Gas turbine engine with inertia damping seal

Abstract

A gas turbine engine includes a compressor section and a turbine section in an axial flow arrangement, the compressor section and the turbine section defining an axially extending longitudinal centerline, and being arranged as a rotor and a stator. A floating seal assembly is disposed at an interface of the rotor and stator to seal at least a portion of the rotor and stator relative to each other. The floating seal assembly includes one or more inertial damping elements tuned to one or more frequencies.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to gas turbine engines, and more particularly, to gas turbine engines incorporating a seal. BACKGROUND

[0002] Turbine engines, and particularly gas turbine engines, are rotary engines that extract energy from a flow of working air that is passed serially through a compressor section, a combustor section, and a turbine section. Compressor and turbine stages include pairs of rotating blades and stationary vanes arranged axially. The compressor section, combustor section, and turbine section can be arranged in an axial flow arrangement and define at least one rotating element or rotor and at least one stationary component or stator. A seal assembly can be located between the stator and rotor and used to reduce leakage fluid between the rotor and stator. BRIEF DESCRIPTION OF DRAWINGS

[0003] A complete and enabling disclosure of the present disclosure, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification, which is to be referred to in conjunction with the drawings, wherein:

[0004] Figure 1 is a cross-sectional view of an exemplary gas turbine engine in accordance with exemplary aspects of the present disclosure.

[0005] Figure 2 is a cross-sectional view of a portion of a high pressure compressor of a gas turbine engine as shown in Figure 1 is an enlarged cross-sectional view of a portion of a high pressure compressor of a gas turbine engine as shown in

[0006] Figure 3A is a schematic perspective view of a floating seal assembly in accordance with exemplary aspects of the present disclosure.

[0007] Figure 3B is a schematic perspective view of a floating seal assembly in accordance with exemplary aspects of the present disclosure. Figure 3A is a schematic perspective view of a floating seal assembly in a partial rotational orientation of

[0008] Figure 4A is a schematic perspective view of an inertial damping element of a floating seal assembly oriented in an axial direction in accordance with exemplary aspects of the present disclosure.

[0009] Figure 4B is a schematic perspective view of an inertial damping element of a floating seal assembly oriented in a circumferential direction in accordance with exemplary aspects of the present disclosure.

[0010] Figure 5 is a schematic perspective view of a floating seal assembly in accordance with exemplary aspects of the present disclosure.

[0011] Figure 6A is a schematic perspective view of a floating seal assembly in accordance with exemplary aspects of the present disclosure. is a schematic perspective view of a floating seal assembly in accordance with exemplary aspects of the present disclosure.

[0012] Figure 6B Based on exemplary aspects of this disclosure Figure 6A A schematic perspective view of the floating sealing assembly in partial rotational orientation.

[0013] Figure 7 This is a schematic perspective view of a floating sealing assembly according to an exemplary aspect of this disclosure.

[0014] Figure 8 Based on exemplary aspects of this disclosure, such as Figure 1 An enlarged cross-sectional view of a portion of the gas turbine engine shown.

[0015] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0016] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0017] The term “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as superior or better than other implementations. Furthermore, all embodiments described herein should be considered exemplary unless explicitly stated otherwise. Unless the context clearly specifies otherwise, the singular forms “a,” “an,” and “the” include plural references. The term “at least one” in the context of, for example, “at least one of A, B, and C” means only A, only B, only C, or any combination of A, B, and C.

[0018] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components. Furthermore, 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 fluid flows, and “downstream” refers to the direction from which fluid flows.

[0019] The term "turbine" refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines that together generate torque output. The term "gas turbine engine" refers to an engine that has a turbine as all or part of its power source. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid electric versions of one or more of these engines.

[0020] The term “gas turbine engine” refers to an engine having a turbine machine as all or a portion of its power source. Example gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and the like, as well as hybrid electric versions of one or more of these engines.

[0021] The term “combustion section” refers to any heat adding system for a turbine machine. For example, the term combustion section can refer to a section including one or more of a deflagration combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat adding assembly. In certain example embodiments, a combustion section can include an annular combustor, a can combustor, a tubular combustor, a trapped vortex combustor (TVC), or other suitable combustion system, or combinations thereof.

[0022] The terms “low” and “high,” or their respective comparative forms (e.g., more “low” and more “high,” where applicable), when used in conjunction with a compressor, turbine, shaft, or spool component, or the like, refer to relative speeds within an engine, unless otherwise noted. For example, a “low turbine” or “low speed turbine” defines a component configured to operate at a lower rotational speed (e.g., maximum allowable rotational speed) than a “high turbine” or “high speed turbine” of the engine.

[0023] The terms “forward” and “aft” refer to relative locations within a gas turbine engine or vehicle, and are based on the normal operating attitude of the gas turbine engine or vehicle. More specifically, forward and aft are used herein with reference to the direction of travel of the vehicle and the direction of propulsive thrust of the gas turbine engine.

[0024] The terms “upstream” and “downstream” refer to the relative direction with respect to the flow of fluid in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows.

[0025] As used herein, the terms “axial” and “axially” refer to a direction and orientation that extends substantially parallel to a centerline of a gas turbine engine. Further, the terms “radial” and “radially” refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms “circumferential” and “circumferentially” refer to a direction and orientation that extends arcuately about the centerline of the gas turbine engine.

