Seal assembly having at least one damping element

Abstract

A seal assembly for a turbomachine, comprising: a rotating component; the non-rotating component is provided with a ring bearing part, a face sealing ring and a joint arranged between the ring bearing part and the non-rotating component. The non-rotating component and the rotating component are arranged at a sealing interface. The joint is linearly and obliquely displaceable to allow displacement of the non-rotating component relative to the rotating component. The sealing interface defines a gap between the face seal ring and the rotating component. The seal assembly further includes at least one damping element arranged with the ring carrier for holding the seal assembly centered in a radial direction in the turbine. In addition, the damping element comprises at least one mass element.

Description

[0001] Priority information

[0002] This application claims priority to Indian patent application serial number 202311049688 filed on July 24, 2023. Technical Field

[0003] The present invention relates generally to turbomachines and, more particularly, to a seal assembly, such as a face seal ring, having at least one damping element for reducing radial vibrations of the turbomachine. Background Art

[0004] A turbine includes a compressor and / or a turbine, such as a gas turbine, a steam turbine, and a hydro turbine. In general, a turbine includes a rotor and a stator, and the rotor may be a shaft or a drum that supports turbine blades and a stator. For example, the turbine blades may be arranged in stages along the rotor of the turbine. The turbine may also include various seals to reduce or prevent leakage of flows (e.g., working fluid flows) between various components of the turbine. For example, the turbine may include one or more face seal rings configured to reduce or prevent leakage of flows between a shaft (e.g., a rotating shaft) and a housing of the turbine.

[0005] However, it is difficult to design a seal in which the center of fluid pressure always passes through the geometric center of the seal. Therefore, there is usually a pressure-torque coupling between the radial and axial vibrations of the seal. The presence of radial vibration of the stator can cause a significant reduction in the axial clearance between the rotor and the seal, including catastrophic rubbing. High seal response amplitudes can also increase interface wear, thereby limiting the service life of the seal. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] In the specification with reference to the accompanying drawings, a complete and enabling disclosure of the present invention including the best mode thereof is set forth for those skilled in the art, in which:

[0007] Figure 1 shows a cross-sectional view of an embodiment of a gas turbine engine having a seal assembly according to the present disclosure;

[0008] Figure 2 Shows Figure 1 An enlarged cross-sectional view of a sealing component;

[0009] Figure 3 shows a cross-sectional view of an embodiment of a sealing assembly according to the present disclosure;

[0010] Figure 4 A partial perspective view of an embodiment of a sealing interface between a rotor ring and a stator slider of a seal assembly according to the present disclosure is shown.

[0011] Figure 5A and Figure 5B shows a partial front view of an embodiment of a plurality of damping elements for a seal assembly according to the present disclosure;

[0012] Figure 6 A partial cross-sectional view of a seal assembly of a turbomachine is shown, particularly showing an embodiment of a damping element of the seal assembly;

[0013] Figure 7 A partial cross-sectional view of a seal assembly of a turbomachine is shown, particularly showing an embodiment of a damping element of the seal assembly;

[0014] Fig. 8A and Figure 8B A schematic diagram showing various components of a seal assembly of a turbomachine, and in particular showing an embodiment of a damping element of the seal assembly;

[0015] Fig.9A and Fig. 9B A schematic diagram showing various components of a sealing assembly of a turbine, and in particular showing another embodiment of a damping element of the sealing assembly;

[0016] Fig.10 A partial cross-sectional view of a seal assembly of a turbomachine is shown, particularly showing an embodiment of a damping element of the seal assembly;

[0017] Fig.11 A partial cross-sectional view of a seal assembly of a turbomachine is shown, particularly showing an embodiment of a damping element of the seal assembly;

[0018] Fig. 12A and Fig. 12B A schematic diagram showing various components of a sealing assembly of a turbine, and in particular showing another embodiment of a damping element of the sealing assembly;

[0019] Fig.13 shows a graph of seal response / static excitation (y-axis) versus stator vibration frequency / seal radial natural frequency (x-axis) in accordance with the present disclosure; and

[0020] Fig.14 The embodiment of the present disclosure is shown as c a / (2√(m a k a )(y-axis) versus mass fraction (x-axis).

