Vibration damping element

Abstract

To provide a system that adjusts and / or entirely eliminates the need for shrouds on a turbomachine rotor blade while still providing vibrational damping.SOLUTION: A vibrational dampening element is attached to a component and configured to adjust the amplitude of oscillations. The vibrational dampening element includes a mass. The mass includes a main body and a member that extends from the main body. The mass is encapsulated in a casing. A fluidic chamber is defined between the mass and the casing. A first fluidic portion is disposed between a first side of the mass and the casing, and a second fluidic portion is disposed between a second side of the mass and the casing. The first fluidic portion includes a first accumulator portion directly neighboring the member, and the second fluidic portion includes a second accumulator portion directly neighboring the member. The first accumulator portion is in fluid communication with the second accumulator portion. The vibrational dampening element further includes a primary passage that extends between the first fluidic portion and the second fluidic portion.SELECTED DRAWING: Figure 3

Description

Technical Field

[0001] The present disclosure generally relates to vibration damping elements configured to adjust the amplitude of vibration of a component. Specifically, the present disclosure generally relates to vibration damping elements configured to adjust the amplitude of vibration of a turbomachinery component.

[0002] Description of Research and Development by Federal Government Funds The present invention was made with government support under Contract No. DE-FE0031613 awarded by the United States Department of Energy. The government has certain rights in the invention.

Background Art

[0003] Turbomachines are used in various industries and applications for energy conversion purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid flowing into the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and burned in the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to produce work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator to generate electricity. Then, the combustion gases are discharged from the gas turbine through the exhaust section.

[0004] Typically, turbomachinery rotor blades are exposed to transient aerodynamic loads that cause them to vibrate. Failure to adequately dampen these vibrations can lead to high-cycle fatigue and premature failure of the blades. Of all the turbine stages, the last stage blade (LSB) is the tallest and therefore the most vibration-prone component of the turbine. Conventional vibration damping methods for turbine blades include platform dampers, damping wires, and shrouds.

[0005] Platform dampers are located directly beneath the blade platform and are effective for medium and long shank blades where movement exists in the blade platform. For IGT rear blades, the shank is short to reduce blade weight and therefore the tensile load on the rotor, and thus the platform damper is not effective.

[0006] Generally, turbomachinery rotor blades obtain damping primarily from shrouds. Shrouds may be located at the blade tip (tip shroud) or midway through the span between the hub and the tip (mid-span shroud). These shrouds contact adjacent blades and provide damping when they rub against each other.

[0007] Shrouds provide damping and stiffness to the airfoil, but they make the blade heavier, thus increasing the tensile load on the rotor and increasing the rotor's weight and cost. Therefore, a lightweight solution for the downstream blades is attractive in driving the overall power of the turbomachinery. In general, shrouds can cause a loss of aerodynamic performance. For example, tip shrouds require a large tip fillet that causes tip loss in order to reduce stress concentration, and mid-span shrouds create additional obstruction to the airflow, reducing aerodynamic efficiency. Finally, tip shrouds have been shown to induce large torsions in the vibration mode geometry of the blade, resulting in high aeroelastic flutter instability.

[0008] Therefore, a system is desired in the art to adjust, and even eliminate, the shroud on the rotor blades of a turbomachinery while still providing vibration damping. [Overview of the project]

[0009] The aspects and advantages of the vibration damping elements, rotor blades, and turbomachinery described herein are, in part, described below, or become apparent from this description, or can be learned through the implementation of the art.

[0010] According to one embodiment, a vibration damping element is provided. The vibration damping element is attached to a component and configured to adjust the amplitude of vibration of the component. The vibration damping element includes a mass. The mass includes a body and a member extending from the body. The vibration damping element further includes a casing enclosing the mass. A fluid chamber is defined between the mass and the casing and filled with fluid. A first fluid portion of the fluid chamber is located between a first side of the mass and the casing. The first fluid portion includes a first accumulator portion directly adjacent to the member. A second fluid portion of the fluid chamber is located between a second side of the mass and the casing. The second fluid portion includes a second accumulator portion directly adjacent to the member. The first accumulator portion is in fluid-relative contact with the second accumulator portion. The vibration damping element further includes a primary passage extending between the first fluid portion and the second fluid portion.

[0011] According to another embodiment, a rotor blade is provided. The rotor blade includes a platform. The rotor blade further includes a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the root, which is coupled to the platform, to the tip. A vibration damping element is attached to the rotor blade and configured to adjust the amplitude of vibration of the rotor blade. The vibration damping element includes a mass. The mass includes a body and a member extending from the body. The vibration damping element further includes a casing enclosing the mass. A fluid chamber is defined between the mass and the casing and filled with fluid. A first fluid portion of the fluid chamber is located between a first side of the mass and the casing. The first fluid portion includes a first accumulator portion directly adjacent to the member. A second fluid portion of the fluid chamber is located between a second side of the mass and the casing. The second fluid portion includes a second accumulator portion directly adjacent to the member. The first accumulator portion is in fluid-related communication with the second accumulator portion. The vibration damping element further includes a primary passage extending between the first fluid portion and the second fluid portion.