[0026] Unless otherwise noted, the terms “coupled,” “fixed,” “attached to” and the like, mean either a direct coupling, fixation, or attachment, or an indirect coupling, fixation or attachment through one or more intermediate departments or features unless otherwise stated herein.

[0027] As used herein, the terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0028] For purposes of the description hereinafter, the terms "upper," "lower," "right," "left," "vertical," "horizontal," "top," "bottom," "lateral," "longitudinal," and derivatives thereof shall relate to the embodiments as they are oriented in the drawings. However, it is to be understood that the embodiments can assume various alternative orientations and, accordingly, such specific embodiments are not to be considered as limiting.

[0029] As described herein, the subject matter of the present disclosure relates to the use of an additive manufacturing machine or system. As used herein, the term "additive manufacturing" generally refers to a manufacturing technique that fabricates a part in a layer-by-layer manner. An exemplary additive manufacturing machine can be configured to utilize any suitable additive manufacturing technique. The additive manufacturing machine can utilize an additive manufacturing technique that includes a powder bed fusion (PBF) technique, such as a direct metal laser melting (DMLM) technique, a selective laser melting (SLM) technique, a directed metal laser sintering (DMLS) technique, or a selective laser sintering (SLS) technique. In an exemplary PBF technique, thin layers of a powder material are sequentially applied to a build plane and then selectively fused or melted to one another in a layer-by-layer manner to form one or more three-dimensional objects. Additively manufactured objects are generally monolithic in nature and can have various integrated sub-components.

[0030] Additionally or alternatively, suitable additive manufacturing techniques can include, for example, a fused deposition modeling (FDM) technique, a direct energy deposition (DED) technique, a laser engineered net shaping (LENS) technique, a laser net shape manufacturing (LNSM) technique, a direct metal deposition (DMD) technique, a digital light processing (DLP) technique, and other additive manufacturing techniques that utilize an energy beam or other energy source to solidify an additive manufacturing material, such as a powder material. Indeed, any suitable additive manufacturing modality can be used with the presently disclosed subject matter.

[0031] Additive manufacturing techniques can generally be described as making an object by building the object point-by-point, line-by-line, layer-by-layer, typically in a vertical direction. Other methods of making are also conceivable and within the scope of the present disclosure. For example, although the discussion herein relates to adding material to form successive layers, the subject matter of the present disclosure can be practiced with any additive manufacturing technique or other manufacturing technique, including layer-additive processes, layer-subtractive processes, or hybrid processes.

[0032] The additive manufacturing processes described herein can be used to form components using any suitable material. For example, the material can be a metal, a ceramic, a polymer, an epoxy, a photopolymer resin, a plastic, or any other suitable material that can be in a solid, a powder, a sheet, a wire, or any other suitable form, or combinations thereof. Additionally or alternatively, example materials can include metals, ceramics, or adhesives, and combinations thereof. Example ceramics can include ultra-high temperature ceramics and / or precursors of ultra-high temperature ceramics, such as polymer precursors. For example, while the thickness can be determined based on any number of parameters and can be any suitable dimension, each successive layer can be between about 10 pm and about 200 pm.

[0033] As used herein, the term“build plane” refers to a plane defined by a surface on which an energy beam impinges to selectively irradiate and thus solidify a powder material during an additive manufacturing process. Typically, the surface of a powder bed defines the build plane. During irradiation of a respective layer of a powder bed, a previously irradiated portion of the respective layer can define a portion of the build plane. Prior to distribution of the powder material on the build module, a build plate supporting the powder bed typically defines the build plane.

[0034] As used herein, the term“solidify” refers to the solidification of a powder material as a result of irradiating the powder material, including by means of melting, fusing, sintering, and the like.

[0035] The present disclosure generally relates to inertial damping floating seal assemblies. The floating seal assemblies include one or more inertial damping elements that are tuned to or activated at certain frequencies to counter resonant modes of the floating seal assemblies while maintaining the primary function of the floating seal assemblies to track rotor motion at tight clearances. As used herein,“damping” refers to the decay of mechanical excitation. In example embodiments, one or more portions of the inertial damping elements are integrated with a fluid column of viscous fluid such that the fluid moves out of phase with the motion of the floating seal assembly and damps the vibration modes. Additionally or alternatively, the inertial damping elements can be coupled to the floating seal assemblies via springs that are tuned in axial, radial, and / or circumferential directions based on the natural frequencies of the floating seal assemblies. Additionally or alternatively, the floating seal assemblies can include one or more internal regions, such as cavities or pockets, such that the inertial damping elements include frictional damping elements disposed within the internal regions of the floating seal assemblies to apply particle damping to the various vibration modes.

[0036] Embodiments of this disclosure provide inherent damping without interaction with adjacent structures (as non-limiting examples, such as contact or friction) and without interfering with rotor tracking. Embodiments of this disclosure provide damping in a specific direction without affecting rotor tracking. Embodiments of this disclosure also enable tighter operating clearances and reduced leakage. Typically, in floating seal applications, a minimum clearance or gap is maintained between the rotor and stator interfaces. Minimum clearances are defined to accommodate the side-to-side, tilting, and / or swaying of conventional floating seal assemblies. Embodiments of this disclosure dampen such side-to-side, tilting, and / or swaying of the floating seal assembly, making it possible to reduce the minimum operating clearance between the rotor and stator.

