Vibration dampening system including resonant-tuned elongated body for damper element for turbine component

Abstract

To provide a vibration dampening system including a resonant-tuned elongated body for a damper element for a turbine component.SOLUTION: A vibration dampening system (120) includes a damper element (174) in a body opening (160) of a turbine component (111). A resonant-tuned elongated body (190) extends through the damper element in the body opening. The elongated body (190) is configured to resonate at a predefined resonant frequency, such as the same resonant frequency as the turbine component (111) in the body opening, to generate a force against the damper element (174) in the body opening. The damper element (174) has a surface (194) in contact with the body opening (160) and / or the elongated body (190).SELECTED DRAWING: Figure 12

Description

[Technical field]

[0001] The present disclosure relates generally to damping vibrations in turbine components such as nozzles or blades. More specifically, the present disclosure relates to a vibration damping system including a resonantly tuned elongated body for use with one or more damper elements in a body opening of a turbine component. [Background technology]

[0002] One concern in turbine operation is the tendency of turbine components such as blades and nozzles to be subjected to vibratory stresses during operation. In many facilities, turbines are operated under conditions of frequent acceleration and deceleration. During turbine acceleration or deceleration, the blade airfoils are subjected, at least momentarily, to vibratory stresses of certain frequencies, often of secondary or tertiary frequencies. Nozzle airfoils and other turbine components are also subjected to similar vibratory stresses. For example, fluctuations in gas temperature, pressure and / or density can excite vibrations throughout the rotor assembly, particularly within the nozzle or blade airfoils. Periodic or "pulsating" gas exiting from the turbine and / or compressor sections upstream can also excite undesirable vibrations. When airfoils are subjected to vibratory stresses, the amplitude of the vibrations can easily increase to a point where they can adversely affect the operation of the gas turbine and / or the life of the components. Turbine blade damper elements have been used to dampen vibrations, but centrifugal forces can cause the damper elements to lock together and / or not vibrate at the desired frequencies within the turbine component, reducing their vibration damping capabilities. Summary of the Invention

[0003] All aspects, embodiments and features listed below may be combined in any manner technically possible.

[0004] An aspect of the disclosure provides a vibration damping system configured to be installed within a first body opening of a turbine component to damp vibrations within the turbine component, the vibration damping system comprising one or more damper elements within the first body opening and a first resonant-tuned elongated body extending through an opening in the one or more damper elements in the first body opening, the first resonant-tuned elongated body configured to resonate at a first predetermined resonant frequency and generate a force against the one or more damper elements in the first body opening, each of the one or more damper elements in the first body opening having a surface in contact with at least one of the first body opening and the first resonant-tuned elongated body.

[0005] Another aspect of the disclosure includes any of the aspects described above, wherein the first resonant tuned elongated body includes at least one of the following characteristics of the first resonant tuned elongated body selected to generate a first predetermined resonant frequency during operation of the turbine component: length, one or more outer dimensions, outer dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine component, one or more attachment types to the turbine component, and number of elongated bodies.

[0006] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening include a plurality of damper elements stacked together along at least a portion of the first resonantly tuned elongated body.

[0007] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening are selected from the group including damper pins, damper elements with flexible legs, spring-suspended damper elements, nested damper pins, plate members with openings, helical metal ribbon springs, and wire mesh.

[0008] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening include a first plurality of stack washers and a second plurality of stack washers having a second outer dimension, the first outer dimension and the second outer dimension being different.

[0009] Another aspect of the present disclosure includes any of the aspects described above, wherein the first outer dimension matches an inner dimension of the first body opening and the second outer dimension is smaller than the inner dimension of the first body opening.

[0010] Other aspects of the present disclosure include any of the aspects described above, wherein the first plurality of stack washers has a first inner dimension and the second plurality of stack washers has a second inner dimension, the first inner dimension being greater than an outer dimension of the first resonant tuned elongated body, and the second inner dimension matching the outer dimension of the first resonant tuned elongated body.

[0011] Another aspect of the disclosure includes any of the aspects described above, wherein the turbine component includes a second body opening, and the vibration damping system further includes one or more damper elements in the second body opening and a second resonant-tuned elongated body extending through openings in the one or more damper elements in the second body opening, the second resonant-tuned elongated body configured to resonate at a second predetermined resonant frequency and generate a force against the one or more damper elements in the second body opening, each of the one or more damper elements in the second body opening having a surface in contact with at least one of the second body opening and the second resonant-tuned elongated body.

[0012] Another aspect of the present disclosure includes any of the aspects described above, wherein the first predetermined resonant frequency corresponds to a resonant frequency of the turbine component within the first body opening.

[0013] Another aspect includes a turbine component including a body having a first body opening defined therein and a vibration damping system configured to damp vibrations in the body and to be located in the first body opening, the vibration damping system including one or more damper elements in the first body opening and a first resonant-tuned elongated body extending through openings in the one or more damper elements in the first body opening, the first resonant-tuned elongated body configured to resonate at a first predetermined resonant frequency and generate a force against the one or more damper elements in the first body opening, each of the one or more damper elements in the first body opening having a surface in contact with at least one of the first body opening and the first resonant-tuned elongated body.

[0014] Another aspect of the disclosure includes any of the aspects described above, wherein the first resonant tuned elongated body includes at least one of the following characteristics of the first resonant tuned elongated body selected to generate a first predetermined resonant frequency during operation of the turbine component: length, one or more outer dimensions, outer dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine blade, one or more attachment types to the turbine blade, and number of elongated bodies.

[0015] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening include a plurality of damper elements stacked together along at least a portion of the first resonantly tuned elongated body.

[0016] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening are selected from the group including damper pins, damper elements with flexible legs, spring-suspended damper elements, nested damper pins, plate members with openings, helical metal ribbon springs, and wire mesh.

[0017] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements in the first body opening include a first plurality of stack washers and a second plurality of stack washers having a second outer dimension, the first outer dimension and the second outer dimension being different.

[0018] Another aspect of the present disclosure includes any of the aspects described above, wherein the first outer dimension matches an inner dimension of the first body opening and the second outer dimension is smaller than the inner dimension of the first body opening.

[0019] Other aspects of the present disclosure include any of the aspects described above, wherein the first plurality of stack washers has a first inner dimension and the second plurality of stack washers has a second inner dimension, the first inner dimension being greater than an outer dimension of the first resonant tuned elongated body, and the second inner dimension matching the outer dimension of the first resonant tuned elongated body.

[0020] Another aspect of the disclosure includes any of the aspects described above, wherein the turbine component includes a second body opening, and the vibration damping system further includes one or more damper elements in the second body opening and a second resonant-tuned elongated body extending through openings in the one or more damper elements in the second body opening, the second resonant-tuned elongated body configured to resonate at a second predetermined resonant frequency and generate a force against the one or more damper elements in the second body opening, each of the one or more damper elements in the second body opening having a surface in contact with at least one of the second body opening and the first resonant-tuned elongated body.

[0021] Another aspect of the present disclosure includes any of the aspects described above, wherein the first predetermined resonant frequency corresponds to a resonant frequency of the turbine component within the first body opening.

[0022] Another aspect includes a method including the steps of selecting a frequency of concern at a body opening defined within an operating turbine component, configuring a resonant tuned elongated body to be placed within the body opening to have the same resonant frequency as the frequency of concern of the turbine component at the body opening, placing the resonant tuned elongated body through an opening of one or more damper elements, and placing the resonant tuned elongated body with the one or more damper elements in the body opening, the one or more damper elements in the body opening having a surface in contact with at least one of the body opening and the resonant tuned elongated body.

[0023] Another aspect of the disclosure includes any of the aspects described above, wherein the step of configuring the resonant tuned elongated body includes selecting at least one of the following characteristics of the resonant tuned elongated body: length, one or more outer dimensions and outer dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine blade, one or more attachment types to the turbine blade, and number of elongated bodies, such that a resonant frequency of the resonant tuned elongated body matches a resonant frequency of the turbine component within the body opening.

[0024] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements are selected from the group including damper pins, damper elements with flexible legs, spring-suspended damper elements, nested damper pins, plate members with openings, helical metal ribbon springs, and wire mesh.

[0025] Another aspect of the present disclosure includes any of the aspects described above, wherein the one or more damper elements include a first plurality of stack washers and a second plurality of stack washers having a second outer dimension, the first outer dimension and the second outer dimension being different.

[0026] Another aspect of the present disclosure includes any of the aspects described above, wherein the first outer dimension matches an inner dimension of the first body opening and the second outer dimension is smaller than the inner dimension of the first body opening.

[0027] Other aspects of the present disclosure include any of the aspects described above, wherein the first plurality of stack washers has a first inner dimension and the second plurality of stack washers has a second inner dimension, the first inner dimension being greater than an outer dimension of the first resonant tuned elongated body, and the second inner dimension matching the outer dimension of the first resonant tuned elongated body.

[0028] Two or more aspects described in this disclosure, including those described in the Summary of the Invention, may be combined to form an embodiment not specifically described herein. Two or more aspects described in this disclosure, including those described in the Summary of the Invention, may be combined to form an embodiment not specifically described herein. That is, all embodiments described herein may be combined with each other.