[0012] In yet another embodiment, a turbomachinery is provided. The turbomachinery comprises a compressor section, a combustor section, and a turbine section. A plurality of rotor blades are provided in the turbine section. Each of the plurality of rotor blades includes a shank extending radially inward from a platform. The rotor blade further includes an airfoil extending radially outward from a root coupled to the platform to a tip. A vibration damping element is attached to the rotor blade and configured to adjust the amplitude of vibration of the rotor blade. The vibration damping element includes a mass. The mass includes a body and a member extending from the body. The vibration damping element further includes a casing enclosing the mass. A fluid chamber is defined between the mass and the casing and filled with fluid. A first fluid portion of the fluid chamber is located between a first side of the mass and the casing. The first fluid portion includes a first accumulator portion directly adjacent to the member. A second fluid portion of the fluid chamber is located between a second side of the mass and the casing. The second fluid portion includes a second accumulator portion directly adjacent to the member. The first accumulator portion is in fluid-related communication with the second accumulator portion. The vibration damping element further includes a primary passage extending between the first fluid portion and the second fluid portion.

[0013] These features, embodiments, and advantages of the vibration damping element, rotor blade, and turbomachinery, as well as other features, embodiments, and advantages, will be better understood by referring to the following description and the appended claims. The appended drawings incorporated herein and constituting part of this specification illustrate embodiments of the art and, together with the description in the specification, are useful in illustrating the principles of the art.

[0014] A full and implementable disclosure of the vibration damping element, rotor blade, and machine, including best modes of manufacture and use of the system and method, directed to those skilled in the art, is described herein with reference to the accompanying drawings. [Brief explanation of the drawing]

[0015] [Figure 1]A schematic diagram of a turbomachinery according to an embodiment of the present disclosure is shown. [Figure 2] This exhibits an exemplary turbine section of a gas turbine comprising multiple turbine stages arranged in a series flow sequence according to embodiments of the present disclosure. [Figure 3] This shows a perspective view of a rotor blade according to an embodiment of the present disclosure. [Figure 4] This shows a perspective view of a vibration damping element according to an embodiment of the present disclosure. [Figure 5] Figure 4 shows a cross-sectional view of the vibration damping element according to an embodiment of this disclosure, along the radial direction. [Figure 6] Figure 4 shows a cross-sectional view of the vibration damping element according to an embodiment of this disclosure, along the axis centerline of the vibration damping element. [Figure 7] A cross-sectional view of the vibration damping element according to the embodiment of this disclosure is shown along the radial direction. [Figure 8] This shows a perspective view of a vibration damping element according to an embodiment of the present disclosure. [Figure 9] Figure 8 shows a cross-sectional view of the vibration damping element according to an embodiment of this disclosure. [Figure 10] Figure 8 shows a cross-sectional view of the vibration damping element according to an embodiment of this disclosure. [Figure 11] Figure 8, according to an embodiment of the present disclosure, shows two adjacent turbomachine rotor blades with vibration damping elements mounted in two different orientations. [Modes for carrying out the invention]

[0016] Hereinafter, embodiments of the vibration damping element, rotor blade, and turbomachinery are referenced in detail, with one or more examples shown in the drawings. Each example is presented for illustrative purposes and is not intended to limit the Art. In fact, it will be apparent to those skilled in the art that modifications and alterations are possible in the Art without departing from the scope or spirit of the claimed Art. For example, features illustrated or described as part of one embodiment can be used in another embodiment to bring about further embodiments. Accordingly, this disclosure is intended to encompass such modifications and alterations that fall within the scope of the appended claims and their equivalents.

[0017] Detailed descriptions use numerals and letters to refer to features in the drawings. Similar or identical reference numerals in the drawings and descriptions are used to refer to similar or identical parts of the present invention. When used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of any individual component.

[0018] As used herein, the terms "upstream" (or "forward") and "downstream" (or "rearward") refer to relative directions with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel and / or coaxial with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component. Approximating terms such as "generally" or "about" include values within plus or minus 10 percent of the stated value. When used in the context of an angle or direction, such terms include the range of plus or minus 10 degrees of the stated angle or direction. For example, "generally perpendicular" includes directions within 10 degrees of perpendicular in any direction, such as clockwise or counterclockwise.