[0021] Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present disclosure. DETAILED DESCRIPTION

[0022] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are shown in the accompanying drawings. Each example is provided to explain the present disclosure, not to limit the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the present disclosure without departing from the scope or spirit of the present disclosure. For example, a feature shown or described as part of one embodiment may be used together with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0023] As used herein, the word "exemplary" means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. In addition, unless expressly noted otherwise, all embodiments described herein should be considered exemplary.

[0024] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0025] In a context such as “at least one of A, B, and C,” the term “at least one of” means only A, only B, only C, or any combination of A, B, and C.

[0026] The term “turbomachine” refers to a machine that includes one or more compressors, a heat generating section (eg, a combustion section), and one or more turbines that together produce a torque output.

[0027] The term "gas turbine engine" refers to an engine having a turbine as all or part of its power source. Exemplary gas turbine engines include turbofan engines, turboprop engines, turbojets, turboshaft engines, etc., as well as hybrid electric versions of one or more of these engines.

[0028] The term "combustion section" refers to any heat addition system of a turbomachine. For example, the term combustion section may refer to a section that includes one or more of a deflagration combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In certain example embodiments, the combustion section may include an annular combustor, a can combustor, a duct combustor, a trapped vortex combustor (TVC), or other suitable combustion systems, or combinations thereof.

[0029] As used herein, the term "rotor" refers to any component of a rotating machine, such as a turbine engine, that rotates about an axis of rotation. For example, a rotor may include a shaft or spool of a rotating machine, such as a turbine engine.

[0030] As used herein, the term "stator" refers to any component of a rotating machine, such as a turbine engine, that has a coaxial construction and arrangement with a rotor of the rotating machine. The stator may be disposed radially inwardly or radially outwardly along a radial axis relative to at least a portion of the rotor. Additionally, or alternatively, the stator may be disposed axially adjacent to at least a portion of the rotor.

[0031] When used with reference to compressors, turbines, shaft or spool components, etc., the terms "low" and "high" or their respective comparative degrees (e.g., lower, higher, where applicable) refer to relative rotational speeds within the engine, unless otherwise specified. For example, a "low turbine" or "low-speed turbine" defines a component that is 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.

[0032] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, front refers to a position closer to the engine inlet, while rear refers to a position closer to the engine nozzle or exhaust.

[0033] The terms "upstream" and "downstream" refer to the relative directions of the fluid flow in the fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing.

[0034] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of the gas turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc around the centerline of the gas turbine engine.

[0035] Unless otherwise stated, the terms "coupled," "fixed," "attached to," and the like refer to both direct coupling, fixing, or attachment as well as indirect coupling, fixing, or attachment via one or more intermediate components or features.

[0036] As used herein, the terms "first," "second," "third," etc. may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0037] The term "adjacent" as used herein with respect to two walls and / or surfaces means that the two walls and / or surfaces are in contact with each other, or that the two walls and / or surfaces are separated only by one or more non-structural layers and the two walls and / or surfaces and the one or more non-structural layers are in a series contact relationship (i.e., a first wall / surface contacts the one or more non-structural layers, and the one or more non-structural layers contacts the second wall / surface).

[0038] As used herein, the terms "monolithic," "unitary," or "monolithic" used to describe a structure refer to a structure that is integrally formed from a continuous material or group of materials, without seams, connecting joints, etc. The monolithic, unitary structures described herein may be formed by additive manufacturing to have the described structure, or may alternatively be formed by a casting process, etc.

[0039] Approximate language as used in the entire specification and claims herein is applied to modify any quantitative representation that can allow variation without causing the basic function associated therewith to change. Therefore, the value modified by one or more terms such as "about", "approximately" and "substantially" is not limited to the specified exact value. In at least some cases, approximate language can correspond to the precision of the instrument used to measure the value or the precision of the method or machine used to construct or manufacture parts and / or systems. For example, approximate language can refer to within a margin of 1%, 2%, 4%, 10%, 15% or 20%. These approximate margins can be applied to a single value, define any end point or two end points of a numerical range, and / or the margin of the range between the end points.

