. For example, in some embodiments, the first plurality of annular gaps 254 may include at least two annular gaps, the first plurality of integral springs 250 may include at least four integral springs, the second plurality of annular gaps 260 may include at least two annular gaps, and the second plurality of integral springs 252 may include at least four integral springs. In some embodiments, the first plurality of annular gaps 254 may include at least five annular gaps, the first plurality of integral springs 250 may include at least ten integral springs, the second plurality of annular gaps 260 may include at least five annular gaps, and the second plurality of integral springs 252 may include at least ten integral springs. In some embodiments, the first plurality of annular gaps 254 may include a total number of annular gaps different from the total number of annular gaps in the second plurality of annular gaps 260. In some embodiments, the first plurality of integral springs 250 may include a total number of integral springs different from the total number of integral springs in the second plurality of integral springs 252.

[0060] like Figure 4 As shown, each of the first plurality of annular gaps 254 has a first gap size W1, the first gap size W1 being in the radial direction R ( Figure 3The first gap size W1 of the first plurality of annular gaps 254 is measured between the radially inner surface of the outer edge 240 and the radially outer surface of the housing base 242. Similarly, each of the second plurality of annular gaps 260 has a second gap size W2, which is measured in the radial direction R between the radially outer surface of the inner edge 244 and the radially inner surface of the housing base 242. In the illustrated embodiment, the first gap size W1 of the first plurality of annular gaps 254 is greater than the second gap size W2 of the second plurality of annular gaps 260. In this way, the first plurality of annular gaps 254 can provide a greater damping value than the second plurality of annular gaps 260. In some embodiments, the second gap size W2 of the second plurality of annular gaps 260 may be greater than or substantially equal to the first gap size W1 of the first plurality of annular gaps 254.

[0061] Figure 6 yes Figure 5 A magnified, detailed view of the area marked "6". (See attached image.) Figure 6 As shown, each of the first plurality of integral springs 250 includes a spring portion 250A, an active damper portion 250B, and a deflection limiter portion 250C. The spring portion 250A of the first plurality of integral springs 250 is located in the radial direction R (… Figure 5 The outer edge is compressible, making the outer edge 240 ( Figure 5 At least some portions of ) can be relative to the stationary housing base 242 ( Figure 5 ) and damper frame 202 ( Figure 3 and Figure 4 ) moves or rotates. The active damper portion 250B of the first plurality of integral springs 250 is each connected to the first plurality of annular gaps 254 ( Figure 5 The deflection limiter portion 250C of the first plurality of integral springs 250 is each connected to the deflection limiter portion of another directly adjacent integral spring in the first plurality of integral springs 250. In this way, the deflection limiter portion 250C of the first plurality of integral springs 250 can limit the deflection of the outer edge 240 relative to the housing base 242 of the bearing housing 204.

[0062] Each integral spring in the second plurality of integral springs 252 of the bearing housing 204 is constructed similarly to the first plurality of integral springs 250, but may differ in orientation, size, etc. For example, Figure 7 yes Figure 5 A magnified, detailed view of the area marked "7". (See image below.) Figure 7 As shown, each of the second plurality of integrated springs 252 includes a spring portion 252A, an active damper portion 252B, and a deflection limiter portion 252C. The spring portion 252A of the second plurality of integrated springs 252 is located in the radial direction R (… Figure 5The inner edge 244 is compressible, making it compressible. Figure 5 At least some portions of ) can be relative to the stationary housing base 242 ( Figure 5 ) and damper frame 202 ( Figure 3 and Figure 4 ) moves or rotates. The active damper portion 252B of the second plurality of integral springs 252 is each connected to the second plurality of annular gaps 260 ( Figure 5 The corresponding one of the two integral springs 252. The deflection limiter portion 252C of the second plurality of integral springs 252 is each connected to the deflection limiter portion of another directly adjacent integral spring in the second plurality of integral springs 252. In this way, the deflection limiter portion 252C of the second plurality of integral springs 252 can limit the deflection of the inner edge 244 relative to the housing base 242 of the bearing housing 204.