[0029] The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will become apparent from the description, drawings, and claims. [Brief description of the drawings]

[0030] These and other features of the present disclosure may be better understood by reference to the following detailed description taken in conjunction with the accompanying drawings, which set forth various embodiments of the present disclosure. [Figure 1] 1 is a cross-sectional view of an exemplary turbomachine in the form of a gas turbine system; [Diagram 2] 1 is a cross-sectional view of a portion of an exemplary turbine according to an embodiment of the present disclosure. [Diagram 3] 1 is a perspective view of an exemplary turbine component in the form of a turbine nozzle including a vibration damping system according to an embodiment of the present disclosure; [Figure 4] 1 is a perspective view of an exemplary turbine component in the form of a turbine blade including a vibration damping system according to an embodiment of the present disclosure; [Diagram 5] 1 is a schematic cross-sectional view of a turbine component, such as a turbine nozzle or blade, having a vibration damping system according to an embodiment of the present disclosure. [Figure 6]1 is a schematic cross-sectional view of a turbine component, such as a turbine nozzle or blade, having a vibration damping system according to an embodiment of the present disclosure. [Figure 7] FIG. 7 is an enlarged cross-sectional view of the damper element of FIGS. 5-6 according to an embodiment of the present disclosure. [Figure 8] 1A-1D are side views of resonant tuned elongated (RTE) bodies having different overall dimensions for a vibration damping system according to an embodiment of the present disclosure. [Figure 9] FIG. 13 is a side view of an RTE body having tapered exterior dimensions according to an embodiment of the present disclosure. [Figure 10] FIG. 13 is a side view of an RTE body having different wall thicknesses according to an embodiment of the present disclosure. [Figure 11] FIG. 1 is a side view of an RTE body having attachment points between its ends according to an embodiment of the present disclosure. [Figure 12] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including a plurality of damper elements including plate members stacked around a periphery of an RTE body according to another embodiment of the present disclosure. [Figure 13] FIG. 13 is a schematic cross-sectional view similar to FIG. 12 but including a retainer on an RTE body according to another embodiment of the present disclosure. [Figure 14] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including a plurality of damper elements including plate members stacked around a periphery of an RTE body according to an additional embodiment of the present disclosure. [Figure 15] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including damper elements (plate members) grouped and stacked around an RTE body according to an additional embodiment of the present disclosure. [Figure 16] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including a vibration damping element including a helical metal ribbon spring and an RTE body according to another embodiment of the present disclosure. [Figure 17] FIG. 1 is a schematic cross-sectional view of a turbine blade having a vibration damping system including multiple spring-suspended damper elements around a periphery of an RTE body according to an embodiment of the present disclosure. [Figure 18]FIG. 1 is a schematic cross-sectional view of a turbine blade having a vibration damping system including multiple spring-suspended damper elements around a periphery of an RTE body according to an embodiment of the present disclosure. [Figure 19] FIG. 13 is a cross-sectional view of a vibration damping system including a plurality of spring-suspended damper elements in operative positions about an RTE body according to another embodiment of the present disclosure. [Figure 20] FIG. 13 is a cross-sectional view of a vibration damping system including multiple spring-suspended damper elements around an RTE body according to another embodiment of the present disclosure. [Figure 21] FIG. 13 is a side, partial cross-sectional view of a vibration damping system including a plurality of stack damper elements having flexible legs at a first location about an RTE body according to another embodiment of the present disclosure. [Figure 22] FIG. 13 is a side, partial cross-sectional view of a vibration damping system including a plurality of stack damper elements having expandable legs at a second location about an RTE body according to another embodiment of the present disclosure. [Figure 23] FIG. 2 is a cross-sectional close-up view of a vibration damping system including a pair of damper elements, each including an outer body and an inner body, around an RTE body according to an embodiment of the present disclosure. [Figure 24] FIG. 13 is a cross-sectional view of a vibration damping system including multiple damper elements, each including an outer body and an inner body, around an RTE body according to another embodiment of the present disclosure. [Diagram 25] FIG. 2 is a schematic cross-sectional view of a turbine component having a vibration damping system including a wire mesh member around a perimeter of an RTE body according to an embodiment of the present disclosure. [Figure 26] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including a wire mesh member around a perimeter of an RTE body according to another embodiment of the present disclosure. [Figure 27] FIG. 13 is a schematic cross-sectional view of a turbine component having a vibration damping system including a wire mesh member penetrating a plurality of RTE bodies according to an additional embodiment of the present disclosure. [Figure 28] FIG. 28 is a cross-sectional view of the vibration damping system of FIG. 27 using multiple RTE bodies according to an embodiment of the present disclosure. [Figure 29] 28 is a cross-sectional view of the vibration damping system of FIG. 27 using multiple RTE bodies according to another embodiment of the present disclosure. [Diagram 30] FIG. 2 is a perspective view of a wire mesh member according to an embodiment of the present disclosure. [Diagram 31] FIG. 1 is a perspective view of an RTE body for a vibration damping system including a wire mesh member retention system according to an embodiment of the present disclosure. [Diagram 32] FIG. 13 is a schematic cross-sectional view of an RTE body for a vibration damping system including a wire mesh member retention system according to another embodiment of the present disclosure.

[0031] It should be noted that the drawings in the present disclosure are not necessarily drawn to scale. The drawings are merely illustrative of exemplary aspects of the present disclosure and are not intended to limit the scope of the present disclosure. In the drawings, like reference numerals represent like elements between multiple drawings. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0032] First, in order to clearly explain the technical content of this disclosure, it is necessary to select terms when referring to and describing the relevant machine components in an exemplary turbomachinery application. Wherever possible, terms common in the art will be used consistent with their ordinary meaning. Unless otherwise indicated, such terms should be interpreted broadly within the context of this application and the appended claims. It will be apparent to those skilled in the art that a component will often be referred to using several different or overlapping terms. What is described as a single component in this specification may be described as consisting of multiple components in another context. Alternatively, what is described as including multiple components in one place in this specification may be described as a single component in another place.

[0033] Additionally, certain descriptive terms are used repeatedly in this specification and it may be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise specified: As used herein, "downstream" and "upstream" are terms that indicate a direction relative to the flow of a fluid, such as the flow of a working fluid through a turbomachine or, for example, air through a combustor or coolant through one of the component systems of a turbomachine. The term "downstream" corresponds to the direction in which the fluid flows, and the term "upstream" refers to the direction opposite to the flow (i.e., the direction from which it flows). The terms "forward" and "aft" refer to directions not further specified, with "forward" referring to the forward or compressor end of the turbomachine and "aft" referring to the aft or turbine end of the turbomachine.

[0034] It is often necessary to describe components that are located at different radial positions relative to a central axis. The term "axial" refers to movement or position parallel to an axis (e.g., the axis of a turbomachine). The term "radial" refers to movement or position perpendicular to an axis (e.g., the axis of a turbomachine). In such cases, if a first component is closer to the axis than a second component, the first component is described herein as being "radially inward" or "proximal to the central axis" of the second component. Conversely, if a first component is located farther from the axis than the second component, the first component is described herein as being "radially outward" or "distal to the central axis" of the second component. Finally, the term "circumferential" refers to movement or position about an axis (e.g., the circumferential inner surface of a casing that extends around the axis of a turbomachine). As discussed above, it will be understood that such terms may be applied in relation to the axis of a turbomachine.

[0035] Furthermore, certain descriptive terms are used repeatedly in this specification, as described below: The terms "first," "second," and "third" are used interchangeably to distinguish one component from another, and do not denote the location or importance of the individual components.

[0036] The terms used herein are merely for the purpose of describing particular embodiments and are not intended to limit the disclosure. In this specification, the singular means the plural, unless otherwise clear from the context. Furthermore, in this specification, the terms "comprises," "includes," and / or "has" refer to the presence of stated features, integers, steps, operations, components, and / or parts, and do not exclude the presence or addition of one or more other features, integers, steps, operations, components, parts, and / or groups thereof. The terms "optionally" or "optionally" refer to the event or circumstance described following the term that may or may not occur, and such a description encompasses the occurrence and non-occurrence of the event.

[0037] When a component or layer is said to be "on," "engaged with," "connected to," or "coupled to" another component or layer, it may be directly on, engaged with, connected to, or coupled to the other component or layer, or there may be intervening components or layers. In contrast, when a component is said to be "directly on," "directly engaged with," "directly connected to," or "directly coupled to" another component or layer, there are no intervening components or layers. Other terms used to describe relationships between components (e.g., "between" and "directly between," "adjacent" and "directly adjacent," etc.) are to be interpreted similarly. As used herein, the term "and / or" includes any and all combinations of one or more of the listed items. The terms "coupled" and "attached" may be used interchangeably herein.

[0038] An embodiment of the present disclosure includes a vibration damping system including one or more damper elements in a body opening of a turbine component. A resonance tuned elongate body extends through the damper element in the body opening. The resonance tuned elongate body is configured to resonate at a predetermined resonant frequency and generate a force against the damper element in the body opening. The damper element has a surface that contacts the body opening and / or the resonance tuned elongate body. The resonance tuned elongate body can be configured to resonate at a predetermined resonant frequency, e.g., a located resonant frequency, by varying a wide variety of material and / or geometric properties thereof. The vibration damping system provides customized vibration damping at one or more locations of the body interior opening of the turbine component to improve vibration damping of the turbine component. The vibration damping system reduces vibrations of turbine components, such as nozzles and blades, with simple placement and does not add significant extra mass to the turbine component. Thus, the vibration damping system and damper element do not increase centrifugal forces on the turbine component or require changes to the component configuration.