[0040] Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein include the endpoints, and the endpoints are independently combinable with each other.

[0041] The present disclosure generally relates to a sealing assembly for a rotating machine having at least one damping element. The sealing assembly according to an embodiment of the present disclosure can be used in any rotating machine, and is particularly suitable for rotating machines including turbines and gas turbine engines, etc. In certain embodiments, the sealing assembly according to the present disclosure includes an air-breathing seal that provides a pressurized fluid film between the seal face and the rotor face. The fluid film can be provided by one or more suction ducts (e.g., high-pressure suction ducts) that allow a fluid (e.g., pressurized air or gas in a turbine engine) to flow from a high-pressure area on one side of the seal assembly to a low-pressure area on the other side of the seal assembly. In other embodiments, the fluid flowing through the suction duct provides a pressurized fluid film between the seal face and the rotor face. The pressurized fluid film can act as a fluid bearing, such as a gas bearing, which inhibits contact between the seal and the rotor. For example, the fluid bearing can be a hydrostatic bearing, an aerostatic bearing, an aerodynamic bearing, or a combination of aerostatic and aerodynamic features known as a hybrid bearing, etc.

[0042] Therefore, the sealing assembly according to the embodiments of the present disclosure is generally considered to be a non-contact seal because the fluid bearing generally inhibits contact between the sealing face and the rotor face. Specifically, the sealing assembly of the present disclosure generally includes a main seal defined by the rotor face of the sealing rotor and the slider face of the sealing slider. The main seal can be configured as an air intake face seal ring, a fluid bearing, a gas bearing, etc. In addition, or as an alternative, the main seal can be configured as a radial film riding seal, an axial film riding seal, a radial carbon seal, an axial carbon seal, or the like.

[0043] However, for such seals, it is difficult to design a seal where the center of fluid pressure always passes through the geometric center of the seal. Therefore, there is usually a pressure-torque coupling between the radial and axial vibrations of the seal. The presence of radial vibration of the stator can cause a significant reduction in the axial clearance between the rotor and the seal, including catastrophic rubbing. The high seal response amplitude also increases interface wear, thereby limiting the service life of the seal. Under high vibration, stall and / or high thermal gradients, non-contacting parts may contact each other, resulting in metal-to-metal friction and / or seal wear. This contact may change the sealing force balance and may also cause the seal to run tighter, resulting in more wear.

[0044] Therefore, the present disclosure generally relates to a sealing assembly for a rotating machine having at least one damping element. For example, in certain embodiments, the present disclosure generally relates to a sealing assembly that introduces a tuned mass damper element into the design of a face seal ring. Specifically, in one embodiment, the sealing assembly of the present disclosure includes features on a sealing slider of a face seal ring that accommodates a circumferential mass segment, as well as springs and damping elements. In addition, in one embodiment, the spring and damping elements are both in the axial and radial directions. Various embodiments of the spring element can be utilized, including but not limited to leaf springs, coil springs, bends generated in situ using wire electrical discharge machining (EDM), and the like. Therefore, in one embodiment, the damping element allows the seal to remain centered in the radial direction. Isolating the seal from radial vibrations can achieve reliable, frictionless operation of the seal in the presence of significant radial vibrations in the stator.

[0045] Furthermore, in one embodiment, the seal assembly of the present disclosure operates by adding as little as about 5% to about 10% additional mass to the seal slider. Additionally, in one embodiment, the damping parameter is defined and selected in a range (e.g., from about 0.1 to about 0.7) that simultaneously allows for the following two defined parameters: broadband frequency attenuation benefit and operating frequency amplification, up to 0.5.