[0037] Now refer to the attached diagram, Figure 1 This is a cross-sectional side view of a gas turbine engine 20 according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In one embodiment, the gas turbine engine 20 is a multi-axis high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." For example... Figure 1 As shown, the gas turbine engine 20 defines an axial direction A (extending parallel to the longitudinal centerline 22 provided for reference), a radial direction R, and a circumferential direction C extending about the longitudinal centerline 22. Generally, the gas turbine engine 20 includes a fan section 24 and a turbine 26 disposed downstream of the fan section 24.

[0038] The depicted exemplary turbine 26 generally includes a casing 28 defining an annular core inlet 30. The casing 28 at least partially surrounds, in a series flow relationship: an axial compressor section 29, which includes a turbocharger or low-pressure (LP) compressor 32 and a high-pressure (HP) compressor 34; a combustion section 36; a turbine section 37, which includes a high-pressure (HP) turbine 38 and a low-pressure (LP) turbine 40; and an exhaust nozzle 42.

[0039] High-pressure (HP) shaft 44 drives HP turbine 38 to HP compressor 34. Low-pressure (LP) shaft 46 drives LP turbine 40 to LP compressor 32. LP compressor 32, HP compressor 34, combustion section 36, HP turbine 38, LP turbine 40, and exhaust nozzle 42 together define a core airflow path 48 through the gas turbine engine 20. LP shaft 46 and HP shaft 44 are rotatable about longitudinal centerline 22 and are coupled to a set of rotatable elements that can collectively define rotor 51.

[0040] In the described embodiment, fan section 24 includes a fan 50 having a plurality of fan blades 52 spaced apart and coupled to disk 54. As depicted, the fan blades 52 extend generally outward from disk 54 in a radial direction R. Each fan blade 52 is operably coupled to a suitable pitch mechanism 56 by means of the fan blades 52, which is rotatable together with disk 54 about pitch axis P, the pitch mechanism 56 being configured to, for example, uniformly and collectively change the pitch of the fan blades 52.

[0041] The gas turbine engine 20 also includes a power gearbox 58. The fan blades 52, disk 54, and pitch mechanism 56 can rotate together about a longitudinal centerline 22 across the power gearbox 58 via the LP shaft 46. The power gearbox 58 includes multiple gears for adjusting the rotational speed of the fan 50 relative to the LP shaft 46, allowing the fan 50 and the LP shaft 46 to rotate at a more efficient relative speed.

[0042] Still referencing Figure 1 In an exemplary embodiment, the disk 54 is covered by a rotatable front hub 60 (sometimes referred to as a "rotor") of the fan section 24. The front hub 60 is aerodynamically shaped to facilitate airflow through a plurality of fan blades 52. Additionally, the exemplary fan section 24 includes an annular fan housing or outer nacelle 62 circumferentially surrounding at least a portion of the fan 50 and / or turbine 26. In the depicted embodiment, the outer nacelle 62 is supported relative to the turbine 26 by a plurality of circumferentially spaced struts or outlet guide vanes 64. Furthermore, a downstream section 66 of the outer nacelle 62 extends over the outer portion of the turbine 26 to define a bypass airflow passage 68 between them.

[0043] However, it should be understood that Figure 1 The exemplary gas turbine engine 20 depicted is provided by way of example only, and in other exemplary embodiments, the gas turbine engine 20 may have other configurations. Additionally or alternatively, although the depicted gas turbine engine 20 is configured as a geared gas turbine engine (e.g., including a power gearbox 58) and a variable-pitch gas turbine engine (e.g., including a fan 50 configured as a variable-pitch fan), in other embodiments, the gas turbine engine 20 may be configured as a direct-drive gas turbine engine (such that the LP shaft 46 rotates at the same speed as the fan 50), a fixed-pitch gas turbine engine (such that the fan 50 includes fan blades 52 that are not rotatable about the pitch axis P), or both. It should also be understood that in other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may (as appropriate) be incorporated into, for example, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet gas turbine engine.

[0044] During operation of the gas turbine engine 20, a certain amount of air 70 enters the gas turbine engine 20 through the external nacelle 62 and the corresponding inlet 72 of the fan section 24. As the certain amount of air 70 passes through the fan blades 52, a first portion of the air 74 is directed or directed into the bypass airflow passage 68, and a second portion of the air 76 is directed or directed into the core airflow path 48, or more specifically, into the LP compressor 32. The ratio between the first portion of air 74 and the second portion of air 76 is commonly referred to as the bypass ratio.

[0045] As the second portion of air 76 enters the LP compressor 32, one or more sequential stages of the low-pressure (LP) compressor rotor blades 80 and low-pressure (LP) compressor stator blades 78, coupled to the LP shaft 46, progressively compress the second portion of air 76 flowing through the LP compressor 32 toward the HP compressor 34. Next, one or more sequential stages of the high-pressure (HP) compressor rotor blades 84 and high-pressure (HP) compressor stator blades 82, coupled to the HP shaft 44, further compress the second portion of air 76 flowing through the HP compressor 34. This supplies compressed air to the combustion section 36, where it is mixed with fuel and combusted to provide combustion gases 86.