[0063] Refer again Figure 5 Each of the first plurality of integral springs 250 in the bearing housing 204 is arranged such that the active damper portion 250B ( Figure 6 ) is located relative to the bearing damper centerline axis 214 in the deflection limiter section 250C ( Figure 6 On the other hand, each of the second plurality of integral springs 252 in the bearing housing 204 is arranged such that the active damper portion 252B ( Figure 7 ) is located relative to the bearing damper centerline axis 214 in the deflection limiter section 252C ( Figure 7 The radial inner side of the first plurality of integral springs 250. Furthermore, in the illustrated embodiment, the first plurality of integral springs 250 and the second plurality of integral springs 252 are arranged such that each integral spring in the first plurality of integral springs 250 is circumferentially disposed between two radially adjacent integral springs in the second plurality of integral springs 252 in the circumferential direction C, and each integral spring in the second plurality of integral springs 252 is circumferentially disposed between two radially adjacent integral springs in the first plurality of integral springs 250 in the circumferential direction C. In this way, when the inner edge 244 and the outer edge 240 move relative to the housing base 242 in the first radial direction (e.g., when the second end 222 of the spring finger 216 deflects relative to the housing base 242 and the damper frame 202 in the first radial direction), some integral springs in the first plurality of integral springs 250 are compressed in the first radial direction, while some integral springs in the second plurality of integral springs 252 are compressed in the second radial direction opposite to the first radial direction, and a damping reaction force is provided in the second radial direction.

[0064] The first plurality of integral springs 250 of the bearing housing 204 may have a first spring factor (e.g., stiffness) that provides a first spring stiffness between the outer edge 240 and the housing base 242. Similarly, the second plurality of integral springs 252 of the bearing housing 204 may have a second spring factor that provides a second spring stiffness between the inner edge 244 and the housing base 242. In some embodiments, the first spring factor of the first plurality of integral springs 250 may be different from (e.g., greater than or less than) the second spring factor of the second plurality of integral springs 252. For example, in some such embodiments, the first spring factor of the first plurality of integral springs 250 may be less than the second spring factor of the second plurality of integral springs 252. In other embodiments, the first spring factor of the first plurality of integral springs 250 may be substantially equal to the second spring factor of the second plurality of integral springs 252.

[0065] In the illustrated embodiment, a first plurality of integral springs 250 are integrally formed with the outer edge 240 and the housing base 242, and a second plurality of integral springs 252 are integrally formed with the inner edge 244 and the housing base 242, such that the bearing housing 204 is a single, integral piece. In some embodiments, the first plurality of integral springs 250 and the second plurality of integral springs 252 may be integrally formed with the bearing housing 204 via a subtractive manufacturing process (e.g., wire EDM). In some embodiments, the bearing housing 204 may be formed via one or more additive manufacturing processes.

[0066] By utilizing a plurality of annular gaps 254 and a plurality of annular gaps 260 maintained by a plurality of first integral springs 250 and a plurality of second integral springs 252 respectively, the bearing housing 204 can increase viscous resistance, thereby reducing the possibility of circumferential flow. This can achieve an increased gap size (e.g., a first gap size W1 or a second gap size W2) in one or both of the plurality of annular gaps 254 or the plurality of annular gaps 260. Figure 4 In this way, the amount of fluid in each of the first plurality of annular gaps 254 and the second plurality of annular gaps 260 can be increased, which can promote an increased damping value of the bearing damper assembly 200 and reduce the likelihood of conditions affecting the overall damping characteristics of the bearing damper assembly 200 (e.g., cavitation and air intake in the first plurality of annular gaps 254 and the second plurality of annular gaps 260). As mentioned above, the damping characteristics of the bearing damper assembly 200 may also be affected by the fluid pressure within the first plurality of annular gaps 254 and the second plurality of annular gaps 260 of the bearing housing 204. In some embodiments, the fluid pressure within at least one of the first plurality of annular gaps 254 or the second plurality of annular gaps 260 can be actively controlled by independently controlling the fluid flow into the first plurality of annular gaps 254 and the second plurality of annular gaps 260.

[0067] in this regard, Figure 8 yes Figures 3 to 7 A schematic diagram of the first fluid circuit 290 and the second fluid circuit 292 of the bearing damper assembly 200. (See diagram) Figure 8 As shown, fluid supplied to the first fluid circuit 290 flows to each of the first plurality of annular gaps 254, while fluid supplied to the second fluid circuit 292 flows to each of the second plurality of annular gaps 260. In the illustrated embodiment, the first fluid circuit 290 and the second fluid circuit 292 are fluidly isolated.

[0068] Specifically, the first fluid circuit 290 includes at least one first inlet (not shown) in fluid communication with the first plurality of annular gaps 254, and the second fluid circuit 292 includes at least one second inlet (not shown) in fluid communication with the second plurality of annular gaps 260. In some embodiments, at least one first inlet of the first fluid circuit 290 or at least one second inlet of the second fluid circuit 292 may be defined by the second end 222 of the damper frame 202 or the plurality of spring fingers 216. In some embodiments, the radial outer surface of the outer edge 240 of the bearing housing 204 may be defined in the circumferential direction C ( Figure 5 The first and second annular grooves extend from the end seal plate 206. The first and second annular grooves are in fluid communication with the first plurality of annular gaps 254 and the second plurality of annular gaps 260, respectively, such that the first and second annular grooves at least partially define at least one first inlet of the first fluid circuit 290 and at least one second inlet of the second fluid circuit 292. In some embodiments, the end seal plate 206 may define a plurality of plate recesses (not shown) that may define at least one first inlet of the first fluid circuit 290 and at least one second inlet of the second fluid circuit 292.