[0046] Reference now Figure 1 , showing a cross-sectional view of an embodiment of a gas turbine engine having a seal assembly according to the present disclosure, Figure 2 Shows Figure 1 1 is an enlarged cross-sectional view of a seal assembly of a gas turbine engine 10. In particular, as shown, the gas turbine engine 10 includes a high pressure gas generator 12 having a single-stage centrifugal compressor 18 as a final compressor stage. The high pressure gas generator 12 has a high pressure rotor 14 including a high pressure compressor 16, a combustor 19, and a high pressure turbine 20 in downstream flow relationship. The rotor 14 is rotatably supported about an engine centerline 22 by a first or forward bearing 24 in a forward frame 26 and an aft bearing 28 disposed downstream of the high pressure turbine 20 in a turbine frame 30.

[0047] Reference Figure 1 and Figure 2 The gas turbine engine 10 also includes a stub shaft 32 located at the front end 34 of the rotor 14 to which it is connected. A high-pressure locking nut 36 is threadedly connected to the front threads 38 on the front end 40 of the stub shaft 32. The high-pressure locking nut 36 is used to fasten, fix and clamp together and put into compression the horizontal bevel gear 42 and the ball bearing inner race 44 of the front bearing 24 that rotatably supports the stub shaft 32. The horizontal bevel gear 42 drivingly engages a power output bevel gear 46, which is fixedly attached to a power output shaft 48.

[0048] Still refer to Figure 1 and Figure 2 , the gas turbine engine 10 further includes a low pressure turbine (LPT) 50 downstream of the high pressure turbine 20. In addition, as shown, the gas turbine engine 10 is connected to a power output shaft 54 ​​via a low pressure drive shaft 52, and the power output shaft 54 ​​is rotatably supported by an output shaft bearing 56.

[0049] Especially Figure 2 As shown, the low-pressure drive shaft 52 is radially located within the power output shaft 54 ​​and is connected to the power output shaft 54 ​​via a spline joint 58. In addition, as shown, the spline joint 58 includes mating internal splines 60 and external splines 62, which extend radially outward and inward from the low-pressure drive shaft 52 and the power output shaft 54, respectively. The spline joint 58 connects the low-pressure drive shaft 52 to the rear end 64 of the power output shaft 54. The rear power shaft locking nut 66 is threadedly connected to the rear thread 68 on the rear end 64 of the power output shaft 54, and is used to tighten, fix and clamp the power output shaft 54 ​​and the roller bearing inner ring 70 of the output shaft bearing 56 together.

[0050] Still refer to Figure 1 and Figure 2 , the gas turbine engine 10 also includes a shaft and a seal assembly 72, which includes an annular seal assembly 100, as described herein, which provides air and / or oil sealing between the two shafts. The seal assembly 100 can also be used with other types of shafts in other applications and machinery. As shown, the stub shaft 32 radially surrounds the pressure drive shaft 52 and is concentric with the pressure drive shaft 52. In addition, as shown, the stub shaft 32 is axially spaced apart from the power output shaft 54 ​​and is located downstream or rearward of the power output shaft 54. In addition, as shown, the annular gap 74 extends axially between the stub shaft 32 and the power output shaft 54.

[0051] In one embodiment, as shown, the seal assembly 100 provides a seal across the annular gap 74. Figure 3 As shown, the seal assembly 100 may be used to provide a seal across the annular gap 74 between various types of axially spaced front and rear axles 52 , 54 .

[0052] Reference now Figure 3 , shows a partial cross-sectional view of an embodiment of a sealing assembly 100 according to the present disclosure. Specifically, as shown in the figure, in one embodiment, the sealing assembly 100 may include a carbon face sealing ring 76, which is positioned relative to a rotating component (e.g., a rotor 14) to form a sealing interface 82 therebetween, and the sealing interface 82 is configured to form a main seal 84 of the sealing assembly 100. Therefore, the main seal 84 is configured to reduce or prevent the working fluid from entering the high pressure upstream area P HIGH Leakage to low pressure downstream area P LOW. In addition, as shown, the seal assembly 100 includes a non-rotating component 88, which includes a ring carrier 86 fixed to the carbon face seal ring 76. The ring carrier 86 can be an integral part of the carbon face seal ring 76 or can be a separate component connected to the carbon face seal ring 76 for easy maintenance. In addition, the ring carrier 86 is fixed to the carbon face seal ring 76 of the gas turbine engine 10 by mechanical assembly, such as by brazing, welding, mechanical fastener friction fit, threaded connection, or any other retention mechanism.