[0019] Referring now to the drawings, FIG. 1 shows a schematic view of one embodiment of a turbomachine, which is a gas turbine 10 in the illustrated embodiment. Although industrial or land-based gas turbines are shown and described herein, the present disclosure is not limited to land-based and / or industrial gas turbines unless specifically recited in the claims. For example, the rotor blades described herein can be used in any type of turbomachine, including but not limited to steam turbines, aircraft gas turbines, or marine gas turbines.

[0020] As shown, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream of the inlet section 12, one or more combustors (not shown) within a combustor section 16 disposed downstream of the compressor section 14, a turbine section 18 disposed downstream of the combustor section 16, and an exhaust section 20 disposed downstream of the turbine section 18. In addition, the gas turbine 10 can include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0021] The compressor section 14 can generally include a plurality of rotor disks 24 (one of which is shown), and a plurality of rotor blades 26 connected to each rotor disk 24 and extending radially outward from each rotor disk 24. Each rotor disk 24 can then be coupled to a portion of a shaft 22 extending through the compressor section 14, or each rotor disk 24 can form such a portion.

[0022] The turbine section 18 can generally include a plurality of rotor disks 28 (one of which is shown), and a plurality of rotor blades 30 extending radially outward from each rotor disk 28 and interconnected to each rotor disk 28. Each rotor disk 28 can then be coupled to a portion of a shaft 22 extending through the turbine section 18, or each rotor disk 28 can form such a portion. The turbine section 18 further includes an outer casing 31 that at least partially defines a hot gas path 32 through the turbine section 18 by circumferentially surrounding a portion of the shaft 22 and the rotor blades 30.

[0023] During operation, a working fluid such as air flows through the inlet section 12 into the compressor section 14, where the air is gradually compressed, and thus pressurized air is delivered to the combustors of the combustor section 16. The pressurized air is mixed with fuel and burned in one or more combustors to produce combustion gases 34. The combustion gases 34 flow from the combustor section 16 to the turbine section 18 through the high-temperature gas path 32, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. This mechanical rotational energy can then be used to operate the compressor section 14 and / or generate electricity. The combustion gases 34 leaving the turbine section 18 can then be exhausted from the gas turbine 10 through the exhaust section 20.

[0024] Figure 2 shows an exemplary turbine section 18 of a gas turbine 10, comprising multiple turbine stages arranged in a series flow sequence. Each stage of the turbine comprises a row of fixed turbine nozzles or vanes (e.g., nozzles 100) arranged axially adjacent to a corresponding row of rotating turbine rotor blades (e.g., blades 50). Figure 2 shows four turbine stages. The exact number of stages in the turbine section 18 may be more or less than the four stages shown in Figure 2. The four stages are merely illustrative of one turbine design and are not intended to limit the turbine rotor blades claimed at this time.

[0025] Each stage comprises a plurality of turbine nozzles or vanes 100 and a plurality of turbine rotor blades 50. The turbine nozzles 100 are mounted on an outer casing 31 and arranged in an annular manner around the axis of the turbine shaft 22. The turbine rotor blades 50 are arranged in an annular manner around the turbine shaft 22 and are coupled to the turbine rotor 36.

[0026] It can be understood that the turbine nozzle 100 and the turbine rotor blades 50 are located, or at least partially located, within the high-temperature gas path 32 of the turbine section 18. The various stages of the turbine 10, as indicated by arrows 20, define, at least partially, the high-temperature gas path 32 through which the combustion gases pass during the operation of the gas turbine 10.

[0027] Figure 3 shows a perspective view of a rotor blade 50 that can be incorporated into any stage of the turbine section 18 or compressor section 14. In an exemplary embodiment, the rotor blade 50 may be used in the turbine section 18. As shown in Figure 3, the turbine rotor blade 50 includes a platform 66, a shank 51, and an airfoil 52. As shown, the shank 51 may extend radially inward from the platform 66 with respect to the axial centerline of the gas turbine 10. In many embodiments, the airfoil 52 may extend from the platform 66 in the opposite direction from the shank 51. For example, the airfoil 52 may extend radially outward from the platform with respect to the axial centerline of the gas turbine 10. In various embodiments, the airfoil 52 includes a positive pressure side surface 54 and an opposite negative pressure side surface 56. The positive pressure side surface 54 and the negative pressure side surface 56 meet or intersect at the leading edge 58 and trailing edge 60 of the airfoil 52. The leading edge 58 and the trailing edge 60 can be positioned apart from each other, and the end of the airfoil section 52 in the axial direction A can be determined. A straight chord line (not shown) extends between the leading edge 58 and the trailing edge 60, and therefore the positive pressure side surface 54 and the negative pressure side surface 56 extend in the chord direction between the leading edge 58 and the trailing edge 60.