[0039] Referring to the drawings, Figure 1 is a cross-sectional view of an exemplary machine including one or more turbines to which the teachings of the present disclosure may be applied. Figure 1 illustrates a turbomachine 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter "GT system 100"). The GT system 100 includes a compressor 102 and a combustor 104. The combustor 104 has a combustion region 105 and a fuel nozzle section 106. The GT system 100 includes a turbine 108 and a common compressor / turbine shaft 110 (hereinafter "rotor 110").

[0040] The GT system 100 may be, for example, a 7HA.03 engine available from General Electric (Greenville, South Carolina, USA). The present disclosure is not limited to any GT system and may be practiced with other engines, including, for example, other General Electric HA, F, B, LM, GT, TM, and E class engine models, as well as engine models from other manufacturers. More importantly, the teachings of the present disclosure are not necessarily applicable only to the turbine of a GT system, but may also be applied to virtually any type of industrial machine or other turbine, such as steam turbines, jet engines, compressors (as in FIG. 1), turbofans, turbochargers, etc. Thus, references to the turbine 108 of the GT system 100 are for illustrative purposes only and not limiting.

[0041] FIG. 2 illustrates a cross-sectional view of an exemplary portion of a turbine 108. In the illustrated example, the turbine 108 includes four stages L0-L3 that may be used in the GT system 100 of FIG. 1. The four stages are labeled L0, L1, L2, and L3. Stage L0 is the first stage and is the smallest (radially) of the four stages. Stage L1 is the second stage and is disposed axially adjacent to the first stage L0. Stage L2 is the third stage and is disposed axially adjacent to the second stage L1. Stage L3 is the fourth and final stage and is the largest (radially). It is noted that four stages are merely an example and each turbine may have more than four stages or less than four stages.

[0042] For illustrative purposes, a turbine component 111 to which the teachings of the present disclosure may be applied may be provided as a turbine static nozzle 112 or a rotating blade 114. The teachings of the present disclosure may also be applied to various other turbine components. A plurality of stationary turbine vanes or nozzles 112 (hereinafter "nozzles 112") cooperate with a plurality of rotating turbine blades 114 (hereinafter "blades 114") to form each stage L0-L3 of the turbine 108 and define a portion of the working fluid path through the turbine 108. The blades 114 of each stage are coupled to the rotor 110 (FIG. 1) (e.g., by respective rotor wheels 116 that circumferentially couple the blades to the rotor 110 (FIG. 1)). In other words, the plurality of blades 114 are circumferentially spaced apart and mechanically coupled to the rotor 110 (e.g., by the rotor wheels 116). The static nozzle section 115 includes a plurality of nozzles 112 mounted to a casing 118 and spaced apart circumferentially around the rotor 110 (FIG. 1). It should be noted that the blades 114 rotate with the rotor 110 (FIG. 1) and are subjected to centrifugal force, whereas the nozzles 112 are stationary components.

[0043] 1 and 2, during operation, air flows through the compressor 102 and the compressed air is provided to the combustor 104. Specifically, the compressed air is provided to a fuel nozzle section 106 contained within the combustor 104. The fuel nozzle section 106 is in fluid communication with a combustion zone 105. The fuel nozzle section 106 is also in fluid communication with a fuel source (not shown in FIG. 1 ) and directs fuel and air to the combustion zone 105. The combustor 104 ignites and combusts the fuel to generate combustion gases. The combustor 104 is in fluid communication with a turbine 108, where thermal energy from the combustion gas stream is converted to mechanical rotational energy by directing the combusted fuel (e.g., working fluid) through a working fluid path to rotate blades 114. The turbine 108 is rotatably coupled to and drives a rotor 110. The compressor 102 may be rotatably coupled to the rotor 110. At least one end of the rotor 110 may extend axially from the compressor 102 or the turbine 108 and may be attached to a load or machine (not shown), such as a generator, a load compressor, and / or another turbine.

[0044] Figures 3 and 4 show perspective views of a (stationary) nozzle 112 and a (rotating) blade 114, respectively, of a type that may employ embodiments of a vibration-damping system 120 of the present disclosure. As will be described below, Figures 5 and 6 show schematic cross-sectional views of a nozzle 112 or a blade 114 including a vibration-damping system 120 according to various embodiments of the present disclosure.

[0045] 3 and 4, each turbine component (e.g., nozzle 112 or blade 114) includes a body 128. With respect to the nozzle or blade, the body 128 has a base end 130, a tip end 132, and an airfoil portion 134 extending between the base end 130 and the tip end 132. As shown in FIG. 3, the nozzle 112 has an outer endwall 136 at the base end 130 and an inner endwall 138 at the tip end 132. The outer endwall 136 couples to the casing 124 (FIG. 2). As shown in FIG. 4, the blade 114 includes a dovetail 140 at the base end 130, which attaches the blade 114 to a rotor wheel 116 (FIG. 2) of the rotor 110 (FIG. 2). The base end 130 of the blade 114 may further include a shank 142 extending between the dovetail 140 and a platform 146. The platform 146 is disposed at the juncture of the airfoil 134 and the shank 142 and defines a portion of the proximal boundary of the centerline of the working fluid path (FIG. 2) through the turbine 108 .

[0046] As will be apparent, the airfoils 134 in the nozzles 112 and blades 114 are the active components of the nozzles 112 or blades 114 that receive the flow of working fluid and, in the case of the blades 114, rotate the rotor 110 (FIG. 1). The airfoils 134 in the nozzles 112 and blades 114 include a concave pressure side (PS) outer wall 150 and a circumferentially or laterally opposed convex suction side (SS) outer wall 152 extending between axially opposed leading and trailing edges 154 and 156. The sidewalls 150 and 152 also extend radially from the base end 130 (i.e., the outer endwall 136 for the nozzle 112 and the platform 146 for the blades 114) to the tip end 132 (i.e., the inner endwall 138 for the nozzle 112 and the tip 158 for the blades 114). In the illustrated example, blade 114 does not include a tip shroud, however, the teachings of this disclosure are equally applicable to blades that include a tip shroud at tip 158. The nozzle 112 and blade 114 shown in Figures 3-4 are exemplary only, and the teachings of this disclosure are applicable to a wide variety of nozzles and blades.

[0047] During turbine operation, the nozzles 112 or blades 114 may be excited into vibration by a number of different forcing functions. For example, variations in temperature, pressure, and / or density of the working fluid may excite vibrations throughout the rotor assembly, and particularly within the airfoils and / or at the tips of the blades 114 or nozzles 112. Periodic (or "pulsating") exhaust gases upstream of the turbine and / or compressor sections may also excite undesirable vibrations. The present disclosure aims to reduce vibrations in the stationary nozzles 112 or rotating turbine blades 114 without significant modifications to the nozzle or blade design.

[0048] 5 and 6 each show a schematic cross-sectional view of a turbine component 111 (e.g., a turbine nozzle 112 or a blade 114) including a vibration damping system 120 according to an embodiment of the present disclosure. (Note that the nozzle 112 in the schematic cross-sectional views of FIGS. 5-6 is shown upside down from that shown in FIG. 3 for ease of explanation, and the inner end wall 138 is omitted. Note that the base end 130 and the tip end 132 of the nozzle 112 are opposite to those of the blade 114.) The vibration damping system 120 is for damping vibrations in the body 128 of the turbine component 111 and is configured to be installed in a body opening or an internal opening 160 in the body 128. Any number of vibration damping systems 120 can be used in the turbine component 111, i.e., having multiple body openings 160. The vibration damping system 120 of the turbine component 111 may also include a body opening or internal opening 160 that extends through, for example, the nozzle 112 or blade 114, the body 128 of the turbine component 111. In the illustrated example, the body opening 160 extends between the tip 132 and the base 130 and at least partially through the airfoil 134. The body opening 160 may extend only a portion of the distance between the base 130 and the tip 132, or may extend through one or more of the base 130 or the tip 132. The body opening 160 may be defined in any portion of any structure of the body 128. For example, if the body 128 includes an internal bulkhead (not shown), the body opening 160 may be defined as an internal cavity in the bulkhead in the body 128, for example, to define a cooling circuit therein. The body opening 160 generally extends radially within the body 128, although this may not be necessary in all cases. For example, some angle, and perhaps curvature, of the body opening 160 relative to the radial extent of the fuselage 128 is possible, and / or the body opening 160 may not extend radially in all turbine components 111. The body opening 160 has an inner surface 162.

[0049] The body opening 160 may originate at the proximal end 130 of the nozzle 112 or blade 114, as shown in FIG. 5, or may originate at the distal end 132 of the nozzle 112 or blade 114, as shown in FIG. 6. More specifically, the body opening 160 may open at the proximal end 130 and terminate at the distal end 132, as shown in FIG. 5, or may open at the distal end 132 and terminate at the proximal end 130, as shown in FIG. 6. The open end aids in the assembly of the vibration damping system 120 at the nozzle 112 or blade 114 and allows for retrofitting of the system to an existing nozzle or blade. The body opening 160 extends through the proximal end 130, as shown in FIG. 5, and may include a closure member 164 for closing the body opening 160. If the body opening 160 extends through the distal end 132, a closure member 166 for the body opening 160 may be provided, as shown in FIG. 6. In addition to closing the body opening 160, the closure members 164, 166 prevent removal of the vibration damping system 120 from the body opening 160. The closure members 164, 166 may also optionally be used to attach a resonance tuned elongate body 190 according to embodiments of the present disclosure.