[0053] In addition, the seal assembly 100 includes an auxiliary seal 80, also referred to herein as a joint, disposed at the interface between the ring carrier 86 and the stator 78 mounted to the engine frame attachment 92. In such an embodiment, the auxiliary seal / joint 80 is capable of linear and tilted displacement to allow the stator 78 to be displaced relative to the rotor 14. In particular, as shown, the auxiliary seal 80 includes a bellows 90 or annular seal that is capable of compression and expansion to allow the ring carrier 86 to translate axially relative to the rotor 14. In this manner, the ring carrier 86 (and therefore the carbon face seal ring 76) can be biased toward the rotor 14 to seal the sealing interface 82.

[0054] When the secondary seal 80 is in place, leakage between the ring carrier 86 and the stator 78 is limited while allowing the ring carrier 86 to move axially away from or toward the rotor 14 to accommodate any rotor translation in the axial direction due to differential thermal expansion of the various components or due to thrust reversal. The diameter of the secondary seal 80, or what is commonly referred to as the pressure balance diameter, is selected to control the closing force of the ring carrier 86.

[0055] In certain embodiments, as the rotor 14 rotates relative to the non-rotating component 88, a circumferential gradient in film thickness (e.g., the gap between the carbon face seal ring 76 and the rotor 14) is created to generate a hydrodynamic pressure at the seal interface 82. Thus, a separation force prevents the carbon face seal ring 76 from contacting the rotor 14 during movement. This occurs when the hydrodynamic opening force is greater than the net closing force generated by the external pressure acting on the ring carrier 86 and the bellows 90.

[0056] Now special reference Figure 3-13 , various views of an embodiment of a sealing assembly 100 having at least one damping element 200 according to the present disclosure are shown. In one embodiment, as Figure 4-5B As shown, the damping element 200 described herein may include a plurality of damping elements 200 arranged circumferentially around the ring carrier 86, such as arranged on top of the carbon face seal ring 76. Thus, in one embodiment, the plurality of damping elements 200 may extend in both the axial direction and the radial direction.

[0057] In one embodiment, as shown, the damping element 200 further includes at least one mass element 202. For example, in one embodiment, the mass element 202 of the damping element 200 described herein can increase the total mass of the non-rotating component 88 by about 5% to about 10%. In other embodiments, the total mass of the non-rotating component 88 can be increased by less than 5% or greater than 10%. More specifically, as Figure 3 , 5A -7 and 10-11, the damping element 200 may be a tuned mass damper having at least one spring element 204 attached to a mass element 202. In particular, Figure 3 A damping element 200 configured as a tuned mass damper for a carbon face seal ring 76 is shown.

[0058] Fig.10 and Fig.11 Each provides a partial cross-sectional view of a seal assembly of a turbomachine, particularly showing various embodiments of a damping element of the seal assembly. In particular, Fig.10 A damping element 200 of a tuned mass damper configured to be mounted on a first configuration of a carrier / slider 205 of a hybrid face seal ring is shown. Fig.11 A damping element 200 configured as a tuned mass damper mounted on a second configuration of a carrier / slide 205 of a hybrid face seal ring is shown. Thus, the damping elements described herein may be applied to various types of seal assemblies.

[0059] For example, in one embodiment, specifically Figure 3 As shown, the spring element 204 and the mass element 202 may be disposed in a recess 206 formed in the radially outer surface of the ring carrier 86. Thus, as shown, in one embodiment, the first end 208 of the spring element 204 may be mounted or otherwise secured to a first surface 210 of the recess 206, and the mass element 202 may be sized larger than an opening 212 of the recess 206, such that movement of the damping element 200 is limited by the recess 206. Furthermore, in one embodiment, the mass element 202 of the damping element 200 may be any suitable mass or weight in addition to or in place of a tuned mass damper.