[0028] The positive pressure side surface 54 generally comprises the aerodynamically concave outer surface of the airfoil 52. Similarly, the negative pressure side surface 56 can generally define the aerodynamically convex outer surface of the airfoil 52. The leading edge 58 of the airfoil 52 may be the first part of the airfoil 52 that is involved with, i.e., exposed to, the combustion gases in the hot gas path 32. The combustion gases may be guided along the aerodynamic contour of the airfoil 52, i.e., along the negative pressure side surface 56 and the positive pressure side surface 54, before being exhausted at the trailing edge 60.

[0029] As shown in Figure 3, the airfoil 52 intersects with the platform 66 of the turbine rotor blade 50 and includes a root or first end 64 extending radially outward from the platform 66. The airfoil 52 has a second end or tip 68 as its radial end. The root 64 of the airfoil 52 may be located at the intersection between the airfoil 52 and the platform 66. The tip 68 is located radially opposite the root 64. Thus, the tip 68 can generally define the radially outermost portion of the rotor blade 50 and may be configured to be located adjacent to a fixed shroud or seal (not shown) of the turbine section 18.

[0030] The positive pressure side surface 54 and the negative pressure side surface 56 extend in the span direction and define the span length 70 of the airfoil 52 between the root 64 and / or platform 66 and the tip 68. In other words, each rotor blade 50 includes an airfoil 52 having oppositely oriented positive pressure side surface 54 and negative pressure side surface 56 that extend in the chord direction between the oppositely oriented leading edge 58 and trailing edge 60, and in the span direction 70 between the root 64 and tip 68 of the airfoil 52.

[0031] In certain configurations, the airfoil 52 may include a fillet 72 formed between the platform 66 and the airfoil 52, close to the root 64. The fillet 72 may include a welded or brazed fillet that can be formed by conventional MIG welding, TIG welding, brazing, etc., and may include an outer shape that can reduce hydrodynamic losses as a result of the presence of the fillet 72. In certain embodiments, the platform 66, the airfoil 52, and the fillet 72 may be formed as a single component by casting and / or machining and / or 3D printing and / or any other suitable technique known at present or to be developed and / or discovered later. In certain configurations, the rotor blade 50 includes a mounting portion 74 (such as a dovetail joint) formed to connect and / or fix the rotor blade 50 to the shaft 22.

[0032] The span length 70 can be measured from the root 64 to the tip 68 of the airfoil section 52. The position at the span length 70 can be indicated using a percentage of the span length 70. For example, "0% span" can refer to the root 64 of the airfoil section 52. Similarly, "100% span" can refer to the tip 68 of the airfoil section.

[0033] As shown in Figure 3, vibration damping elements 300 can be attached to the rotor blades 50 to adjust the amplitude of vibration of the rotor blades during operation of the gas turbine 10. As shown in the figure, in some embodiments, the vibration damping elements 300 may be attached close to the leading edge 58 of the airfoil 52. In other embodiments (not shown), the vibration damping elements 300 may be attached near the trailing edge 60, on or directly below the platform 66, on or inside the positive pressure side surface 54, on or inside the negative pressure side surface 56, and / or on or inside the shank 66.

[0034] In exemplary embodiments, the vibration damping element 300 may be attached to the rotor blade 50, for example by welding or brazing, to reduce and / or completely eliminate vibrations of the rotor blade 50 without causing any obstruction to the flow of combustion gases passing outside the airfoil 52. For example, the vibration damping element 300 may be located inside the airfoil 52 so as to be coupled and fixed to the inner surface of the airfoil 52. In such embodiments, housing the vibration damping element 300 inside the airfoil 52 can provide advantageous damping to the rotor blade 50 without causing additional obstruction to the flow of combustion gases 34. In other embodiments (not shown), the vibration damping element 300 may be directly coupled and fixed to the outer surface of the airfoil 52, for example by welding and / or brazing. The vibration damping element 300 is large enough to significantly reduce, and / or eliminate, vibrations that cause damage to the airfoil section 52 during operation, but can be small enough not to obstruct the flow of combustion gases past the airfoil section 52 and therefore not affect the aerodynamic efficiency of the rotor blade 50.

[0035] As shown in Figure 3, one or more vibration damping elements 300 can be positioned along various locations on the airfoil 52, for example, between 0% and 100% of the span length 70 of the airfoil 52. For example, the rotor blade 50 may include one or more mid-span vibration damping elements 302 that may be positioned in the mid-span region of the airfoil 52. For example, the mid-span vibration damping elements 302 may be positioned on the airfoil 52 between approximately 25% and approximately 75% of the span length 70 of the airfoil 52. In certain embodiments, one or more vibration damping elements 300 may be positioned on the airfoil 52 between approximately 40% and approximately 60% of the span length 70 of the airfoil 52.