[0050] 5 and 6 will be used periodically in the drawings to illustrate how certain vibration damping systems 120 may be used in different radially oriented nozzles 112 or blades 114. As will be further explained, some forms of vibration damping systems 120 are only applicable to turbine blades 114 or other turbine components 111 that experience centrifugal forces, i.e., radially outward centrifugal forces.

[0051] The vibration damping system 120 of the turbine component 111 may include one or more damper elements 174 in, for example, the nozzle 112 or blade 114, the body opening 160. The one or more damper elements 174 may be stacked together. As described further herein, the one or more damper elements 174 may take a wide variety of forms. For purposes of explanation in connection with FIGS. 5 and 6, and as shown in FIG. 7, the one or more damper elements 174 in the body opening 160 may include a first plurality of stack washers 176 and a second plurality of stack washers 178. Each "washer" includes a plate member having an opening 192 therein. The washers 176, 178 may have a circular outer edge, although this is not necessary in all cases.

[0052] The vibration damping system 120 of the turbine component 111 also includes a resonant tuned elongated body 190 that extends through an opening 192 in the damper element 174, e.g., the nozzle 112 or blade 114, and into the body opening 160. The resonant tuned elongated body 190 (hereinafter "RTE body 190") is configured to resonate at a predetermined resonant frequency. As used herein, a "predetermined resonant frequency" may be any frequency configured to address a frequency of concern in the turbine component 111. The predetermined resonant frequency may be, for example, a resonant frequency of the turbine component 111 at the body opening 160 during operation of the turbine component 111, or a resonant frequency known to affect the turbine component 111 at the body opening 160 during operation. Examples of the latter may include, but are not limited to, frequencies just above or below the resonant frequency of the turbine component 111 in the body opening 160 during operation. The RTE body 190 generates a force F against the damper element 174 in the body opening 160. Body opening 160 (ie, interior surface 162) has an inner dimension ID1 and RTE body 190 has an outer dimension OD1.

[0053] 7, each of the damper elements 174 in the body opening 160 has a surface 194 that contacts at least one of the body opening 160 and the RTE body 190. More specifically, the first plurality of stack washers 176 has a first outer dimension OD2 and the second plurality of stack washers 178 has a second outer dimension OD3. The first outer dimension OD2 and the second outer dimension OD3 are different. Additionally, the first plurality of stack washers 176 has an inner dimension ID2 and the second plurality of stack washers 178 has an inner dimension ID3. The inner dimension ID2 of the first plurality of stack washers 176 and the inner dimension ID3 of the second plurality of stack washers 178 are different. In one embodiment, a first outer dimension OD2 of the first plurality of stack washers 176 matches the inner dimension ID1 of the body opening 160, i.e., the inner dimension ID1 of its inner surface 162, and a second outer dimension OD3 of the second plurality of stack washers 178 is smaller than the inner dimension ID1 of the body opening 160. Thus, a surface 194 of the first plurality of stack washers 176 contacts the body opening 160. The inner dimension ID2 of the first plurality of stack washers 176 is larger than the outer dimension OD1 of the RTE body 190, and the inner dimension ID3 of the second plurality of stack washers 178 matches the outer dimension OD1 of the RTE body 190. In this manner, an inner surface 196 of the second plurality of stack washers 178 contacts the RTE body 190. Thus, each damper element 174 in body opening 160 has a surface 194 or 196 that contacts at least one of body opening 160 and RTE body 190, respectively. As used herein, "matching" means that the dimensions recited are close to the same size or slightly smaller or larger to allow for installation of the respective parts, e.g., washer 176 in body opening 160, or RTE body 190 through inner surface 196 of washer 178. As will be appreciated by those skilled in the art, the amount of "slightly smaller or larger" can vary depending on the tolerances required for installation.

[0054] The RTE body 190 can be configured to match a predetermined resonant frequency in several ways. More specifically, the RTE body 190 includes at least one of the following properties: material (e.g., mass, flexibility, hardness, etc.) and length L (FIGS. 5-6) selected to generate a predetermined resonant frequency in the RTE body 190 during operation of the turbine component 111. In addition, one or more outer dimensions of the RTE body 190 can be adjusted. In FIGS. 5-7, the RTE body 190 has a single outer dimension OD1. However, as shown in FIG. 8, the RTE body 190 may have sections 200 with different outer dimensions OD4, OD5. While two sections 200 are shown, the RTE body 190 may have any number of sections 200 with different outer dimensions. As described further herein, sections 200 of different outer dimensions may also be used to hold the damper element 174 against the RTE body 190. 9, the outer dimension taper along the length L of the RTE body 190 may be selected to match a predetermined resonant frequency of the RTE body 190 and the resonant frequency of the turbine component 111 within the body opening 160. In this case, the outer dimension OD6 of the RTE body 190 at one location is greater than the outer dimension OD7 of the RTE body 190 at another location, and the body tapers from one location to another, i.e., is conical. The outer dimensions and / or angle of taper can be adjusted to obtain the desired resonant frequency.

[0055] 10A, the RTE body 190 may also include one or more hollow sections (two shown 210, 212 each having a wall thickness (T1, T2)) at one or more locations configured to tune the resonant frequency of the RTE body 190. That is, the RTE body 190 may include one or more hollow sections 210, 212 having different wall thicknesses T1, T2. In another embodiment shown in FIG. 10B, the RTE body 190 may simply be tubular with a uniform wall thickness T3.

[0056] In addition to the geometric characteristics of the RTE body 190, one or more types of attachment to the turbine component 111 can be tailored, as shown in FIG. 5 and FIG. 6. In FIG. 5 and FIG. 6, the RTE body 190 is fixedly connected to the proximal end 130 in FIG. 5 or the distal end 132 in FIG. 6, while the opposing ends of the RTE body 190 are free to vibrate. The RTE body 190 can also be fixed to both ends. The type of attachment can include threaded fasteners, welds, clamps or other types of attachments and can be selected to control a predetermined resonant frequency. The length of the RTE body 190 used for attachment can also be varied to control the resonant frequency. In FIG. 5 and FIG. 6, the RTE body 190 has one attachment location to the turbine component 111. However, as shown in FIG. 11, the RTE body 190 can have multiple (additional) attachment locations 220 with the turbine component 111 to control its resonant frequency. In the illustrated example, the RTE body 190 includes attachment locations 220, i.e., pinned locations, between its ends to define a predetermined resonant frequency. The form of attachment at locations 220 can be any form that affects the vibration frequency of the RTE body 190, i.e., simple contact, fixed attachment (e.g., fasteners, welding, etc.), among other options.

[0057] The one or more damper elements 174 can take a wide variety of forms other than those shown in Figures 5-11. Figures 12-32 illustrate alternative forms of the one or more damper elements 174. In some embodiments, the one or more damper elements 174 in the body opening 160 include a plurality of damper elements 174 stacked together along at least a portion of the RTE body 190. For example, Figures 5-7 illustrate an embodiment using a plurality of stack damper elements 174 using stack washers of different sizes, i.e., the damper element 174 in the body opening 160 may include a first plurality of stack washers 176 and a second plurality of stack washers 178. As further described herein, the one or more damper elements 174 in the body opening 160 may be selected from a group including: a damper pin, a damper element with flexible legs (see FIGS. 21-22), a spring-suspended damper element (see FIGS. 17-20), nested damper pins (see FIGS. 23-24), a plate member with an opening (e.g., a flat or curved washer, see FIGS. 5-7, 12-15), a helical metal ribbon spring (see FIG. 16), and a wire mesh (see FIGS. 25-32).

[0058] FIG. 12 shows a schematic cross-sectional view of an RTE body 190 having a stack damper element 174 in the form of a stack plate member 230 having an opening 232 therein, i.e., a turbine component 111 including a washer-based vibration damping system 120. (The plate members 230 of FIGS. 12-15 are similar to those of FIGS. 5-7, except that the plate members 230 are concave / convex and have the same outer dimension OD7 that matches the inner dimension ID1 of the body opening 160.) The stack plate members 230 may be held in place or restricted from moving. For example, retaining members 234 (FIG. 13), 236 (FIG. 14), 242 (FIG. 15) on the RTE body 190 may be used to restrain the plate members 230. Thus, according to an embodiment of the present disclosure, the retaining members 234, 236, 242 on the RTE body 190 may be used to retain the plate members 230 relative to the length of the RTE body 190 and / or to control the predetermined resonant frequency of the RTE body 190 in operation within the body opening 160 of the turbine component 111. A compression member 238, e.g., a spring or other flexible member or weight, may be used to apply pressure to the plate members 230. FIG. 15 illustrates a cross-sectional view of another embodiment in which a plurality of stack plate members 230 are separated into at least two groups 240. Note that while three groups 240A-C are shown in FIG. 15, any number of groups may be used. The retaining members 242 on the RTE body 190 engage the endmost plate members 230X of each group 240A-C to prevent each group from moving relative to the length of the RTE body 190. End 244 of body opening 160 may retain group 240A closest to tip 132, or a separate retainer (similar to 242, not shown) can be used. Any number of groups 240 with each group containing any number of plate members 230 can be used to provide the desired vibration damping.