[0060] In other embodiments, the spring element 204 may be any suitable type of spring formed using a variety of techniques. Figure 4, a cross-sectional view of an embodiment of the damping element 200 is shown, as when viewing the rotor 14 toward the carbon face seal ring 76. Specifically, as shown, the damping element 200 can be formed integrally with the ring carrier 86, rather than the mass element 202 and the spring element 204 being separate components fixed to the ring carrier 86. For example, in one embodiment, the damping element 200 can be formed integrally with the ring carrier 86 using an additive manufacturing process, such as using an electrical discharge machining (EDM) process. Therefore, it should be understood that the spring element 204 described herein can be any suitable type of spring or the like. For example, generally as Figure 3 , 6 As shown in FIG. 7 , the spring element 204 may be a coil spring. Figure 5A and Figure 5B As shown, for example, the spring element 204 may be a leaf spring.

[0061] Reference now Figure 6 and Figure 7 , shows a schematic diagram of another embodiment of the sealing assembly 100 according to the present disclosure. Specifically, as Figure 6 As shown, the spring element 204 described herein may extend radially inward from the surface 216 of the ring carrier 86 and into a recess 218 formed between the carbon face seal ring 76 and the ring carrier 86. In certain embodiments, the recess 218 may contain a fluid. Figure 7 As shown, in one embodiment, the spring elements 204 described herein may extend radially inward from the surface 216 of the ring carrier 86 and between the carbon face seal ring 76 and the ring carrier 86 .

[0062] Reference now Figures 8A-9B , shows a schematic diagram of another embodiment of a sealing assembly 100 having a damping element 200 as described herein according to the present disclosure. Specifically, as Fig. 8A and Fig.9A As shown, the damping element 200 may include a flexible hairpin-shaped carrier 220. Thus, in one embodiment, as Fig. 8A and 8B As shown, the mass element 202 can be a radial foil damper 222 supported by a spring element 204 disposed within a flexible hairpin-shaped bearing 220. In such an embodiment, the radial foil damper 222 can be clamped within the ring bearing 86 as shown. Therefore, high frequency vibrations of the seal assembly 100 cause relative movement between the inner diameter (ID) and the outer diameter (OD) of the radial foil damper 222. This causes sliding between the spring element 204 and the ID / OD, which dissipates the energy generated by friction. In addition, as shown in FIG. Fig.9A and Fig. 9BAs shown, the mass element may be a fluid 224 confined by a plurality of sealing members 226 (eg, piston rings or O-rings) disposed within a flexible hairpin-shaped carrier 220 .

[0063] Reference now Fig. 12A and Fig. 12B , shows a schematic diagram of another embodiment of a sealing assembly 100 according to the present disclosure having a damping element 200 described herein. Specifically, as shown in the figure, the mass element 202 of the damping element 200 described herein may include one or more mass balls 228 movably arranged in one or more channels 230 containing a viscous fluid 232. The balls 228 are allowed to move or slide within the corresponding channels 230, but the movement is mitigated by the viscous fluid 232 to provide the desired damping. Such a damping element 200 can therefore be fixed to the ring carrier 86, for example, fixed between the ring carrier 86 and the carbon face sealing ring 76. In addition, as specifically shown Fig. 12B As shown, the plurality of damping elements 200 may be arranged circumferentially about the ring carrier 86 in any suitable pattern and may be evenly or unevenly spaced about the ring carrier 86 .

[0064] Reference now Fig.13 and Fig.14 , various graphs depicting the advantages of the present disclosure are shown. In particular, Fig.13 A graph 300 of seal response / static excitation (mils / mil) (y-axis) versus stator vibration frequency / seal radial natural frequency (mils / mil) (x-axis) is shown in accordance with the present disclosure, and Fig.14 The embodiment of the present disclosure is shown as c a / (2√(m a k a ) (y-axis) versus mass fraction (x-axis) in a graph 400, where c a is the damping constant of the damping element 200 described herein, m a is the mass of the damping element 200 described herein, k a is the stiffness of the damping element 200 described herein.