[0036] As shown in Figure 3, the rotor blade 50 may further include one or more span tip vibration damping elements 304 positioned radially away from the mid-span vibration damping elements 302. In various embodiments, the span tip vibration damping elements 304 may be positioned between approximately 75% and 100% of the span length 70 of the airfoil section 52. In specific embodiments, the span tip vibration damping elements 304 may be positioned between approximately 90% and 100% of the span length 70 of the airfoil section 52.

[0037] In many embodiments, each of the damping elements 302 and 304 can be sized differently to target a specific frequency range of the rotor blade 50. For example, the span tip vibration damping element 304 can be sized to adjust to the natural frequency at which the vibration mode of the rotor blade 50 is dominant at the tip. Similarly, the mid-span vibration damping element 302 can be sized to adjust to the natural frequency at which the vibration mode of the rotor blade 50 is dominant in the mid-span region. For example, each vibration damping element 300 can be sized to adjust to the frequency of the rotor blade 50 based on the respective span position of the airfoil section 52 to which they are attached.

[0038] Figure 4 shows a perspective view of the vibration damping element 300, Figure 5 is a cross-sectional view of the vibration damping element 300 along the radial direction R, and Figure 6 is a cross-sectional view of the vibration damping element 300 along the axial centerline 301. As shown, the axial centerline 301 of the vibration damping element 300 defines an axial direction A substantially parallel to and / or substantially aligned with the axial centerline 301, a radial direction R perpendicular to axis A, and a circumferential direction C extending around axis A. In exemplary embodiments, the axial centerline 301 of the vibration damping element 300 can be aligned (or coaxial) with the direction of motion or vibration of the component to which the vibration damping element 300 is attached.

[0039] In many embodiments, the vibration damping element 300 includes a casing 306 that encloses or surrounds a mass 308. For example, as shown in Figure 5, the casing 306 can be positioned away from the mass 308 such that a fluid chamber 309 is defined in the space between the mass 308 and the casing 306. In this way, the mass 308 can be suspended in the fluid inside the casing 306 so that the mass 308 can move in the fluid relative to the casing 306. For example, when the vibration damping element 300 is attached to a vibrating component, the mass 308 can vibrate in the fluid enclosed by the casing 306, which dampens the vibration of the component by pushing the fluid between the fluid portions 318, 328 of the fluid chamber 309 defined between the casing 306 and the mass 308.

[0040] In exemplary embodiments, the fluid chamber 309 is defined between the mass and the casing and may be filled with a fluid (in particular, a liquid such as liquid gallium or other suitable liquid). For example, the casing 306 may have an inner surface having a shape that mimics the outer surface shape of the mass 308. In various embodiments, the inner surface of the casing 306 is separated from the mass 308 so that the fluid chamber is defined in the space between the mass 308 and the casing 306. In many embodiments, the fluid chamber 309 may include a first fluid portion 318 and a second fluid portion 328. The first fluid portion 318 may be defined between a first side surface 320 of the mass 308 and the casing 306, and the second fluid portion 328 may be defined between a second side surface 330 of the mass 308 and the casing 306.

[0041] In exemplary embodiments, the mass 308 may include a body 310 and a member or annular member 312 extending from the body 310. For example, the annular member 312 may extend in the circumferential direction C, enclosing the body 310 of the mass 308, such that the mass 308 has a circular cross-sectional shape (Figure 6). In many embodiments, the body 310 of the mass 308 may define a first thickness 314, and the annular member 312 of the mass 308 may define a second thickness 316. As shown in Figure 5, the second thickness 316 of the annular member 312 may be less than the first thickness 314 of the body 310. In this way, the majority of the mass 308's weight can be positioned centrally, i.e., close to the axial centerline 301 of the vibration damping element 300.

[0042] As described above, the first fluid portion 318 of the fluid chamber 309 may be positioned between the first side surface 320 of the mass 308 and the casing 306. As shown in the figure, the first fluid portion 318 may include a first central portion 322 extending along the body 310 on the first side surface 320, a first accumulator portion 324 extending along the annular member 312 on the first side surface 320, and a first connecting portion 326 positioned between the first central portion 322 and the first accumulator portion 324. For example, the first central portion 322 may be positioned axially between the first side surface 320 of the body 310 and the casing 306 with respect to the axial centerline 301 of the vibration damping element 300. The first accumulator portion 324 may be positioned axially between the first side surface 320 of the annular member 312 and the casing 306. In various embodiments, both the first accumulator portion 324 and the first connecting portion 326 may be annular passages surrounding the first central portion 322 and defined in the circumferential direction C. For example, the first central portion 322 may extend radially between the axial centerline 301 and the first connecting portion 326 so that the first connecting portion 326 provides fluid communication between the first central portion 322 of the first fluid portion 318 and the first accumulator portion 324.