[0059] 16 illustrates a schematic cross-sectional view of a turbine component 111 including a vibration damping system 120 that uses an RTE body 190 having a damper element 174 in the form of a helical metal ribbon spring 246 having an opening 248 therein. The helical metal ribbon spring 246 may have a uniform outer dimension OD8 that matches the inner dimension ID1 of the body opening 160.

[0060] 17-20 show schematic cross-sectional views of a turbine component 111, such as a turbine blade 114, including a vibration damping system 120 using an RTE body 190 having a stack damper element 174 including a spring-suspended bearing member 249. FIG 19 shows an enlarged cross-sectional view of the spring-suspended bear member 249. FIG 20 shows an enlarged cross-sectional view of a spring-suspended bear member 249 according to an alternative embodiment.

[0061] 17 and 18 illustrate that the damper element 174 may include an RTE body 190 having an axially fixed position within the body opening 160. In FIGS. 17 and 18, the spring-suspended bearing member 249 includes a disc spring 250 fixedly coupled to the RTE body 190 at a center 252 of the disc spring 250 and a bearing member 254 coupled to an outer portion thereof, i.e., a first side 256 of the disc spring 250 relative to the center 252. The bearing member 254 may include any element capable of frictionally engaging a first bearing surface 258 to damp vibrations. As will be described, the location of the first bearing surface 258 may vary depending on the particular damper element 174. In FIGS. 17-20, the disc spring 250 includes any form of disc spring, also known as, for example, a Belleville washer, Belleville spring, cupped spring washer, conical disk spring, conical spring washer, etc. While shown in a planar initial configuration, the disc spring 250 can have any frusto-conical arrangement, among other shapes. The disc spring 250 can have any configuration capable of providing the desired spring action or spring constant.

[0062] The disc spring 250 has a center portion 252 coupled to the RTE body 190 and an outer portion 260 having a first side 256 coupled to a bearing member 254. The disc spring 250 also includes a second side 262 opposite the first side 256. The center 252 of the disc spring 250 may be fixedly coupled to the RTE body 190 in any manner now known or later developed. For example, if the center 252 includes an opening, the center 252 of the disc spring 252 may be welded or brazed to the RTE body 190. Alternatively, the disc spring 250 and the RTE body 190 may be stack molded as a unitary piece with the bearing member 254. The bearing member 254 is coupled to the first side 256 of the disc spring 250 and extends radially distal from the first side 256 of the disc spring 250, i.e., relative to the turbine shaft. In some embodiments, the bearing member 254 may extend radially inward from the first side 256 of the Belleville spring 250 toward the proximal end 130 of the blade 114. FIG. 18 illustrates a cross-sectional view of a spring-suspended bearing member 249 in which the bearing member 254 extends radially distally from the first side 256 of the Belleville spring 250, but extends radially outward from the first side 256 of the Belleville spring 250, i.e., toward the distal end 132 of the blade 114. The Belleville spring 250 can have a different thickness than the bearing member 254. The thickness of the Belleville spring 250 can vary over its radial range to provide any desired spring action or spring constant.

[0063] FIG. 19 shows the damper element 174 in an actuated position in which the disc springs 250 are in an elastically extended state under the influence of centrifugal force CF caused by the rotating blades 114 rotating above a predetermined rotational speed. In this position, the disc springs 250 are elastically extended at their outer portions 260 (radially outward toward the tips 132 (FIGS. 17-18)), eliminating the gap between the disc springs 250 (see FIGS. 17-18) and frictionally engaging the bearing members 254 with the first bearing surfaces 258 to damp vibrations. As shown, for stacked damper elements 174 other than the radially outermost damper element 174X, the first bearing surface 258 may be the second side surface 262 of the disc springs 250 of the adjacent damper element. That is, the first bearing surface 258 includes the second side surface 262 of the disc springs 250 opposite the first side surface 256. The end surface 266 of the bearing member 254 frictionally engages the second side 262 of the disc spring 250 of the adjacent damper element 174 to damp vibration. In the case of the radially outermost damper element 174X, the second side 262 of that disc spring 250 frictionally engages the first bearing surface 258, i.e., the radially outer end surface 270, which is part of the end surface 270 of the body opening 160. In view of the above, it will be appreciated that the first bearing surface 258 can be located on either the second side 262 of the disc spring 250 of the rotating blade 114 or the end surface 270 of the body opening 160. The term "elastically extended" refers to the disc spring 250 being sufficiently extended to frictionally engage the bearing member 254 with the first bearing surface 258, but may not be fully extended because the travel distance of the bearing member 254 is limited by the first bearing surface 258. Belleville springs 250 may also be used to control the predetermined resonant frequency of RTE body 190, for example, by providing different outer dimensions and / or mounting / pinning locations between the ends of RTE body 190.

[0064] FIG. 20 shows a cross-sectional view of another embodiment in which the disc springs 250 may, but are not necessarily, fixedly connected to the RTE body 190. In FIG. 20, the RTE body 190 may further include a positioning collar 272, which may be concentrically disposed with the RTE body 190. The positioning collar 272 may thus axially position each disc spring 250 relative to the RTE body 190 without the disc springs 250 being fixedly connected to the RTE body 190. The positioning collar 272 may be a tubular member that slides over the RTE body 190 or may be integral with the RTE body 190. In either case, the end 274 of the positioning collar 272 may abut the second side 262 of the disc spring 250 at the center 252 adjacent the positioning disc spring 250, providing a surface against which the disc spring 250 may elastically stretch. Positioning collar 272 may also be used to control the predetermined resonant frequency of RTE body 190, for example, by providing different outer dimensions.

[0065] 21-22 show side, partial cross-sectional views of a vibration damping system 120 including a plurality of stacked damper elements 174 including flexible legs according to another embodiment of the present disclosure. FIG. 21 shows the damper element 174 in a first, relaxed position, and FIG. 22 shows the damper element 174 in a second, actuated position with the flexible legs frictionally engaged with the body opening 160. In this embodiment, the damper element 174 includes a head member 300 having at least a partially angled surface 302. The damper element 174 also includes a plurality of flexible and expandable legs 304 (hereinafter simply "flexible legs 304") extending from the head member 300. Each flexible leg 304 includes a radially extending (relative to the blade 114) body portion 306 having an end portion 308. The end section 308 has an outer end surface 310 and an inner end surface 312. As shown in Figures 21-22, the head member 172 engages with the flexible legs 304 of another, adjacent damper element 174, causing the flexible legs 304 to bend outward and frictionally engage with the inner surface 162 of the body opening 160 to damp vibrations under the influence of centrifugal force CF caused by rotation of the rotating blade 114 at a rotational speed higher than a predetermined rotational speed.

[0066] Each flexible leg 304 may have any configuration that may enable it to flex outwardly such that the outer end surface 310 may frictionally engage the inner surface 162 of the body opening 160 in the blade 114. In the illustrated exemplary embodiment, adjacent radially extending body sections 306 (hereinafter "body sections 306") of the flexible legs 304 define a slot 314 therebetween. The slot 314 may terminate at the head member 300. The slot 314 may have a rounded radial outer extent 316, e.g., U-shaped. However, other shapes are possible, such as V-shaped, cathedral-shaped, etc. Any number of flexible legs 304 may be provided on each damper element 174. In one embodiment, three (3) to six (6) flexible legs 304 are used on each damper element 174, although other numbers are possible. In other embodiments, body portion 306 can have alternative structures, such as wider or thinner sections, curvatures, voids, etc., to assist and / or control its bending.

[0067] As previously mentioned, the head member 300 has at least a partially inclined surface 302. The at least partially inclined surface 302 (hereinafter for brevity, "inclined surface 302") may extend, for example, as a solid circular surface or partially around the periphery of the head member 300, i.e., also with breaks or open areas between the inclined surfaces. The one or more inclined surfaces 302 may have an angle α ranging between 25° and 55° with respect to the inner surface 162 of the body opening 160. As previously mentioned, the body opening 160 may extend generally radially in the body 128 of the blade 114. The inner end surface 312 of the plurality of flexible legs 304 is configured to receive, i.e., engage and move under the influence of, the inclined surface 302 of the head member 300 of the adjacent damper element 174. The inner end surface 312 of the flexible leg 304 may have an angle β ranging between 25° and 55° relative to the inner surface 162 of the body opening 160. Although the angles α and β may be the same, this is not necessary in all cases as long as the head member 300 is capable of pushing the leg 304 of the adjacent damper element 174 outwardly toward the inner surface 162 of the body opening 160. That is, the head member 300 of the adjacent damper element 174 may frictionally engage the outer end surface 310 of the flexible leg 304 with the inner surface 162 of the body opening 160 to damp vibrations when a specific centrifugal force CF is applied based on a predetermined rotational speed of the blade 114.

[0068] In one embodiment, the head member 300 and collectively the body portions 306 of the flexible legs 304 each have a first outer dimension OD9. The outer end surfaces 310 of the flexible legs 304 collectively define a second outer dimension OD10 that is greater than the first outer dimension OD9. Thus, the head member 300 and the body portion 306 have an outer dimension OD9, i.e., OD10, that is less than the outer end surfaces 310 of the flexible legs 304. Although shown and described as having the same outer dimension OD9, the body portion 306 and the head member 300 may have different outer dimensions, so long as both are less than the outer dimension OD10 of the outer end surfaces 310. As shown in FIGS. 21 and 22, the second outer dimension OD10 of the outer end surfaces 310 matches the inner dimension ID1 of the body opening 160, such that in a relaxed state, the flexible legs 304 pass freely through the body opening 160. Additionally, in one embodiment, the outer end surface 310 of each flexible leg 304 may be parallel to the inner surface 162 of the body opening 160 in the relaxed state of the plurality of flexible legs 304. In another embodiment, the outer end surface 310 of each flexible leg 304 may not be parallel to the inner surface 162 of the body opening 160 in the relaxed state of the plurality of flexible legs 304, but by no more than ±5°. In any case, the damper element 174 may be easily inserted into the body opening 160, either singly or pre-stacked, without the outer end surfaces 310 of its end sections 308 impeding insertion.