[0046] Combustion gas 86 is directed through HP turbine 38, where a portion of the thermal and / or kinetic energy from the combustion gas 86 is extracted via a sequential stage of high-pressure (HP) turbine stator blades 88 connected to the turbine housing and high-pressure (HP) turbine rotor blades 90 connected to the HP shaft 44, thus rotating the HP shaft 44 to support the operation of HP compressor 34. Combustion gas 86 is then directed through LP turbine 40, where a second portion of the thermal and kinetic energy is extracted from the combustion gas 86 via a sequential stage of low-pressure (LP) turbine stator blades 92 connected to the turbine housing and low-pressure (LP) turbine rotor blades 94 connected to the LP shaft 46, thus rotating the LP shaft 46 to support the operation of LP compressor 32 and / or the rotation of fan 50. Complementing the rotor 51, the stationary parts of the gas turbine engine 20 (such as the LP compressor stator blades 78, the HP compressor stator blades 82, the HP turbine stator blades 88, and the LP turbine stator blades 92) are also referred to individually or collectively as the stator 63. Therefore, the stator 63 can refer to the combination of non-rotating components throughout the gas turbine engine 20.

[0047] Combustion gas 86 is then directed through the exhaust nozzle 42 of turbine 26 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 74 increases significantly as it is directed through bypass airflow passage 68 before exiting the fan nozzle exhaust section 96 of gas turbine engine 20, also providing propulsive thrust. HP turbine 38, LP turbine 40, and exhaust nozzle 42 at least partially define a hot gas path 98 for directing combustion gas 86 through turbine 26.

[0048] Figure 2 Further shown Figure 1 The gas turbine engine 20 includes a rotor 51, a stator 63, and a floating seal assembly 100 disposed or positioned at the interface between the rotor 51 and the stator 63. In the example shown, at least a portion of the floating seal assembly 100 may be disposed on the HP turbine 38 ( Figure 1 The floating seal assembly 100 is located within and hangs from a portion of the stator 63, particularly from the HP turbine stator blade 88, which extends from the outer portion of the stator 63 and is situated between two adjacent HP turbine rotor blades 90. In the illustrated embodiment, the floating seal assembly 100 is a floating radial seal assembly. However, it will be understood that the floating seal assembly 100 may be positioned within any part of the gas turbine engine 20 (e.g., fan section 24, compressor section (e.g., LP compressor 32 and / or HP compressor 34) or turbine section (e.g., HP turbine 38 and / or LP turbine 40)). Figure 1 The floating seal assembly 100 can be positioned relative to any suitable rotating and stationary component of the gas turbine engine 20, or at its interface. Therefore, the floating seal assembly 100 can be positioned relative to any suitable stationary component (such as, but not limited to, LP compressor stator blade 78, HP compressor stator blade 82, HP turbine stator blade 88, or LP turbine stator blade 92). For the purposes of this disclosure, the HP turbine stator blade 88 or any other blade (e.g., LP compressor stator blade 78, HP compressor stator blade 82, or LP turbine stator blade 92) hanging from the stator 63 can be collectively referred to as the stator 63.

[0049] The floating seal assembly 100 may include a bracket assembly 102 supported by a stator 63 and having a seal seat 106 defining a sealing cavity 108. The floating seal assembly 100 may also include a seal body 104 at least partially located within the sealing cavity 108. One or more sealing surfaces 112 and a pivot connection 110 may be disposed between the seal body 104 and the bracket assembly 102. A seal 120 may be disposed between the seal body 104 and the bracket assembly 102. The seal 120 may be configured to restrict, restrain, or otherwise prevent fluid from intruding between a portion of the seal body 104 and the bracket assembly 102 and into the sealing cavity 108.

[0050] During operation of the gas turbine engine 20, the working fluid 114 can flow over the HP turbine rotor blades 90 and the HP turbine stator blades 88. In a specific example, the working fluid 114 can be supplied by a second portion of air 76 ( Figure 1 However, it will be understood that the working fluid 114 can be any suitable working fluid or airflow, such as, but not limited to, the second portion of air 76. Figure 1 Combustion gases, ambient airflow, any combination thereof, or any other suitable fluid as described herein. Most of the working fluid 114 may flow over the HP turbine rotor blades 90 and HP turbine stator blades 88 to define the core airflow path 48. Figure 1 Leaking fluid 116 is diverted from working fluid 114 and enters the HP compressor rotor blades 84 and HP compressor stator blades 82. Figure 1 The space between the stator 63 (e.g., the radially inner portion of the HP turbine stator blade 88) and the rotor 51 flows. Furthermore, specific portions of the gas turbine engine 20 can be defined by various pressure differentials. As a non-limiting example, one side of the floating seal assembly 100 (e.g., in this case, axially forward or upstream of the floating seal assembly 100) can be defined by pressure 122, while other portions (e.g., in this case, axially rearward or downstream of the floating seal assembly 100) can be defined by pressure 124. Pressure 122 can be higher than pressure 124, thereby defining a pressure differential across the floating seal assembly 100.