[0043] In certain embodiments, as described above, the second fluid portion 328 of the fluid chamber 309 can be positioned between the second side surface 330 of the mass 308 and the casing 306. As shown in the figure, the second fluid portion 328 may include a second central portion 332 extending along the body 310 on the second side surface 330, a second accumulator portion 334 extending along the annular member 312 on the second side surface 330, and a second connecting portion 336 positioned between the second central portion 332 and the second accumulator portion 334. For example, the second central portion 332 may be positioned axially between the second side surface 330 of the body 310 and the casing 306 with respect to the axial centerline 301 of the vibration damping element 300. The second accumulator portion 334 may be positioned axially between the second side surface 330 of the annular member 312 and the casing 306. In various embodiments, both the second accumulator portion 334 and the second connecting portion 336 may be annular passages surrounding the second central portion 332 and defined in the circumferential direction C. For example, the second central portion 332 may extend radially between the axial centerline 301 and the second connecting portion 336 so that the second connecting portion 336 provides fluid communication between the second central portion 332 of the second fluid portion 328 and the second accumulator portion 334.

[0044] In various embodiments, the vibration damping element 300 may further include a first bellows tube 358 extending between a first side surface 320 of the annular member 312 and the casing 306, and a second bellows tube 360 ​​extending between a second side surface 330 of the annular member 312 and the casing. The bellows tubes 358, 360 may be obedient so as to be able to flex or contract along the axial centerline 301 so that the mass vibrates axially in the fluid and provides a viscous damping force when attached to a vibrating component (such as a turbine rotor blade 50). For example, in an exemplary embodiment, the mass 308 can be suspended in the fluid by the first bellows tube 358 and the second bellows tube 360. In various embodiments, the first bellows tube 358 and the second bellows tube 360 ​​may be annular so as to extend circumferentially C around the body 310 of the mass 308. In this way, the first bellows tube 358 and the second bellows tube 360 ​​surround the main body 310 with a mass of 308, and can partially define the first fluid portion 318 and the second fluid portion 328, respectively.

[0045] As shown in Figures 5 and 6, the primary passage 362 may extend between the first fluid section 318 and the second fluid section 328 to provide fluid communication between the first fluid section 318 and the second fluid section 328. For example, the primary passage 362 may extend directly from the first central section 322 of the first fluid section 318 to the second central section 332 of the second fluid section 328. In various embodiments, the primary passage 362 may extend along the axial centerline 301 of the vibration damping element 300 so that the primary passage 362 extends coaxially with the axial centerline 301. In other embodiments, multiple primary passages may extend between the first fluid section 318 and the second fluid section 328 of the fluid chamber 309 so as to symmetrically surround the axial centerline 301 of the vibration damping element 300. In exemplary embodiments, when the vibration damping element 300 is attached to a vibrating or oscillating component (such as the rotor blade 50 of a turbomachine shown in Figure 3), the primary passage 362 can be oriented substantially along the vibration direction of the component.

[0046] In many exemplary embodiments, the vibration damping element 300 may further include a plurality of secondary passages 364 defined within the mass 308 and positioned circumferentially apart from one another. The plurality of secondary passages 364 may be arranged around the vibration damping element 300 so as to surround the axial centerline 301. In certain embodiments, each of the secondary passages 364 may be defined within the annular member 312 such that each extends substantially axially between the first fluid portion 318 and the second fluid portion 328. For example, each of the plurality of secondary passages 364 may extend through the annular member 312 from the first accumulator portion 324 of the first fluid portion 318 to the second accumulator portion 334 of the second fluid portion 328.

[0047] The vibration damping element 300 described herein can operate on the principle of a tuned vibration absorber. For example, during the operation of the vibration damping element 300, a fluid (particularly liquid such as liquid gallium or other suitable liquid) can flow between the first fluid section 318 and the second fluid section 328 through the primary passage 362 and a plurality of secondary passages 364. For example, when the vibration damping element 300 is attached to a vibrating component such as a turbine rotor blade 50, the viscous force generated by the fluid rapidly moving between the fluid sections 318 and 328 of the fluid chamber 309 in the primary passage 362 and secondary passages 364 conveniently dampens the amplitude of vibration of the vibrating component. The viscous damping force generated within the vibration damping element 300 cancels out the vibration of the component to which the vibration damping element 300 is attached, conveniently reducing the amplitude of vibration of the vibrating component.

[0048] In an exemplary embodiment, the multiple secondary passages 364 ensure that there is no accumulation of fluid pressure around the accumulator portions 324, 334, i.e., the vibration damping element 300. In this way, the multiple secondary passages 364 conveniently enhance the effectiveness of the vibration damping element 300 by ensuring that there are no rigid regions.