[0069] In some embodiments, at least one of the first fluid circuit 290 or the second fluid circuit 292 may be configured such that fluid flows in parallel (i.e., simultaneously) from at least one first inlet or at least one second inlet to each of the first plurality of annular gaps 254 or the second plurality of annular gaps 260. In some embodiments, at least one of the first fluid circuit 290 or the second fluid circuit 292 may be configured such that fluid flows serially from at least one first inlet or at least one second inlet to each of the first plurality of annular gaps 254 or the second plurality of annular gaps 260.

[0070] Still referencing Figure 8Fluid within the first plurality of annular gaps 254 and the second plurality of annular gaps 260 flows out of the first plurality of annular gaps 254 and the second plurality of annular gaps 260, respectively. Specifically, the first fluid circuit 290 includes a first plurality of outlets (not shown) in fluid communication with the first plurality of annular gaps 254, and the second fluid circuit 292 includes a second plurality of outlets (not shown) in fluid communication with the second plurality of annular gaps 260. For example, in Figures 3 to 8 In the illustrated embodiment, the second end 222 of the spring finger 216 and the bearing housing 204 are arranged such that an outer clearance 230 and an inner clearance 232 are defined between corresponding portions of the bearing housing 204 and the damper frame 202, the inner clearance 232 being relative to the bearing damper centerline axis 214. Figure 3 The outer gaps 230 are radially inside the outer gaps 230. Therefore, in some embodiments, the plurality of outer gaps 230 may define a first plurality of outlets of the first fluid circuit 290, and the plurality of inner gaps 232 may define a second plurality of outlets of the second fluid circuit 292. In other embodiments, at least one of the first plurality of outlets of the first fluid circuit 290 or the second plurality of outlets of the second fluid circuit 292 may be provided by an external spring 210. Figure 3 The second ends 222 of a plurality of spring fingers 216 define the first fluid circuit 290. For example, in some such embodiments, the outer wall 219 of the second ends 222 of the plurality of spring fingers 216 may define a first plurality of outlets of the first fluid circuit 290, while the inner wall 221 of the second ends 222 of the plurality of spring fingers 216 may define a second plurality of outlets of the second fluid circuit 292. In some embodiments, the damper frame 202 may define a plurality of frame recesses (not shown) that may define at least one of the first plurality of outlets of the first fluid circuit 290 or the second plurality of outlets of the second fluid circuit 292. In some embodiments, the first fluid circuit 290 may include a single first outlet in fluid communication with a first plurality of annular gaps 254, or the second fluid circuit 292 may include a single second outlet in fluid communication with a second plurality of annular gaps 260.

[0071] like Figure 8As shown, the bearing damper assembly 200 also includes a pump 294 that supplies fluid (e.g., from a tank 298) to a first fluid circuit 290 (e.g., via at least one first inlet (not shown)) and a second fluid circuit 292 (e.g., via at least one second inlet (not shown)). One or more valves 296 may be disposed between the pump 294 and at least one first inlet of the first fluid circuit 290 or at least one second inlet of the second fluid circuit 292 to selectively supply fluid to one or both of the first fluid circuit 290 or the second fluid circuit 292. Thus, by controlling the fluid flow to the first plurality of annular gaps 254 and the second plurality of annular gaps 260 of the bearing housing 204 via controlling the pump 294 and one or more valves 296, the fluid pressure within one or both of the first plurality of annular gaps 254 or the second plurality of annular gaps 260 can be varied. For example, in the illustrated embodiment, one or more valves 296 include a first valve 296A disposed between the pump 294 and at least one first inlet of the first fluid circuit 290, and a second valve 296B disposed between the pump 294 and at least one second inlet of the second fluid circuit 292. In this way, via controlling the first valve 296A and the second valve 296B, the bearing damper assembly 200 can operate in one of at least three damping modes (i.e., a first damping mode, a second damping mode, and a third damping mode).