[0069] As shown in FIGS. 21-22, the damper element 174 includes an opening 320 through the center of the head member 300, and the RTE body 190 extends through the opening 320 in the head member 300. The opening 320 and the RTE body 190 can have any mating cross-sectional shape, such as circular, rectangular or elliptical, polygonal, etc. A single RTE body 190 can extend through each damper element 174 in a stack of damper elements 174 in the vibration damping system 120. The RTE body 190 is configured to resonate at a predetermined resonant frequency, for example, the same frequency as the rotating blades 114 in the body opening 160, such that the RTE body 190 generates a force against one or more damper elements 174. As described herein, the RTE body 190 can be configured to resonate at a predetermined resonant frequency, for example, the same resonant frequency as the rotating blades 114, by controlling its mass, flexibility, stiffness, dimensions, and length, among other factors. The RTE body 190 slides freely within the opening 320, but has a close clearance such that movement of the RTE body 190 caused by vibration of the blade 114 physically impinges on the inside of the opening 320, causing the respective damper elements 174 to move. In this manner, the RTE body 190 can reduce the likelihood of the damper elements 174 sticking against the inner surface 162 of the body opening 160, or to each other. In another embodiment not shown, the vibration damping system 120 as shown in FIGS. 21-22 may further include a radially outer retaining element secured to the RTE body 190 for retaining a plurality of stacked damper elements 174 on the RTE body 190.

[0070] FIG 23 shows a cross-sectional close-up view of a vibration damping system 120 including damper elements 174 each including an outer body and an inner body around an RTE body 190 according to an embodiment of the present disclosure. FIG 24 shows a cross-sectional view of a vibration damping system 120 including damper elements 174 each including an outer body and an inner body around an RTE body 190 according to another embodiment of the present disclosure. Each damper element 174 may include an outer body 340 having an inner opening 342. The outer body 340 may also include a first end surface 344 and an opposing second end surface 346.

[0071] The outer body 340 may have an outer surface 348 having a shape and size to match the body opening 160, e.g., to fit within the body opening 160, which in turn has an inner surface 162 having an inner dimension ID1. Each outer body 340 has an outer dimension OD11 sized to frictionally engage the inner dimension ID1 of the body opening 160 to damp vibrations during movement of the turbine component 111, e.g., the nozzle 112 or blade 114. That is, the outer dimension OD11 of the outer body 340 of each damper element 174 rubs against the inner surface 162 of the airframe opening 160 to damp vibrations during movement of the airfoil 134 (FIGS. 3-4) of the nozzle 112 or blade 114. During assembly, the inner dimension ID1 and the outer dimension OD11 are dimensioned to allow the damper element 174 to be placed within the body opening 160, i.e., to match as defined herein. In one non-limiting example, the difference between the outer dimension OD11 of the damper element 174 and the inner dimension ID1 of the inner surface 162 of the body opening 160 may be in the range of approximately 0.04 to 0.06 millimeters (mm), which allows the damper element 174 to be inserted but frictionally engages during use and relative movement of the airfoil portion 134 of the nozzle 112 or blade 114 (Figures 3-4).

[0072] The first end surface 344 and the second end surface 346 of the outer body 340 are complementary, i.e., mating, such that they can frictionally engage one another. In the FIG. 23 embodiment, the first end surface 344 of the outer body 340 is at least partially concave and the second end surface 346 of the outer body 340 is at least partially convex. In this manner, the first end surface 344 and the second end surface 346 of adjacent damper elements 174 can frictionally engage one another and move rotationally relative to one another as the nozzle 112 or blade 114 moves.

[0073] In another embodiment, as shown in the schematic cross-sectional view of FIG. 24, the first end surface 344 of the outer body 340 is planar and the second end surface 346 of the outer body 340 is also planar. Again, the first end surface 344 and the second end surface 346 of adjacent damper elements 174 can frictionally engage and slide against one another as the turbine component 111, e.g., the nozzle 112 or the blade 114, moves. Other complementary shapes for the end surfaces 344, 346 are also possible. The outer body 340 also includes a central opening 350 (part of the inner opening 342) that extends through the first end surface 344 and the second end surface 346. As will be described, the central opening 350 is configured to allow the RTE body 190 to extend therethrough and to allow pivotal movement of the inner body 360 within the outer body 340.

[0074] Each damper element 174 may also include an inner body 360 that is movable in a nested manner within the inner opening 342 of the outer body 340. The inner body 360 has a central opening 362 that includes a first portion 364 configured to internally engage the RTE body 190. The inner body 360 also includes an outer surface 366 configured to frictionally engage a portion 368 of the inner opening 342 of the outer body 340. The inner body 360 and the inner opening 342 of the outer body 340 may take a variety of forms. In one embodiment shown in FIG. 23, the outer surface 366 of the inner body 360 may have a pear shape. More specifically, the outer surface 366 of the inner body 360 may include a bulbous base 370 and a narrower neck 372. The bulbous base 370 and the narrow neck 372 are integral with one another, i.e., of one-piece construction. In the example shown in FIG. 23, the narrow neck 372 includes a first portion 364 of the central opening 362 of the inner body 360. The first portion 364 has an internal dimension ID2 configured to engage with the external dimension OD12 of the RTE body 190. The internal dimension ID2 allows for sliding engagement with the external dimension OD12 of the RTE body 190. However, the first portion 364 of the central opening 362 has a sufficient (radial) length to oblige the inner body 360 to move with the RTE body 190, e.g., tilt, pivot, or otherwise move under the influence of the RTE body 190. The predetermined resonant frequency of the RTE body 190 may also be controlled.

[0075] The spherical base 370 includes a second portion 378 of the central opening 362 of the inner body 360 having an inner dimension ID3 that is greater than the inner dimension ID2 of the first portion 364 of the central opening 362 of the inner body 360. Thus, the second portion 378 of the central opening 362 of the inner body 360 is spaced apart from the RTE body 190. The central opening 350 of the outer body 340 is also spaced apart from the damper element 174 and the inner body 360 of the RTE body 190 at both end faces 344, 346. In this way, the second portion 378 of the central opening 362 of the inner body 360 allows a pivotal movement of the inner body 360 within the outer body 340 under the effect of bending and / or movement of the RTE body 190 such that the turbine component 111, i.e. the nozzle 112 or the blade 114, vibrates.

[0076] The inner opening 342 of the outer body 340 has a shape configured to receive the pear shape of the outer side 366 of the inner body 360 and allow frictional engagement between the inner body 360 and the outer body 340 under the influence of the RTE body 190 against the inner body 360. When the RTE body 190 moves, for example, flexes with the airfoil 134 during its movement, it imparts motion to the inner body 360 through the first portion 364 of the central opening 362 of the inner body 360, which can cause the inner body 360 to rock or tilt relative to the outer body 340. When this occurs, the inner body 360 and the outer body 340 frictionally engage to damp vibrations. The frictional engagement can occur anywhere along the outer side 366 of the inner body 360 and the inner opening 342 of the outer body 340. For example, frictional engagement may occur near the top of the bulbous base 370 and the outer surface 366 of the inner body 360 and the corner 380 of the inner opening 342 of the outer body 340, where it expands to match the pear shape of the inner body 360. Frictional engagement may also occur anywhere along the outer surface 366 of the bulbous base 370 and / or the narrower neck portion 372.

[0077] 24, in one embodiment, the inner body 360 includes a planar washer member 382. The planar washer member 382 may include any plate having a central opening 384 therein. The central opening 384 of the planar washer member 382 has an inner dimension ID4 configured to engage with the outer dimension OD13 of the RTE body 190, i.e., slidingly engages but forces lateral pivoting with the RTE body 190. The inner dimension ID4 allows for sliding engagement with the outer dimension OD13 of the RTE body 190. However, the planar washer member 382 has a sufficient (radial) length to be obliged to move with the RTE body 190, e.g., tilt, pivot, or otherwise move under the influence of the RTE body 190. In this manner, the inner body 360 (washer member 382) moves and moves with the RTE body 190 as the turbine component 111, e.g., the nozzle 112 or blade 114.

[0078] In FIG. 24, the outer body 340 includes a cup member 386 providing an inner opening 342 that is configured to receive the planar washer member 382. In one example, the cup member 386 includes a base 388 and a tubular side 390 that collectively surround and encapsulate the planar washer member 382 with the adjacent damper element 174. The outer body 340 also includes a first end face 344 and a second end face 346 (surfaces of the cup member 386), which are planar as previously described. The inner body 360, and more particularly the cup member 386, also includes a central opening 392 (a portion of the inner opening 342) through which the RTE body 190 can freely pass. The inner body 360, including the planar washer member 382, ​​may frictionally engage any portion of the inner opening 342 of the outer body 340 to dampen vibrations. The planar end faces 344, 346 of adjacent damper elements 174 also frictionally engage each other to dampen vibrations. The outer body 340 (i.e., the outer surface of the cup member 386) is sized to slide within the body opening 160 but may frictionally engage the inner surface 162 of the body opening 160, i.e., their respective dimensions match, to dampen vibrations during operation of the nozzle 112 or blade 114. The RTE body 190 may also deflect during operation of the nozzle 112 or blade 114 to dampen vibrations. Any number of stacked damper elements 174, as in FIG. 24 , may be employed in the vibration damping system 120.