[0049] In many embodiments, the natural frequency of the vibration damping element 300 can be adjusted to a desired mode by changing the stiffness of the bellows tubes 358, 360. Similarly, the natural frequency of the vibration damping element 300 can be adjusted by adjusting the density, size, or weight of the mass 308. This conveniently allows the vibration damping element 300 to be adjusted based on the component to which it is mounted, for example, each of the first, second, and / or third stage turbine rotor blades may include individually adjusted vibration damping elements 300.

[0050] The vibration damping element 300 described herein may be advantageous over conventional designs of damping elements, such as damping elements with only one passage connecting two fluid chambers. For example, the accumulator portions 324, 334 and the multiple secondary passages 364 ensure that there is no force leakage to the stiffness around the damping element 300 and that there is no pressure buildup in the fluid surrounding the bellows tube.

[0051] Figure 7 shows a cross-sectional view of the vibration damping element 300 according to an embodiment of the present disclosure, along the radial direction R. As shown, the annular member 312 may be corrugated to include a plurality of wrinkles, folds, and / or ridges, which conveniently enhances its obedience in the axial direction (i.e., the direction of vibration of the mass 308 when attached to a vibrating component).

[0052] In various embodiments, the annular member 312 may extend continuously between a corrugated portion 342 and a linear portion 344. The corrugated portion 342 of the annular member 312 may extend continuously between a plurality of peaks 338 and valleys 340 that are spaced apart in the axial direction from each other. As shown in Figure 7, the corrugated portion 342 of the annular member 312 may extend radially from the body 310 to the linear portion 344. The linear portion 344 may extend radially from the corrugated portion 342 to the free end 345. In the embodiment shown in Figure 7, a plurality of secondary passages can be defined in the linear portion 344 of the annular member.

[0053] As shown in Figure 7, the casing 306 may be approximately separated from the mass 308 in order to partially define the first fluid portion 318 and the second fluid portion 328 on either side of the mass 308. As shown in the figure, the casing 306 may include a first portion 350 and a second portion that are coupled to both sides of the mass 308. For example, the first portion 350 may be coupled to the free end 345 on the first side of the annular member 312, and the second portion 352 of the casing 306 may be coupled to the free end 345 on the second side of the annular member 312.

[0054] In the embodiment shown in Figure 7, the first fluid portion 318 may further include a first corrugated passage 354 and a second corrugated passage 356 located on either side of the corrugated portion 342 of the annular member 312. For example, the first and second corrugated passages may extend along the corrugated portion 342 on both sides of the annular member 312. In such embodiments, as shown, the first accumulator portion 324 of the first fluid portion 318 and the second accumulator portion 334 of the second fluid portion 328 may extend along the linear portion 344 on both sides of the annular member 312.

[0055] Figures 8 to 10 show vibration damping elements 400 according to another embodiment of the present disclosure. As shown, the vibration damping element 400 may be a “hammer” damper, comprising a large mass mounted on an elongated beam or member. Figure 8 shows a perspective view of the vibration damping element 400, with the casing 406 indicated by a dashed line. Figure 9 shows a cross-sectional view of the vibration damping element 400 along a first direction, and Figure 10 shows a cross-sectional view of the vibration damping element 400 along a second direction perpendicular to the first direction.

[0056] In exemplary embodiments, the vibration damping element 400 may be defined between the mass 408 and the casing 406 and include a fluid chamber 409 filled with a fluid (particularly liquid such as liquid gallium or other suitable liquid). For example, the casing 406 may have an inner surface having a shape that mimics the outer surface shape of the mass 408. In various embodiments, the inner surface of the casing 406 is separated from the mass 408 so that the fluid chamber 409 is defined in the space between the mass 408 and the casing 406. In many embodiments, the fluid chamber 409 may include a first fluid portion 418 and a second fluid portion 428. The first fluid portion 418 may be defined between a first side surface 420 of the mass 408 and the casing 406, and the second fluid portion 428 may be defined between a second side surface 430 of the mass 408 and the casing 406.

[0057] As shown in conjunction with Figures 8 to 10, the vibration damping element 400 includes a casing 406 that encloses or surrounds a mass 408. As shown, the mass 408 may include a body 410 and a member 412 extending from the body and coupled to the casing 406. For example, as shown in Figures 9 and 10, the member 412 of the mass 408 may be attached to the casing 406 and cantilevered from the casing 406 such that a first fluid portion 418 and a second fluid portion 428 are defined in the space between the mass 408 and the casing 406. In this way, the body 410 of the mass 408 may be movable relative to the casing 406 in the fluid held by the fluid chamber 409. For example, when the vibration damping element 400 is attached to a vibrating component (such as the rotor blade 50 of a turbomachinery or other component), the body 410 with mass 408 can vibrate within the fluid enclosed by the casing 406, which causes the fluid to move between the fluid portions 418 and 428 of the fluid chamber 409 defined between the casing 406 and the mass 408, thereby generating a viscous force that dampens the vibration of the component.