[0072] Specifically, by operating pump 294 with each of the first valve 296A and the second valve 296B in the open position, bearing damper assembly 200 can operate in a first damping mode, such that fluid from pump 294 is supplied to each of the first plurality of annular gaps 254 and the second plurality of annular gaps 260 of bearing housing 204. When bearing damper assembly 200 operates in the first damping mode, the first plurality of circumferential damping sectors corresponding to the first plurality of annular gaps 254 and the second plurality of circumferential damping sectors corresponding to the second plurality of annular gaps 260 are activated (i.e., providing active damping). In the illustrated embodiment, the second plurality of circumferential damping sectors (i.e., the second plurality of annular gaps 260) are relative to the bearing damper centerline axis 214 (…). Figure 5 The bearing damper assembly 200 is located radially inside the first plurality of circumferential damping sectors (i.e., the first plurality of annular gaps 254). Therefore, when operating in the first damping mode, the bearing damper assembly 200 can provide a first damping level.

[0073] Still referencing Figure 8By operating pump 294 with first valve 296A in the open position and second valve 296B in the closed position, bearing damper assembly 200 can operate in a second damping mode, such that fluid from pump 294 is supplied only to the first plurality of annular gaps 254 of bearing housing 204. In the second damping mode, the first plurality of circumferential damping sectors are activated, while the second plurality of circumferential damping sectors are deactivated (i.e., no active damping is provided). Therefore, when operating in the second damping mode, bearing damper assembly 200 can provide a second damping level that is different from (e.g., smaller) than the first damping level.

[0074] By operating pump 294 with first valve 296A in the closed position and second valve 296B in the open position, bearing damper assembly 200 can operate in a third damping mode, such that fluid from pump 294 is supplied only to the second plurality of annular gaps 260 of bearing housing 204. When bearing damper assembly 200 operates in the third damping mode, the first plurality of circumferential damping sectors are deactivated, while the second plurality of circumferential damping sectors are activated. Therefore, when operating in the third damping mode, bearing damper assembly 200 can provide a third damping level that is different from the first damping level (e.g., smaller) and different from the second damping level (e.g., larger or smaller).

[0075] exist Figure 8 In the illustrated embodiment, pump 294 is a gear pump, and first valve 296A and second valve 296B are two-way ball valves. In some embodiments, pump 294 may be a centrifugal pump, positive displacement pump, screw pump, etc., and first valve 296A and second valve 296B may be, for example, electromagnetically actuated ball valves. In some embodiments, first valve 296A may be a valve of a different type than second valve 296B. In some embodiments, bearing damper assembly 200 may include two or more pumps 294. For example, in some such embodiments, bearing damper assembly 200 may include a first pump in fluid communication with a first fluid circuit 290 and a second pump in fluid communication with a second fluid circuit 292. In some such embodiments, bearing damper assembly 200 may not include one or more valves 296. In some embodiments, one or more valves 296 of bearing damper assembly 200 may include at least three valves. For example, in some such embodiments, one or more valves 296 of the bearing damper assembly 200 may include a first plurality of valves controlling fluid flow to a respective annular gap in a first plurality of annular gaps 254 and a second plurality of valves controlling fluid flow to a respective annular gap in a second plurality of annular gaps 260.

[0076] In some embodiments, the bearing damper assembly 200 may further include an electronic controller (not shown) electrically connected to the first valve 296A and the second valve 296B. In some such embodiments, the electronic controller may be configured to selectively operate the bearing damper assembly 200 in a first damping mode, a second damping mode, or a third damping mode (e.g., via controlling the first valve 296A and the second valve 296B). For example, in some such embodiments, the electronic controller may be configured to respond to the turbine engine 10 ( Figure 1 The first operating condition of ) (e.g., rotating component 120 ( Figure 2 The electronic controller can operate the bearing damper assembly 200 in a first damping mode in response to a first sensing speed of the turbine engine 10, and in a second damping mode in response to a second operating condition of the turbine engine 10 (e.g., a second sensing speed of the rotating component 120, the second sensing speed being less than the first sensing speed). Furthermore, the electronic controller can also be configured to operate the bearing damper assembly 200 in a second damping mode in response to a second operating condition of the turbine engine 10 (e.g., a second sensing speed of the rotating component 120, the second sensing speed being less than the first sensing speed). Figure 1 The bearing damper assembly 200 operates in the third damping mode under the third operating conditions (e.g., the third sensing speed of the rotating component 120, which is less than the second sensing speed).

[0077] Figure 9 and Figure 10 A turbine engine 10 according to another embodiment is shown. Figure 1 Another exemplary bearing damper assembly 300, for example Figure 2 The bearing damper assembly 100 or Figures 3 to 8 200 bearing damper assembly. Figure 9 This is a schematic cross-sectional view of the bearing damper assembly 300, and Figure 10 yes Figure 9 A detailed enlarged cross-sectional view of the area marked "10". Bearing damper assembly 300 and... Figure 2 The bearing damper assembly 100 and Figures 3 to 8 The bearing damper assembly 200 is basically similar. The same or similar reference figures will be used for the bearing damper assembly 300 as described above. Figures 2 to 8 The components of the bearing damper assemblies 100 and 200 discussed herein are the same as or similar to the components described above. The above description of such components of bearing damper assemblies 100 and 200 also applies to these components of bearing damper assembly 300, and detailed descriptions of these components are omitted here.