[0065] Specifically, Fig.13 As shown, points A, B and C are shown, wherein point B of curve 302 is the highest point of the response curve before the damping element 200 of the present disclosure is applied; point C of curve 304 is a point at the same x-axis value after the damping element 200 of the present disclosure is applied, and point A is the highest point on curve 304. In addition, as Fig.14 As shown, the mass fraction of the mass element 202 described herein may range from about 0.05 to about 0.25, and is represented by c a / (2√(ma k a ) can be in the range of from about 0.1 to about 0.7. Thus, in an embodiment, the damping parameter is defined and selected in a range (e.g., from about 0.1 to about 0.7) that allows for both of the following defined parameters: broadband frequency attenuation benefit (from Fig.13 C / B) and operating frequency amplification ( Fig.13 In other words, as shown, the best combination of these parameters is represented by the shaded area 402, where the best point 404 is the lowest quality score of 50% attenuation.

[0066] The following topics provide further aspects:

[0067] A sealing assembly for a turbine, the sealing assembly comprising: a rotating component; a non-rotating component, the non-rotating component comprising a ring carrier, a face sealing ring and a joint arranged between the ring carrier and the non-rotating component, the non-rotating component and the rotating component being arranged at a sealing interface, the joint being capable of linear and tilting displacement to allow the non-rotating component to be displaced relative to the rotating component, the sealing interface defining a gap between the face sealing ring and the rotating component; and at least one damping element, the at least one damping element being arranged with the ring carrier for keeping the sealing assembly centered in a radial direction in the turbine, the at least one damping element comprising at least one mass element.

[0068] A seal assembly as described in any of the preceding clauses, wherein at least one damping element comprises at least one tuned mass damper comprising at least one spring element attached to at least one mass element.

[0069] Seal assembly according to any of the preceding clauses, wherein at least one spring element and at least one mass element of at least one damping element are arranged in at least one recess formed in the radially outer surface of the ring carrier.

[0070] A seal assembly as in any of the preceding clauses, wherein at least one spring element extends radially inwardly from a surface of the ring carrier and into a recess formed between the face seal ring and the ring carrier.

[0071] A seal assembly as described in any of the preceding clauses, wherein at least one spring element extends radially inwardly from a surface of the ring carrier between the face seal ring and the ring carrier.

[0072] A seal assembly as described in any of the preceding clauses, wherein at least one spring element comprises at least one of a coil spring or a leaf spring.

[0073] A seal assembly as described in any of the preceding clauses, wherein at least one damping element is formed integrally with the ring carrier.

[0074] A seal assembly according to any of the preceding clauses, wherein the at least one damping element comprises a plurality of damping elements, the plurality of damping elements extending in an axial direction and in a radial direction.

[0075] A seal assembly as claimed in any preceding clause, wherein the at least one damping element further comprises a flexible hairpin carrier, the at least one mass element being a radial foil damper supported by a spring element and arranged within the flexible hairpin carrier.

[0076] A seal assembly as claimed in any preceding clause, wherein the at least one damping element further comprises a flexible hairpin carrier, the at least one mass element being a fluid confined by a plurality of sealing members arranged within the flexible hairpin carrier.

[0077] A seal assembly as described in any of the preceding clauses, wherein at least one mass element of at least one damping element further comprises one or more mass balls movably arranged in one or more channels containing the viscous fluid.

[0078] A seal assembly as in any of the preceding clauses, wherein at least one mass element in the at least one damping element increases the total mass of the non-rotating component by about 5% to about 10%.

[0079] A seal assembly according to any of the preceding clauses, wherein a mass fraction of at least one mass element of at least one damping element is in the range of about 0.05 to about 0.25 and is denoted by c a / (2√(m a k a )'s damping parameter ranges from about 0.1 to about 0.7 to provide an optimal combination of broadband amplification and operating frequency amplification of less than 0.5.