[0051] The floating seal assembly 100 can reduce or otherwise eliminate the amount of leaking fluid 116 flowing from the upstream portion of the HP turbine stator blades 88 exposed to pressure 122 to the downstream portion of the HP turbine stator blades 88 exposed to pressure 124. This is accomplished via a labyrinth between the stator 63 and the rotor 51. In other words, the floating seal assembly 100 can create a tortuous path for the leaking fluid 116, thereby reducing or eliminating the amount of leaking fluid 116 that could flow around the radially inward portion of the stator 63. The seal body 104 can move freely in the radial direction within the sealing cavity 108. The seal body 104 may also include aerodynamic lift-generating features (not shown) (such as, but not limited to, helical grooves, Rayleigh pads), or otherwise include curvature mismatch between the radii of the seal body 104 and the rotor 51. The aerodynamic lift-generating features can generate a fluid film between the seal body 104 and the rotor 51. The fluid film can generate lift between the rotor 51 and the seal 104, allowing the seal 104 to float on the rotor 51 without rubbing, touching, or otherwise contacting the rotor 51.

[0052] Figure 3A and Figure 3BThis is a schematic perspective view of a floating seal assembly 100 according to aspects of the present disclosure. In the illustrated embodiment, the floating seal assembly 100 includes one or more inertial damping elements 130. Embodiments of the one or more inertial damping elements 130 provide tuned inertial damping that is activated at certain frequencies to counteract resonant vibration modes of the floating seal assembly 100 while maintaining the primary function of the floating seal assembly 100 in tracking the motion of the rotor 51 with a tight clearance from the rotor 51. In an exemplary embodiment, the one or more inertial damping elements 130 include one or more tubes 140 containing or integrated with a fluid 142. The fluid 142 may be a viscous fluid (as a non-limiting example, such as a liquid, such as a silicone damping fluid), such that the fluid 142 moves out of phase with the motion of the floating seal assembly 100 at a target frequency where damping is desired. In an exemplary embodiment, the dimensions and / or orientation of the one or more tubes 140 are designed to enable damping in one or more of the axial direction A, radial direction R, or circumferential direction C. Figure 3B The floating seal assembly 100 is depicted in terms of vibrational movement in the axial direction. However, it should be understood that the floating seal assembly 100 may also experience vibrational movement in the radial direction R or the circumferential direction C. Correspondingly, one or more inertial damping elements 130 may be positioned or oriented to dampen axial, radial, and / or circumferential vibrations.

[0053] In an exemplary embodiment, one or more tubes 140 may include one or more hollow cylindrical tube segments 144. The dimensions and / or orientation of the one or more tube segments 144 are designed to enable damping in one or more of the axial direction A, radial direction R, or circumferential direction C. In an exemplary embodiment, one or more tubes 140 may be U-shaped geometries, having a single tube segment 144A extending between a pair of tube segments 144B, 144C, wherein tube segments 144B, 144C are positioned at opposite ends of tube segment 144A and are positioned at least partially perpendicular to tube segment 144A. However, it should be understood that one or more tubes 140 may be constructed with other geometries. A fluid 142 disposed within the tube 140 serves as a tuned damper corresponding to a specific frequency. In an exemplary embodiment, one or more factors may be used to construct the inertial damping element 130 to dampen vibrations corresponding to a specific direction and frequency. Non-limiting examples include, for instance, the cross-sectional area of ​​pipe segment 144, the density of fluid 142, the height of the column of fluid 142 (e.g., within pipe segments 144B, 144C), the width of the column of fluid 142 (e.g., within pipe segment 144A), and acceleration due to gravity. In exemplary embodiments, such as in aerospace applications (for example, an aircraft having a gas turbine engine incorporating a floating seal assembly 100 according to aspects of this disclosure), acceleration due to gravity is influenced at least based on the different G-values ​​or loads experienced during different flight conditions based on vertical acceleration (e.g., takeoff and landing, and cruise). Embodiments of this disclosure construct an inertial damping element 130 to dampen vibrations corresponding to a specific direction and frequency based on different flight conditions or G-loads that the floating seal assembly 100 will encounter, or to dampen vibrations corresponding to a specific direction and frequency activated under different flight conditions or G-loads that the floating seal assembly 100 will encounter. Therefore, in exemplary embodiments, different inertial damping elements 130 can be tuned to account for different or corresponding G-loads. Figure 3B As depicted, in response to the swaying or pitching movement of the floating seal assembly 100 relative to the axial direction A (by... Figure 3B (Indicated by direction 150), fluid 142 flows out of phase relative to a specific resonant frequency within pipe section 144.

[0054] exist Figure 3A and Figure 3B In the illustrated embodiment, one or more inertial damping elements 130 are fixed or coupled to the outer surface or outward-facing surface of the seal 104. In the illustrated embodiment, one or more inertial damping elements 130 are positioned relative to the rotor 51 ( Figure 2It is fixed or coupled to the radially outward surface 152 of the seal body 104; however, it should be understood that one or more inertial damping elements 130 may be otherwise positioned relative to the seal body 104 or located elsewhere on the floating seal assembly 100. Although Figure 3A and Figure 3B Only a single inertial damping element 130 is depicted, but it should be understood that two or more inertial damping elements 130 may be positioned on the floating seal assembly 100 to dampen vibrations in other directions and at other resonant frequencies.