[0078] like Figure 9 As shown, the bearing damper assembly 300 includes a damper frame 302, a bearing housing 304, an end sealing plate 306, a bearing 308, and a plurality of spring fingers 316. Figure 9The outer spring 310 (only one is shown in the image), damper frame 302, bearing housing 304, end seal plate 306, bearing 308 and outer spring 310 are similar to Figures 3 to 8 The bearing damper assembly 200 includes a damper frame 202, a bearing housing 204, an end seal plate 206, a bearing 208, and an external spring 210. Furthermore, the bearing housing 304 of the bearing damper assembly 300 includes an outer edge 340, a housing base 342, and an inner edge 344. Figure 10 The outer edge 340, the outer shell base 342, and the inner edge 344 are similar to Figures 3 to 8 The bearing housing 204 has an outer edge 240, a housing base 242, and an inner edge 244. In the illustrated embodiment, the damper frame 302, bearing housing 304, end seal plate 306, and outer spring 310 are annular, such that the bearing damper assembly 300 defines the bearing damper centerline axis 314, and the outer edge 340, housing base 342, and inner edge 344 of the bearing housing 304 are annular about the bearing damper centerline axis 314. The bearing housing 304 also includes a first plurality of annular gaps 354 ( Figure 10 ), and the second multiple annular gaps 360 ( Figure 10 The first plurality of integral springs (not shown) and the second plurality of integral springs (not shown), the first plurality of annular gaps 354, the second plurality of annular gaps 360, the first plurality of integral springs and the second plurality of integral springs are similar to Figures 3 to 8 The bearing housing 204 has a first plurality of annular gaps 254, a second plurality of annular gaps 260, a first plurality of integral springs 250, and a second plurality of integral springs 252.

[0079] exist Figure 9 and Figure 10 In the illustrated embodiment, the outer edge 340 and inner edge 344 of the bearing housing 304 are fixedly connected to the damper frame 302, while the housing base 342 of the bearing housing 304 is connected to the second end 322 of the spring finger 316, the second end 322 being connected to the first end 318 ( Figure 9 The bearing housing 304's housing base 342 (and the second end 322 of the spring finger 316) can be positioned relative to the outer edge 340 and inner edge 344 of the bearing housing 304 (and the damper frame 302) in at least the radial direction R. Figure 9 Move on.

[0080] Specifically, the outer edge 340 and inner edge 344 of the bearing housing 304 are connected to each other via a connecting wall 370, which extends between the outer edge 340 and the inner edge 344 at a second axial side 358 of the bearing housing 304 opposite to the first axial side 356. An outer flange 372 of the bearing housing 304 extends radially outward from the connecting wall 370 adjacent to the outer edge 340, such that the connecting wall 370 and the outer flange 372 define the second axial side 358 of the bearing housing 304. The connecting wall 370 and the outer flange 372 of the bearing housing 304 are received within a flange portion 324 of the damper frame 302. In the illustrated embodiment, the outer flange 372 is fixedly coupled to the damper frame 302 via a plurality of housing fasteners 311, which are received in a first plurality of housing openings 348 defined by the outer flange 372. Figure 10 Only one is shown in the text.

[0081] At least a portion of the bearing housing 304 is received within a finger-shaped groove 326 defined by the second end 322 of the spring finger 316. An end seal 306 is disposed between the first axial side 356 of the bearing housing 304 and the second end 322 of the spring finger 316. The end seal 306 may define an outer clearance 330 and an inner clearance 332, the inner clearance 332 being relative to the bearing damper centerline axis 314. Figure 3 On the radially inner side of the outer gap 330, the outer gap 330 and the inner gap 332 are in fluid communication with the corresponding annular gaps in the first plurality of annular gaps 354 and the second plurality of annular gaps 360. The housing base 342 of the bearing housing 304 is connected to the second end 322 of the spring finger 316 via a plurality of finger fasteners 376, the plurality of finger fasteners 376 being received in the second plurality of housing openings 378 defined by the housing base 340. Figure 10 Only one is shown in the text.

[0082] In some embodiments, the bearing housing 304 may not include the connecting wall 370, such that the outer edge 340 and the inner edge 344 are not directly connected. For example, in some such embodiments, the outer flange 372 may extend radially outward from the outer edge 340, and the bearing housing 304 may also include an inner flange (not shown) that extends radially inward from the inner edge 344. In some such embodiments, both the outer flange 372 and the inner flange (not shown) of the bearing housing 304 may be fixedly coupled to the damper frame 302.