[0079] 23, the vibration damping system 120 may include an RTE body 190 extending into and fixed relative to the body opening 160. The RTE body 190 passes through an inner opening 342 of the outer body 340, including central openings at the end faces 344, 346. The RTE body 190 also passes through a second portion 378 of the central opening 362 of the inner body 360 and is slidingly engaged by a first portion 364 of the central opening 362 of the inner body 360. More specifically, the RTE body 190 extends into the body opening 160 of the turbine component 111, e.g., the nozzle 112 or the blade 114, and engages within the first portion 364 of the central opening 362 of each inner body 360 of the plurality of stack damper elements 174. As previously mentioned, the inner body 360 and the first portion 364 of the central opening 362 of the RTE body 190 are sized and shaped so that the inner body 360 slides freely on the RTE body 190, but the inner body 360 can move as dictated by the RTE body 190. In this manner, each damper element 174 may experience different motion with the RTE body 190 and provide different vibration damping through the frictional engagement of the outer body 340 and the inner body 360. The vibration damping system 120 of FIG. 24 operates in a similar manner. Varying shapes and sizes of the outer body 340 and the inner body 360 may also be used to control the predetermined resonant frequency of the RTE body 190.

[0080] 25 shows a schematic cross-sectional view of a vibration damping system 120 including an RTE body 190 used with a damper element 174 in the form of a wire mesh member 400. FIG 25 shows the RTE body 190 attached to the tip 130 of a turbine component 111, with a number of wire mesh members 400 attached. A retaining member 402 may be positioned along the RTE body 190 to retain the wire mesh members 400 and control a predetermined resonant frequency of the RTE body 190.

[0081] FIG. 26 shows a schematic cross-sectional view of a vibration damping system 120 including an RTE body 190 used with a damper element 174 in the form of a wire mesh member 400. FIG. 26 shows the RTE body 190 attached to the base end 132 of the turbine component 111 and with a single mesh member 400. A retaining member 402 may be positioned along the RTE body 190 to retain the wire mesh member 400 and control a predetermined resonant frequency of the RTE body 190. The vibration damping system 120 may also optionally include a compression member 404 movable along the RTE body 190 to compress the one or more wire mesh members against the retaining member 402 during operation of the turbine component 111, i.e., beyond the compression provided by the centrifugal force of the rotating blades 114.

[0082] 27, in another embodiment, multiple RTE bodies 190 may be used. The RTE body 190 includes one or more first RTE bodies 190A having a second end 410A fixed relative to the distal end 132 of the body 128 and a first free end 412A extending toward the proximal end 130. The RTE body 190 also includes one or more second RTE bodies 190B having a second end 412B fixed relative to the proximal end 130 of the body 128 and a first free end 410B extending toward the distal end 132. Any number of each RTE body 190A, 190B may be employed.

[0083] The mesh member 400 surrounds both types of RTE bodies 190A, 190B such that each RTE body 190A, 190B is in contact with one or more of the other RTE bodies 190A, 190B during operation of the turbine component 111. In this manner, each RTE body 190A, 190B is in contact with one or more of the other RTE bodies 190A secured to the tip end 132 and / or one or more of the other RTE bodies 190B secured to the base end 130.

[0084] Figures 28 and 29 show cross-sectional views of various embodiments taken along line AA in Figure 27. Figure 28 shows a cross-sectional view of an embodiment including one RTE body 190A and one RTE body 190B. Figure 29 shows a cross-sectional view including multiple (e.g., two) RTE bodies 190A and multiple (e.g., two) RTE bodies 190B. Any number of each type of RTE body 190A, 190B may be used as long as they are surrounded by one or more wire mesh members to allow limited movement within the body opening 160, for example, in circumferential (in and out of the page) and radial (up and down the page).

[0085] A retaining member 402 (FIGS. 25-26) may be provided to retain wire mesh member 400 along the length of RTE body 190, 190A, 190B. In one example, retaining member 402 may be disposed on one or more of RTE bodies 190A and / or 190B to prevent wire mesh member 400 from moving along the length of RTE body 190, e.g., due to centrifugal or vibrational forces of blade 114 or vibrational forces of nozzle 112, as in FIG. 25. Alternatively, retaining member 402 may be provided by closed end 414 of body opening 160 at tip 132 of body 128, as shown in FIG. 27. (Note that this retention member arrangement may be used as an alternative to the embodiment of FIGS. 25-26. In FIG. 27, fixed end 410A of RTE body(s) 190A may be secured by being threaded or otherwise secured to closed end 414 of body opening 160. Although not shown, fixed end 412B of RTE body(s) 190B may be similarly secured to proximal end 130.

[0086] FIG. 30 shows a perspective view illustrating a wire mesh member 400. The wire mesh member 400 includes any now known or later developed wire mesh dampening material suitable for restricting movement of the RTE body(s) 190. The wire mesh member 400 may also be coated with various coating materials to vary its frictional characteristics. The wire mesh member 400 may be referred to as "metal rubber." As shown in FIG. 30, the wire mesh member 400 may include a woven wire mesh material 418.

[0087] FIG. 31 shows a perspective view of a vibration damping system 120 including an RTE body 190 including a retention system 420 including multiple retention members 422. In this embodiment, each retention member 422 includes a protrusion 424 on the RTE body 190. The RTE body 190 also includes portions on its outer surface where no protrusions 424 are present. The one or more protrusions 424 may extend any extent around and / or along the RTE body 190 to create a desired outer dimension on the wire mesh member 400 and / or a desired predetermined resonant frequency of the RTE body 190. In an exemplary embodiment, the protrusion(s) 424 may extend symmetrically around the entire circumference of the RTE body 190, although such symmetry is not required. Any number of protrusions 424 may be provided on the RTE body 190, for example, one for each wire mesh member 400.

[0088] 32 shows an assembled side view of an RTE body 190 including a retention system 430 and retention members 432 according to another embodiment of the present disclosure. In this embodiment, each retention member 432 includes a threaded portion 434 on a first portion of the outer surface of the RTE body 190. The RTE member 190 may also optionally include a non-threaded section 436 on a second portion on the outer surface of the RTE body 190. If no threads are provided, the portion 436 is provided and the inner dimensions of the wire mesh member 400 are free to slide relative to the RTE body 190. Any number of threads 434 may be provided for threading into a respective number of wire mesh members 400. The threads 434 may have any thread style required to allow threaded insertion into the wire mesh member(s) 400 and outward compression of the wire mesh members 400 during assembly. The threaded segment(s) 434 may extend to any extent around and / or along the RTE body 190 to create a desired overall dimension and / or a predetermined resonant frequency. The threaded portion 434 may also alternatively extend the entire length of the RTE body 190.

[0089] 3 and 4, in one embodiment, a single body opening 160 is used in the turbine component 111. Alternatively, in another embodiment, the turbine component 111 includes a first vibration damping system 120A having a first body opening 160A and a second vibration damping system 120B having a second body opening 160B. The vibration damping system 120A in the first body opening 160A includes an RTE body 190A. In this alternative embodiment, multiple vibration damping systems 120 may be used with other systems (120B) each including one or more damper elements 174 in another respective (second) body opening 160B. The damper elements 174 in the second body opening 160B may take any of the forms described above. The vibration damping system 120B also includes another (second) RTE body 190B that extends through an opening in the damper element 174 to the other body opening 160B. The second RTE body 190B may be configured to resonate at a predetermined resonant frequency, for example, the same frequency as the turbine component 111 at the second body opening 160B, i.e., a frequency different from the predetermined resonant frequency of the first RTE body 190. The second RTE body 190B generates a force on the damper elements 174 at the second body opening 160B in a manner similar to that described for the RTE bodies described herein. Each of the damper elements 174 at the second body opening 160B has a surface in contact with at least one of the second body opening 160B and the other (second) RTE body 190B.

[0090] Embodiments of the present disclosure may include any turbine component 111, such as a turbine nozzle 112 or a turbine blade 114. It will be appreciated that those embodiments that require centrifugal force (CF) to actuate one or more damper elements 174 may be employed with turbine components 111 that rotate and experience centrifugal force CF, such as turbine blades 114.

[0091] Methods according to embodiments of the present disclosure may include selecting a frequency of concern Fc for a turbine component 111 operating in a body opening 160 defined in the turbine component. The frequency of concern Fc may be any frequency, typically a resonant frequency, of the turbine component 111 in the body opening 160 that a user may wish to attenuate. Once the frequency of concern Fc is selected, the RTE body 190 to be placed at / within the body opening 160 is configured to have a predetermined resonant frequency, for example, a frequency that is the same as or close to the frequency of concern Fc of the turbine component 111 in the body opening 160. Configuring the RTE body 190 may include selecting (selecting and / or modifying) at least one of the following characteristics of the RTE body 190: length, one or more exterior dimensions, exterior dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine component, one or more attachment types to the turbine component, and number of elongated bodies to generate a resonant frequency of the RTE body 190 during operation of the turbine component 111. In this manner, the RTE body 190 can attenuate vibrations at a predetermined frequency of concern Fc, providing customized vibration attenuation at one or more particular body aperture 160 locations.