[0055] Figure 4A and Figure 4B Exemplary positions and / or orientations of the inertial damping element 130 relative to various directions are depicted. For example... Figure 4A As depicted, the inertial damping element 130 is oriented relative to the axial direction to dampen the swaying or pitching movement of the floating seal assembly 100 relative to the axial direction A, indicated by direction 150. Figure 4B As depicted, the inertial damping element 130 is oriented relative to the circumferential direction to dampen the swaying or pitching movement of the floating seal assembly 100 relative to the circumferential direction C, indicated by direction 160. Therefore, it should be understood that one or more inertial damping elements 130 may be arranged in their own different orientations to dampen vibrations corresponding to different directions (e.g., pitch, roll, or yaw) at a specific frequency.

[0056] Figure 5 This is a schematic perspective view of a floating seal assembly 100 according to aspects of the present disclosure. In the illustrated embodiment, the floating seal assembly 100 includes an inner region 170 formed within a seal body 104. The inner region 170 may be a closed or open cavity, or other type of location disposed within an outer boundary 172 of the seal body 104. In the illustrated embodiment, one or more inertial damping elements 130 are disposed within the inner region 170. In the illustrated embodiment, one or more inertial damping elements 130 are positioned to dampen vibrations in the axial direction A; however, it should be understood that the orientation of one or more of the inertial damping elements 130 may vary to dampen vibrations in other directions, such as the radial direction R and the circumferential direction C. It should also be understood that the floating seal assembly 100 may include a combination of inertial damping elements 130 disposed externally relative to the seal body 104 and inertial damping elements 130 disposed internally.

[0057] Figure 6A and Figure 6B This is a schematic perspective view of a floating seal assembly 100 according to aspects of the present disclosure. In the illustrated embodiment, the floating seal assembly 100 includes one or more inertial damping elements 130. In the illustrated embodiment, the one or more inertial damping elements 130 are formed as rigid, solid, or non-fluid damping elements, rather than as combined...Figure 3A , Figure 3B , Figure 4A and Figure 4B Depicting and describing fluid-based damping elements. Figure 6A and Figure 6B In this embodiment, one or more inertial damping elements 130 include one or more mass elements 180 coupled to the seal 104 via one or more compliant elements 182. The one or more compliant elements 182 are tuned in one or more of the axial direction A, radial direction R, or circumferential direction C. The one or more compliant elements 182 can be any type of elastic device that provides a desired amount of compliance (e.g., expansion and compression) such that the compliant element 182 returns to its original shape or position after extension or deformation. As a non-limiting example, this could be any type of spring (e.g., leaf spring, coil spring, etc.) or flexure generated in place using wire electrical discharge machining (EDM) technology. In an exemplary embodiment, the one or more mass elements 180 function as dampers by being out of phase with the motion of the seal 104 at certain specific frequencies. In the illustrated embodiment, a single mass element 180 is depicted oriented along the axial direction A and coupled to the seal 104 via two compliant elements 182; however, with combination... Figure 3A , Figure 3B , Figure 4A and Figure 4B Similarly, as described, one or more mass elements 180 may be oriented in other directions, and the mass elements 180 may be coupled to the seal 104 using additional or fewer compliant elements 182 having the same or different stiffness levels. Figure 6B As depicted, the seal 104 can undergo rocking vibration movement along the axial direction A, indicated by direction 190, and can undergo rocking movement in the radial direction R, indicated by direction 192. Mass element 180 moves out of phase with the movement of the seal 104 in the axial direction A (indicated by direction 194) and radial direction R (indicated by direction 196) via conforming element 182. In the illustrated embodiment, one or more mass elements 180 are coupled to surface 152 of the seal 104 via one or more conforming elements 182; however, it should be understood that one or more mass elements 180 can be coupled to other locations of the seal 104 via one or more conforming elements 182. Additionally, in the illustrated embodiment, one or more mass elements 180 are coupled to the outer surface of the seal 104; however, with... Figure 5 Similar to that depicted, one or more mass elements 180 and corresponding compliant elements 182 can be coupled to the internal regions of the seal 104, such as internal region 170. Figure 5 Additionally, the floating seal assembly 100 may include a combination of an internally disposed mass element 180 and an externally disposed mass element 180 and a corresponding conforming element 182.

[0058] Figure 7 This is a schematic perspective view of a floating seal assembly 100 according to aspects of this disclosure. In the illustrated embodiment, the floating seal assembly 100 includes one or more inertial damping elements 130. Figure 7 In the illustrated embodiment, one or more inertial damping elements 130 include friction damping elements 200 disposed within one or more internal regions 202 of the seal 104. The internal region 202 may be a closed cavity disposed within the outer boundary of the seal 104. In an exemplary embodiment, the one or more internal regions 202 may be positioned at different locations within the seal 104 and may be configured with different geometries to provide vibration damping in one or more of the axial direction A, radial direction R, and circumferential direction C. In an exemplary embodiment, the friction damping element 200 includes a plurality of loose materials that absorb energy via frictional dissipation. The friction damping element 200 may include any type of loose material, such as granular materials as a non-limiting example. In an exemplary embodiment, the seal 104 may be additively manufactured. In such an exemplary embodiment, the friction damping element 200 may be unconsolidated powder 204. In such an exemplary embodiment, the seal 104 may be formed by an additive manufacturing process such that the powder 204 is consolidated in the region of the seal 104 surrounding the internal region 202 to form the internal region 202. A portion of powder 204 can be applied to the region of the inner region 202 during the additive manufacturing process, but without agglomeration, so that powder 204 remains loose or unconsolidated within the inner region 202. Therefore, the unconsolidated powder 204 absorbs energy through frictional dissipation within the inner region 202.