[0083] Figure 11 This is a flowchart illustrating a method 400 for damping the vibrations of rotating components of a turbine engine via a bearing damper assembly. Although referenced... Figures 3 to 8 The bearing damper assembly 200, but method 400 can be with Figures 2 to 10It can be used with any one of the bearing damper assemblies 100, 200 and 300 or with any other bearing damper system of other turbine engines.

[0084] In step 410, method 400 includes selectively supplying fluid to a first plurality of annular gaps in the bearing housing via a first fluid circuit of the bearing damper assembly. For example, refer to Figures 3 to 8 The bearing damper assembly 200 shown, step 410 includes via pump 294 ( Figure 8 Fluid is supplied to the first plurality of annular gaps 254 of the bearing housing 204 of the bearing damper assembly 200 via the first fluid circuit 290. In some embodiments, step 410 may include, for example, operating the bearing damper assembly 200 in a second damping mode by moving the first valve 296A to the open position and the second valve 296B to the closed position. In some embodiments, a controller (not shown) of the bearing damper assembly 200 may selectively supply fluid to the first fluid circuit 290 by controlling the first valve 296A and the second valve 296B to operate the bearing damper assembly 200 in the second damping mode.

[0085] In step 420, method 400 includes selectively supplying fluid to a second plurality of annular gaps in the bearing housing via a second fluid circuit of the bearing damper assembly. For example, refer to Figures 3 to 8 The bearing damper assembly 200 shown, step 420 includes via pump 294 ( Figure 8 Fluid is supplied to the second plurality of annular gaps 260 of the bearing housing 204 of the bearing damper assembly 200 via the second fluid circuit 292. In some embodiments, step 420 may include, for example, operating the bearing damper assembly 200 in a third damping mode by moving the first valve 296A to a closed position and the second valve 296B to an open position. In some embodiments, a controller (not shown) of the bearing damper assembly 200 may selectively supply fluid to the second fluid circuit 292 by controlling the first valve 296A and the second valve 296B to operate the bearing damper assembly 200 in a third damping mode.

[0086] In some embodiments, step 420 may be performed before step 410, such as... Figure 11 As indicated by the double-headed arrows. In some embodiments, steps 410 and 420 can be performed simultaneously. For example, refer to... Figure 8In some such embodiments, steps 410 and 420 of the illustrated bearing damper assembly 200 may include, for example, operating the bearing damper assembly 200 in a first damping mode by moving the first valve 296A and the second valve 296B to the open position. In some such embodiments, a controller (not shown) of the bearing damper assembly 200 may selectively and simultaneously supply fluid to both the first fluid circuit 290 and the second fluid circuit 292 by controlling the first valve 296A and the second valve 296B to operate the bearing damper assembly 200 in the first damping mode. In some embodiments, method 400 may include only one of steps 410 or 420, or both steps 410 and 420, as shown. Figure 11 The “and / or” in the text is shown. Alternatively, step 410 can be performed first, or step 420 can be performed first.

[0087] Therefore, this disclosure provides an improved bearing damper assembly for a turbine engine, which can operate in multiple variable damping modes under various operating modes of the turbine engine. Specifically, embodiments of this disclosure can provide a bearing damper assembly having a first plurality of annular gaps and a second plurality of annular gaps, the second plurality of annular gaps being radially inside the first plurality of annular gaps, the first plurality of annular gaps and the second plurality of annular gaps being independently activated to provide various damping characteristics of the bearing damper assembly, which can improve the operating performance and durability of the bearing damper assembly and the turbine engine in a range of operating modes.

[0088] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0089] A bearing damper assembly for a turbine engine defines a bearing damper centerline axis, a radial direction extending perpendicular to the bearing damper centerline axis, and a circumferential direction about the bearing damper centerline axis. The bearing damper assembly includes a damper frame, a bearing housing disposed within the damper frame, and an end seal plate connected to the bearing housing. The bearing housing is annular and includes a housing base, an outer edge, and an inner edge. The outer edge is disposed radially outward of the housing base relative to the radial direction and connected to the housing base via a first plurality of integral springs, forming a first plurality of annular gaps between the outer edge and the housing base. The inner edge is disposed radially inward of the housing base relative to the radial direction and connected to the housing base via a second plurality of integral springs, forming a second plurality of annular gaps between the inner edge and the housing base. Each of the first plurality of annular gaps is constrained in the circumferential direction by two integral springs of the first plurality of integral springs, which are in fluid communication with a first fluid loop of the bearing damper assembly. Each of the second plurality of annular gaps is constrained in the circumferential direction by two integral springs of the second plurality of integral springs, which are in fluid communication with a second fluid circuit of the bearing damper assembly. The first plurality of annular gaps and the second plurality of annular gaps are configured to be filled with fluid via the first fluid circuit and the second fluid circuit, respectively, to dampen vibrations generated on the rotating components of the turbine engine.