[0092] The method may further include placing the RTE body 190 through an opening in the one or more damper elements 174. This step may be performed outside the turbine component 111 and / or the damper element 174 may be placed in the body opening 160 and then the RTE body 190 may be inserted through the damper element (174) 174. In either case, the RTE body 190 with the one or more damper elements 174 is located in the body opening 160. As described above, the damper element 174 in the body opening 160 has a surface in contact with at least one of the body opening 160 and the RTE body 190 that provides vibration damping. The one or more damper elements 174 may be selected from any of the configurations described herein, among others. In one embodiment shown in FIGS. 5-7, the damper element 174 may include a first plurality of stack washers 176 having a first outer dimension OD2 and a second plurality of stack washers 178 having a second outer dimension OD3 (OD2≠OD3). In one embodiment, the first outer dimension OD2 matches the inner dimension ID1 of the body opening 160 (i.e., "match" means close to the same dimension or slightly smaller to allow for insertion of the washer 176 into the body opening 160), and the second outer dimension OD3 is smaller than the inner dimension ID1 of the body opening 160. The first plurality of stacked washers 176 has a first inner dimension ID2, and the second plurality of stacked washers 178 has a second inner dimension ID3. The first inner dimension ID2 is larger than the outer dimension OD1 of the RTE body 190, and the second inner dimension ID3 matches the outer dimension OD1 of the RTE body 190 (i.e., "match" means close to the same dimension or slightly larger to allow for insertion of the RTE body 190 into the washer 178).

[0093] The embodiments of the present disclosure provide various technical and commercial advantages, examples of which are discussed herein. The vibration damping system 120 reduces vibrations of the turbine components with a simple arrangement and does not add a lot of extra mass to the turbine components 111, e.g., the nozzles 112 or the blades 114. The vibration damping system 120 does not increase centrifugal forces on the base ends 130 of the nozzles 112 or the tips 132 of the blades 114 or require configuration changes to the turbine components 111. The vibration damping system 120 allows for a wide variety of different vibration characteristics of the turbine components and / or the vibration damping system 120 (the RTE body 190 and / or the damping elements (174)) beyond simply different frequencies, such as different mode shapes and / or different amplitudes. The vibration damping system 120 also allows for customization of the RTE body 190 attachment, e.g., "fixed free" where one end is fixed, moments are allowed, and there is no translation and rotation; or "fixed pin" where one end is fixed, rotation is allowed, and there is no moment or translation. "Fixed-fixed" with both ends fixed. There are various configurations with an attachment (pinned) in the center of the RTE body 190.

[0094] Approximate expressions used in the present specification and claims are applied to describe a quantity that can vary within a tolerance range without causing a change in the basic function to which the quantity relates. Thus, values ​​modified with terms such as "about", "approximately" and "substantially" are not limited to their exact numerical value. In at least some cases, the approximate expression corresponds to the precision of the instrument that measures the value. In some cases, the approximate expression corresponds to the precision of the instrument that measures the value. In the present specification and claims, ranges of numerical limitations are combinable and / or interchangeable with each other. Such ranges specify and include all subranges contained within the range, unless otherwise clear from the context. "About" used in conjunction with a particular value of a range applies to the upper and lower limits and may indicate ±10% of the stated numerical value, except where it depends on the precision of the instrument that measures the value.

[0095] The corresponding structures, materials, acts, and equivalents of the elements identified by functional descriptions in the following claims include any structures, materials, or acts that perform the function in combination with other elements specifically described in the claims. The description of the present disclosure is for the purpose of illustration and explanation, and is not exhaustive or limited to the disclosed form. Numerous modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the present disclosure. The embodiments of the present disclosure have been selected and described to best suitably explain the principles and practical applications of the present disclosure and to enable those skilled in the art to understand the disclosure regarding various embodiments and various modifications suitable for specific applications. [Explanation of symbols]

[0096] 111 Turbine parts 112 Nozzle 114 Blade 120 Vibration Damping System 128 Main Unit 160A First Body Opening 160B Second body opening 174 Damper element 176 First stack washer 178 Second stack washer 190 Resonant tuning long body 190A First Resonant Tuning Elongated Body 190B Second resonant tuning elongated body 192 Opening in damper element 194 Damper element contact surface

Claims

1. 1. A vibration damping system (120) configured to be installed within a first body opening (160A) of a turbine component (111) for damping vibrations in the turbine component (111), the vibration damping system (120) comprising: one or more damper elements (174) within the first body opening (160A); a first resonant tuned elongate body (190A) extending through an opening (192) in one or more damper elements (174) in the first body opening (160A), the first resonant tuned elongate body (190A) configured to resonate at a first predetermined resonant frequency and generate a force on the one or more damper elements (174) in the first body opening (160A); wherein each of the one or more damper elements (174) in the first body opening (160A) has a surface (194) in contact with at least one of the first body opening (160A) and the first resonantly tuned elongated body (190A).

2. 2. The vibration damping system (120) of claim 1, wherein the first resonant tuned elongated body (190A) includes at least one of the following characteristics of the first resonant tuned elongated body (190A) selected to generate a first predetermined resonant frequency during operation of the turbine component (111): length, one or more outer dimensions, outer dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine component (111), one or more attachment types to the turbine component (111), and number of elongated bodies (190).

3. 2. The vibration damping system of claim 1, wherein the one or more damper elements in the first body opening include a plurality of damper elements stacked together along at least a portion of the first resonant tuned elongated body.

4. 2. The vibration damping system of claim 1, wherein the one or more damper elements in the first body opening are selected from the group including a damper pin, a damper element having a flexible leg, a spring-suspended damper element, nested damper pins, a plate member having an opening, a helical metal ribbon spring, and a wire mesh.

5. 2. The vibration damping system of claim 1, wherein the one or more damper elements in the first body opening include a first plurality of stack washers having a first outer dimension and a second plurality of stack washers having a second outer dimension, the first outer dimension and the second outer dimension being different.

6. 6. The vibration damping system (120) of claim 5, wherein the first outer dimension (OD2) matches an inner dimension of the first body opening (160A) and the second outer dimension (OD3) is smaller than the inner dimension of the first body opening (160A).

7. 7. The vibration damping system of claim 6, wherein the first plurality of stack washers has a first inner dimension (ID2) and the second plurality of stack washers has a second inner dimension (ID3), the first inner dimension (ID2) being greater than an outer dimension (OD1) of the first resonant tuned elongated body (190A), and the second inner dimension (ID3) matching the outer dimension (OD1) of the first resonant tuned elongated body (190A).

8. The turbine component (111) includes a second body opening (160B), and the vibration damping system (120) comprises: one or more damper elements (174) within the second body opening (160B); a second resonant-tuned elongate body (190B) extending through an opening (192) in the one or more damper elements (174) in the second body opening (160B), the second resonant-tuned elongate body (190B) configured to resonate at a second predetermined resonant frequency and generate a force on the one or more damper elements (174) in the second body opening (160B); 2. The vibration damping system of claim 1, further comprising: one or more damper elements in the second body opening having a surface in contact with at least one of the second body opening and the second resonant tuned elongated body.

9. The turbine component (111) of any of the preceding claims, wherein the first predetermined resonant frequency corresponds to a resonant frequency of the turbine component (111) within the first body opening (160A).

10. A turbine component (111), comprising: a body (128) having a first body opening (160A) defined therein; a vibration damping system (120) configured to damp vibrations within the body (128) and to be located within the first body opening (160A); The vibration damping system (120) comprises: one or more damper elements (174) within the first body opening (160A); a first resonant tuned elongate body (190A) extending through an opening (192) in one or more damper elements (174) in the first body opening (160A), the first resonant tuned elongate body (190A) configured to resonate at a first predetermined resonant frequency and generate a force on the one or more damper elements (174) in the first body opening (160A); wherein each of the one or more damper elements (174) in the first body opening (160A) has a surface (194) in contact with at least one of the first body opening (160A) and the first resonant tuned elongated body (190A).

11. 11. The turbine component (111) of claim 10, wherein the first resonant tuned elongated body (190A) includes at least one of the following characteristics of the first resonant tuned elongated body (190A) selected to generate a first predetermined resonant frequency during operation: length, one or more outer dimensions, outer dimension taper along the length, wall thickness at one or more locations, material, one or more attachment locations to the turbine blade (114), one or more attachment types to the turbine blade (114), and number of elongated bodies (190).

12. 11. The turbine component of claim 10, wherein the one or more damper elements in the first body opening include a plurality of damper elements stacked together along at least a portion of the first resonant tuned elongated body.

13. 11. The turbine component of claim 10, wherein the one or more damper elements in the first body opening are selected from the group including a damper pin, a damper element having flexible legs, a spring-suspended damper element, nested damper pins, a plate member having an opening, a helical metal ribbon spring, and a wire mesh.

14. 11. The turbine component of claim 10, wherein the at least one damper element in the first body opening comprises a first plurality of stack washers having a first outer dimension and a second plurality of stack washers having a second outer dimension, the first outer dimension and the second outer dimension being different.

15. The turbine component (111) of claim 14, wherein the first outer dimension (OD2) matches an inner dimension of the first body opening (160A) and the second outer dimension (OD3) is smaller than the inner dimension of the first body opening (160A).

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