[0080] A seal assembly as in any of the preceding clauses, wherein the seal assembly is configured as at least one of a carbon face seal ring, a suction face seal ring, a hybrid face seal ring, a fluid bearing, a gas bearing, or a film riding seal.

[0081] A turbine comprises: a rotor; a stator, the stator and the rotor are arranged at a sealing interface; and a sealing assembly, the sealing assembly at the sealing interface comprises: a ring carrier; a face seal ring; and a joint, the joint is arranged between the ring carrier and a non-rotating component, the joint can be linearly and tilted to allow the stator to be displaced relative to the rotor, the sealing interface defines a gap between the face seal ring and the rotor; and at least one damping element, the at least one damping element is arranged with the ring carrier, and is used to keep the sealing assembly centered in the turbine in a radial direction, the at least one damping element comprises at least one mass element.

[0082] A turbine as claimed in any preceding clause, wherein at least one damping element comprises at least one tuned mass damper comprising at least one spring element attached to at least one mass element.

[0083] A turbine according to any of the preceding clauses, wherein at least one spring element and at least one mass element of at least one damping element are arranged in at least one recess formed in the radially outer surface of the ring carrier.

[0084] A turbine as in any of the preceding clauses, wherein at least one spring element extends radially inwardly from a surface of the ring carrier and into a recess formed between the face seal ring and the ring carrier.

[0085] A turbine as claimed in any preceding clause, wherein at least one spring element extends radially inwardly from a surface of the ring carrier between the face seal ring and the ring carrier.

[0086] A turbine as in any preceding clause, wherein at least one spring element comprises at least one of a coil spring or a leaf spring.

[0087] This written description uses exemplary embodiments to describe the presently disclosed subject matter, including the best mode, and also to enable any person skilled in the art to practice such subject matter, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the presently disclosed subject matter is defined by the claims, and may include other examples that occur to one skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims.

Claims

1. A sealing assembly for a turbine, characterized in that: The sealing assembly comprises: Rotating parts; a non-rotating component, the non-rotating component comprising a ring carrier, a face seal ring, and a joint disposed between the ring carrier and the non-rotating component, the non-rotating component and the rotating component being arranged at a sealing interface, the joint being capable of linear and tilting displacement to allow the non-rotating component to be displaced relative to the rotating component, the sealing interface defining a gap between the face seal ring and the rotating component; and At least one damping element is arranged with the ring carrier for holding the seal assembly centered in the turbomachine in a radial direction, the at least one damping element comprising at least one mass element.

2. The sealing assembly according to claim 1, characterized in that: Wherein the at least one damping element comprises at least one tuned mass damper comprising at least one spring element attached to the at least one mass element.

3. The sealing assembly according to claim 2, characterized in that: The at least one spring element and the at least one mass element of the at least one damping element are arranged in at least one recess formed in the radially outer surface of the ring carrier.

4. The sealing assembly according to claim 2, characterized in that: Wherein the at least one spring element extends radially inwardly from a surface of the ring carrier and into a recess formed between the face seal ring and the ring carrier.

5. The sealing assembly according to claim 2, characterized in that: Wherein the at least one spring element extends radially inwardly from a surface of the ring carrier between the face seal ring and the ring carrier.

6. The sealing assembly according to claim 2, characterized in that: The at least one spring element comprises at least one of a coil spring or a leaf spring.

7. The sealing assembly according to claim 1, characterized in that: Wherein the at least one damping element is formed integrally with the ring carrier.

8. The sealing assembly according to claim 1, characterized in that The at least one damping element comprises a plurality of damping elements, and the plurality of damping elements extend in an axial direction and a radial direction.

9. The sealing assembly according to claim 2, characterized in that: Wherein the at least one damping element further comprises a flexible hairpin-shaped carrier, the at least one mass element is a radial foil damper supported by the spring element and arranged within the flexible hairpin-shaped carrier.

10. The sealing assembly according to claim 2, characterized in that Wherein the at least one damping element further comprises a flexible hairpin-shaped carrier, the at least one mass element is a fluid confined by a plurality of sealing members arranged within the flexible hairpin-shaped carrier.

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