[0090] The bearing damper assembly according to the foregoing clause further includes an external spring comprising a plurality of spring fingers, each of the plurality of spring fingers having a first end fixedly connected to the frame of the turbine engine and a second end engaging the bearing housing.

[0091] According to any of the foregoing clauses, the base of the bearing housing is fixedly connected to the damper frame, such that the outer edge and the inner edge are movable relative to the base of the housing, the damper frame, or both.

[0092] According to any of the foregoing clauses, the end seal plate is connected to the base of the bearing housing.

[0093] According to any of the preceding clauses, the outer edge and the inner edge of the bearing housing are fixedly connected to the damper frame, such that the base of the housing is movable relative to the outer edge, the inner edge, the damper frame, or all three.

[0094] The bearing damper assembly according to any of the foregoing provisions further includes an external spring comprising a plurality of spring fingers, each of the plurality of spring fingers having a first end fixedly coupled to the frame of the turbine engine and a second end engaging the bearing housing. The housing base of the bearing housing is coupled to the second end of the plurality of spring fingers.

[0095] According to any of the foregoing clauses, the first plurality of annular gaps have a first gap size measured in the radial direction, and the second plurality of annular gaps have a second gap size measured in the radial direction, the second gap size being different from the first gap size.

[0096] According to any of the foregoing clauses, the first gap size is larger than the second gap size in the bearing damper assembly.

[0097] According to any of the foregoing clauses, the first plurality of integral springs have a first spring factor, and the second plurality of integral springs have a second spring factor different from the first spring factor.

[0098] According to any of the foregoing clauses, the first spring coefficient is less than the second spring coefficient in the bearing damper assembly.

[0099] According to any of the foregoing clauses, the first plurality of annular gaps include at least two annular gaps, and the second plurality of annular gaps include at least two annular gaps.

[0100] According to any of the foregoing clauses, the first plurality of annular gaps include at least four annular gaps, and the second plurality of annular gaps include at least four annular gaps.

[0101] According to any of the foregoing clauses, the number of annular gaps in the first plurality of annular gaps is equal to the number of annular gaps in the second plurality of annular gaps.

[0102] The bearing damper assembly according to any of the foregoing clauses further includes a pump in fluid communication with the first fluid circuit and the second fluid circuit to provide fluid to the first plurality of annular gaps and the second plurality of annular gaps, respectively.

[0103] The bearing damper assembly according to any of the foregoing clauses further includes at least one valve disposed between the pump and the first fluid circuit and the second fluid circuit, the at least one valve being controllable to control the fluid flow supplied to the first fluid circuit and the second fluid circuit.

[0104] The bearing damper assembly according to any of the foregoing clauses further includes an electronic controller electrically connected to the at least one valve, the electronic controller being configured to selectively supply fluid to the first fluid circuit and the second fluid circuit via controlling the at least one valve.

[0105] According to any of the preceding clauses, the bearing damper assembly includes a first valve disposed between the pump and the first fluid circuit and a second valve disposed between the pump and the second fluid circuit.

[0106] According to any of the foregoing clauses, each of the first plurality of integral springs includes a spring portion and an active damper portion, the spring portion being compressible in the radial direction such that at least some portions of the outer edge are movable or circumferential relative to the stationary housing base and the damper frame, and the active damper portion being connected to a corresponding one of the first plurality of annular gaps.

[0107] According to any of the foregoing clauses, each of the first plurality of integral springs further includes a deflection limiter portion connected to a deflection limiter portion of another directly adjacent integral spring in the first plurality of integral springs to limit the deflection of the outer edge relative to the housing base of the bearing housing.

[0108] According to any of the foregoing clauses, each of the second plurality of integral springs includes a spring portion and an active damper portion, the spring portion being compressible in the radial direction such that at least some portions of the inner edge are movable or circumferential relative to the stationary housing base and the damper frame, and the active damper portion being connected to a corresponding one of the second plurality of annular gaps.

[0109] According to any of the foregoing clauses, each of the second plurality of integral springs further includes a deflection limiter portion connected to a deflection limiter portion of another directly adjacent integral spring in the second plurality of integral springs to limit the deflection of the inner edge relative to the base of the bearing housing.