[0059] As described above, it has one or more inertial damping elements 130 ( Figure 3A-7 ) floating seal assembly 100 ( Figure 3A-7 ) can be positioned in the gas turbine engine 20 ( Figure 1 ) gas turbine engine 20 ( Figure 1 Between any suitable rotating and stationary parts. Figure 8 A floating seal assembly 300 configured as a floating surface seal assembly is further illustrated. The floating seal assembly 300 can be configured similarly to include a combination Figure 3A-7 The floating seal assembly 100 of one or more of the inertial damping elements 130 described and illustrated Figure 3A-7 It should be understood that the floating seal assembly 300 may have a different shape or appearance than that shown. The stator 63 may be a turbine 26. Figure 1 The housing of ) and the rotor 51 can be the turbine 26 ( Figure 1 The shaft of the rotor 51. The floating seal assembly 300 is disposed between the stator 63 and the rotor 51.

[0060] In the example shown, the floating seal assembly 300 includes a seal body 302. This is combined with the floating seal assembly 100 described above. Figure 3A-7 Similar to the description, one or more inertial damping elements 130 may be located on and / or coupled to the outer surface of the seal 302, disposed within the inner region 304 of the seal 302, or any combination thereof.

[0061] Therefore, embodiments of this disclosure provide a floating seal assembly with one or more inertial damping elements, which are tuned to or activated at certain frequencies to counteract the resonant modes of the floating seal assembly while maintaining the primary function of the floating seal assembly in tracking rotor motion within a tight clearance. Embodiments of this disclosure provide inherent damping without interaction with adjacent structures (as a non-limiting example, such as contact or friction) and without interfering with rotor tracking. Embodiments of this disclosure provide damping to accommodate the lateral, tilting, and / or swaying of conventional floating seal assemblies and enable a reduction in the minimum operating clearance between the rotor and stator. Embodiments of the floating seal assembly according to this disclosure may include multiple inertial damping elements, each configured to address different resonant frequencies and different accelerations due to different G-values ​​experienced by the carrier incorporating the floating seal assembly.

[0062] This written description uses examples to disclose this disclosure, including best practices, and to enable any person skilled in the art to practice this disclosure, including making and using any device or system and methods of making any combination. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0063] Further details are provided by the following topics:

[0064] A gas turbine engine includes: a compressor section and a turbine section arranged in an axial flow configuration, the compressor section and the turbine section defining an axially extending longitudinal centerline and arranged as a rotor and a stator; and a floating seal assembly disposed at the interface of the rotor and the stator, the floating seal assembly including one or more inertial damping elements tuned to one or more frequencies.

[0065] According to the gas turbine engine described in the foregoing clause, at least one of the one or more inertial damping elements comprises fluid.

[0066] According to any of the preceding clauses, in a gas turbine engine, at least one of the one or more inertial damping elements comprises: one or more tubes; and fluid disposed within the one or more tubes.

[0067] A gas turbine engine according to any of the foregoing clauses, wherein one or more pipes are U-shaped.

[0068] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal body, and at least one of the one or more inertial damping elements is positioned within an inner region of the seal body.

[0069] According to any of the preceding clauses, the turbine engine includes a floating seal assembly comprising a seal body, and at least one of the one or more inertial damping elements is coupled to the outer surface of the seal body.

[0070] According to any of the foregoing clauses, the turbine engine, wherein the floating seal assembly includes a seal body, and wherein a first inertial damping element of the one or more inertial damping elements is coupled to an outer surface of the seal body, and a second inertial damping element of the one or more inertial damping elements is disposed within an inner region of the seal body.

[0071] According to any of the preceding clauses, in a gas turbine engine, at least one of the one or more inertial damping elements comprises one or more tubes oriented in at least one of the axial, radial, or circumferential directions.

[0072] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal body, and at least one of the one or more inertial damping elements includes: one or more mass elements; and one or more compliant elements that connect the one or more mass elements to the seal body.

[0073] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal having one or more internal zones, and at least one of the one or more inertial damping elements includes one or more friction damping elements disposed within the one or more internal zones.

[0074] The gas turbine engine according to any of the foregoing clauses, wherein the one or more friction damping elements comprise unconsolidated powder.

[0075] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal body having one or more internal regions defined during an additive manufacturing process, and at least one of the one or more internal regions includes unconsolidated powder from the additive manufacturing process.

[0076] The gas turbine engine according to any of the foregoing clauses, wherein the floating seal assembly includes at least one of a floating radial seal assembly or a floating surface seal assembly.

[0077] According to any of the preceding clauses, in a gas turbine engine, at least one of the one or more inertial damping elements comprises at least one fluid-filled U-tube.

[0078] According to any of the foregoing clauses, the gas turbine engine wherein the one or more inertial damping elements include a first inertial damping element tuned to a first frequency and a second inertial damping element tuned to a second frequency, the second frequency being different from the first frequency.

[0079] In any of the preceding clauses of the gas turbine engine, at least one of the first and second inertial damping elements comprises fluid.

[0080] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal body, and at least one of the first and second inertial damping elements comprises: one or more mass elements; and one or more compliant elements that connect the one or more mass elements to the seal body.

[0081] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal defining an inner region, and at least one of the first inertial damping element and the second inertial damping element is disposed within the inner region.

[0082] According to any of the preceding clauses, in a gas turbine engine, the floating seal assembly includes a seal body, and the seal body includes one or more internal regions, and at least one of the first inertial damping element and the second inertial damping element includes one or more friction damping elements disposed within the one or more internal regions.

[0083] The gas turbine engine according to any of the foregoing clauses, wherein the floating seal assembly includes at least one of a floating radial seal assembly or a floating surface seal assembly.

[0084] A gas turbine engine includes: a compressor section and a turbine section arranged in an axial flow configuration, the compressor section and the turbine section defining an axially extending longitudinal centerline and arranged as a rotor and a stator; and a floating seal assembly that seals at least a portion of the rotor and the stator relative to a first pressure zone and a second pressure zone, the first pressure zone being pressurized greater than the second pressure zone, the floating seal assembly including one or more inertial damping elements that dampen vibrations in at least one of an axial direction, a radial direction, or a circumferential direction at one or more frequencies.

[0085] According to any of the preceding clauses, in a gas turbine engine, at least one of the one or more inertial damping elements comprises: one or more tubes oriented in at least one of the axial direction, the radial direction, or the circumferential direction; and fluid disposed within the one or more tubes.

[0086] A floating seal assembly for sealing the interface between a rotating component and a stationary component of a gas turbine engine, the floating seal assembly comprising: a seal body including one or more sealing surfaces configured to define one or more seals between the rotating component and the stationary component; and one or more inertial damping elements coupled to the seal body and tuned to one or more frequencies.

[0087] The floating sealing assembly according to any of the foregoing clauses, wherein at least one of the one or more inertial damping elements contains fluid.

[0088] According to any of the foregoing clauses, in a floating seal assembly, at least one of the one or more inertial damping elements is positioned within the inner region of the seal body.

[0089] The floating seal assembly according to any of the foregoing clauses, wherein the one or more inertial damping elements include a first inertial damping element tuned to a first frequency and a second inertial damping element tuned to a second frequency, the second frequency being different from the first frequency.

[0090] According to any of the foregoing clauses, in a floating seal assembly, at least one of the one or more inertial damping elements comprises: one or more mass elements; and one or more compliant elements that connect the one or more mass elements to the seal body.

[0091] The floating seal assembly according to any of the foregoing clauses, wherein the seal body includes one or more internal regions, and wherein at least one of the one or more inertial damping elements includes one or more friction damping elements disposed within the one or more internal regions.

[0092] The floating seal assembly according to any of the foregoing clauses, wherein the one or more inertial damping elements include a first inertial damping element tuned to a first frequency and a second inertial damping element tuned to a second frequency, the second frequency being different from the first frequency.

[0093] The floating seal assembly according to any of the foregoing clauses, wherein the one or more inertial damping elements include a first inertial damping element tuned to a first G-load and a second inertial damping element tuned to a second G-load, the second G-load being different from the first G-load.

[0094] The floating sealing assembly according to any of the foregoing clauses, wherein the floating sealing assembly includes at least one of a floating radial sealing assembly or a floating surface sealing assembly.

Claims

1. A gas turbine engine, characterized in that, include: A compressor section and a turbine section are arranged in an axial flow configuration, the compressor section and the turbine section defining an axially extending longitudinal centerline and being arranged as a rotor and a stator; as well as A floating seal assembly disposed at the interface between the rotor and the stator, the floating seal assembly including one or more inertial damping elements tuned to one or more frequencies.

2. The gas turbine engine according to claim 1, characterized in that, in, At least one of the one or more inertial damping elements comprises a fluid.

3. The gas turbine engine according to claim 1, characterized in that, in, At least one of the one or more inertial damping elements includes: One or more tubes; and Fluid, wherein the fluid is disposed within one or more tubes.

4. The gas turbine engine according to claim 1, characterized in that, in, The floating seal assembly includes a seal body, and at least one of the one or more inertial damping elements is positioned within the inner region of the seal body.

5. The gas turbine engine according to claim 1, characterized in that, in, The floating seal assembly includes a seal body, and at least one of the one or more inertial damping elements is coupled to the outer surface of the seal body.

6. The gas turbine engine according to claim 1, characterized in that, in, At least one of the one or more inertial damping elements comprises one or more tubes oriented in at least one of the axial, radial, or circumferential directions.

7. The gas turbine engine according to claim 1, characterized in that, in, The floating seal assembly includes a seal body, and at least one of the one or more inertial damping elements comprises: One or more mass elements; and One or more compliant elements, which connect the one or more mass elements to the seal.

8. The gas turbine engine according to claim 1, characterized in that, in, The floating seal assembly includes a seal having one or more internal zones, and at least one of the one or more inertial damping elements includes one or more friction damping elements disposed within the one or more internal zones.

9. The gas turbine engine according to claim 8, characterized in that, in, The one or more friction damping elements comprise unconsolidated powder.

10. The gas turbine engine according to claim 1, characterized in that, in, The floating sealing assembly includes at least one of a floating radial sealing assembly or a floating surface sealing assembly.

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