[0110] A method for damping vibrations of a rotating component of a turbine engine includes selectively supplying fluid to at least one of the following: a first fluid circuit of a bearing damper assembly, the first fluid circuit being in fluid communication with a first plurality of annular gaps formed between a housing base and an outer edge of a bearing housing of the bearing damper assembly; or a second fluid circuit of the bearing damper assembly, the second fluid circuit being in fluid communication with a second plurality of annular gaps formed between a housing base and an inner edge of the bearing housing of the bearing damper assembly. The second plurality of annular gaps are disposed radially inside the first plurality of annular gaps. Each of the first plurality of annular gaps is circumferentially constrained by two integral springs of a first plurality of integral springs of the bearing housing. Each of the second plurality of annular gaps is circumferentially constrained by two integral springs of a second plurality of integral springs of the bearing housing.

[0111] According to the method described in the preceding clause, the base of the bearing housing is fixedly connected to the damper frame of the bearing damper assembly, such that the outer edge and the inner edge of the bearing housing are movable relative to the base of the housing and the damper frame.

[0112] According to any of the foregoing descriptions, the outer edge and the inner edge of the bearing housing are fixedly connected to the damper frame of the bearing damper assembly, such that the housing base of the bearing housing is movable relative to the outer edge, the inner edge, the damper frame, or all three.

[0113] While the foregoing description is directed to preferred embodiments, it should be noted that other variations and modifications will be apparent to those skilled in the art and can be made without departing from this disclosure. Furthermore, features described in connection with one embodiment can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A bearing damper assembly for a turbine engine, characterized in that, The bearing damper assembly defines a bearing damper centerline axis, a radial direction extending perpendicular to the bearing damper centerline axis, and a circumferential direction about the bearing damper centerline axis. The bearing damper assembly includes: Damper frame; A bearing housing disposed within the damper frame, the bearing housing being annular and comprising: Base of the outer shell; An outer edge, the outer edge being disposed radially outward of the housing base relative to the radial direction, the outer edge being connected to the housing base via a first plurality of integral springs, such that a first plurality of annular gaps are formed between the outer edge and the housing base, each of the first plurality of annular gaps being constrained in the circumferential direction by two of the first plurality of integral springs, the first plurality of integral springs being in fluid communication with a first fluid circuit of the bearing damper assembly; and An inner edge, disposed radially inside the housing base relative to the radial direction, is connected to the housing base via a second plurality of integral springs, forming a second plurality of annular gaps between the inner edge and the housing base. Each of the second plurality of annular gaps is constrained in the circumferential direction by two integral springs of the second plurality of integral springs, which are in fluid communication with a second fluid circuit of the bearing damper assembly; and An end sealing plate, which is connected to the bearing housing. The first plurality of annular gaps and the second plurality of annular gaps are configured to be filled with fluid via the first fluid circuit and the second fluid circuit, respectively, to dampen vibrations generated on the rotating components of the turbine engine.

2. The bearing damper assembly according to claim 1, characterized in that, It further includes an external spring comprising a plurality of spring fingers, each of the plurality of spring fingers having a first end fixedly connected to the frame of the turbine engine and a second end engaging the bearing housing.

3. The bearing damper assembly according to claim 1, characterized in that, in, The base of the bearing housing is fixedly connected to the damper frame, such that the outer edge and the inner edge are movable relative to the base of the housing, the damper frame, or both.

4. The bearing damper assembly according to claim 3, characterized in that, in, The end sealing plate is connected to the base of the bearing housing.

5. The bearing damper assembly according to claim 1, characterized in that, in, The outer edge and the inner edge of the bearing housing are fixedly connected to the damper frame, such that the base of the housing can move relative to the outer edge, the inner edge, the damper frame, or all three.

6. The bearing damper assembly according to claim 5, characterized in that, The device further includes an external spring comprising a plurality of spring fingers, each of the plurality of spring fingers having a first end fixedly connected to the frame of the turbine engine and a second end engaging the bearing housing, the base of the bearing housing being connected to the second end of the plurality of spring fingers.

7. The bearing damper assembly according to claim 1, characterized in that, in, The first plurality of annular gaps have a first gap size measured in the radial direction, and the second plurality of annular gaps have a second gap size measured in the radial direction, the second gap size being different from the first gap size.

8. The bearing damper assembly according to claim 7, characterized in that, in, The first gap size is larger than the second gap size.

9. The bearing damper assembly according to claim 1, characterized in that, in, The first plurality of integral springs have a first spring coefficient, and the second plurality of integral springs have a second spring coefficient different from the first spring coefficient.

10. The bearing damper assembly according to claim 9, characterized in that, in, The first spring constant is less than the second spring constant.

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