[0058] As shown in Figures 9 and 10, the first fluid portion 418 of the fluid chamber 409 may be defined between the first side surface 420 of the mass 408 and the casing 406, and the second fluid portion 428 of the fluid chamber 409 may be defined between the second side surface 430 of the mass and the casing 406. When the vibration damping element 400 is attached to a component (such as the rotor blade of a turbomachinery shown in Figure 3), the first side surface 420 and the second side surface 430 may be substantially perpendicular to the direction of vibration 402 of the component, such that the fluid portions 418 and 428 of the fluid chamber are positioned facing each other with respect to the direction of vibration 402 of the component. In this way, the first fluid portion 418 and the second fluid portion 428 may extend substantially perpendicular to the direction of vibration 402 of the component. In an exemplary embodiment, the primary passage 450 extends along the body 410 of mass 408, substantially parallel to the direction of vibration 402, and the first fluid portion 418 can be coupled to the second fluid portion 428 with respect to the fluid.

[0059] In many embodiments, the first fluid portion 418 of the fluid chamber 409 may include a first accumulator portion 424 extending along a member 412 of mass 408, and the second fluid portion 428 may include a second accumulator portion 434 extending along the member 412 on the side opposite to the first accumulator portion 424. For example, the first accumulator portion 424 and the second accumulator portion 434 may be located on opposite sides of the member 412 and may extend substantially perpendicular to the direction of vibration 402 of the component. In an exemplary embodiment, a secondary passage 452 may extend along the member 412 substantially parallel to the direction of vibration 402, and the first accumulator portion 424 may be coupled to the second accumulator portion 434 with respect to the fluid.

[0060] Figure 11 shows rotor blades 50 of two adjacent turbomachinery with vibration damping elements 400 mounted in two different orientations. As shown, the vibration damping element 400 can be mounted on the airfoil 52 such that the body 410 with mass 408 lies radially outward of the member 412 with respect to the radial direction of the gas turbine 10. In such a configuration, the member 412 may be under a tensile centrifugal load. In another configuration, as shown, the vibration damping element 400 can be mounted on the airfoil 52 such that the body 410 with mass 408 lies radially inward of the member 412 with respect to the radial direction of the gas turbine 10. In such a configuration, the member 412 may be under a compressive centrifugal load.

[0061] When the vibration damping element 400 is in operation, i.e., when the vibration damping element 400 is attached to a component that is shaking or vibrating, fluid can be flowed by the mass 408 between the first fluid portion 418 and the second fluid portion 428 through the primary passage 450 and the secondary passage 452. For example, when the vibration damping element 400 is attached to a vibrating component such as a turbine rotor blade 50, viscous forces arise in the primary passage 450 and the secondary passage 452 from the fluid rapidly moving between the fluid portions 418 and 428 of the fluid chamber 409. These viscous forces cancel out the vibration of the component and reduce the amplitude of the vibration of the component. In an exemplary embodiment, multiple secondary passages 452 between accumulator portions 424 and 434 ensure that there is no pressure buildup in the fluid within the accumulator portions 424 and 434, i.e., around the member 412.

[0062] This specification discloses the present invention, including its best mode, and uses examples to enable those skilled in the art to carry out the invention, including the manufacture and use of any apparatus or system and the execution of any related methods. The patentable scope of the present invention is defined by the claims and may include other embodiments that a person skilled in the art could conceive. Such other embodiments are included in the technical scope of the claims if they include structural elements that do not differ from the language of the claims, or if they include equivalent structural elements that do not differ substantially from the language of the claims. [Explanation of symbols]

[0063] 10 Gas Turbines 12 Entrance Section 14 Compressor Section 16. Combustor Section 18 Turbine Section 20 Exhaust Section / Arrow 22 Turbine shaft 24 Rotor Discs 26 rotor blades 28 Rotor Discs 30 rotor blades 31 Outer casing 32 High-temperature gas pathway 34 Combustion gases 36 Turbine rotor 50 Turbine Rotor Blades 51 Shank 52 Airfoil 54 Positive pressure side surface 56 Negative pressure side surface 58 Leading edge 60 Trailing edge 64 The root or first end (of the airfoil) 66 Platforms 68 The tip or second end (of the airfoil) 70 (Airfoil section) Span direction 72 fillets 74 Mounting part 100 Turbine or vane 300 Vibration damping element 301 (Axis centerline of vibration damping element) 302 Span Intermediate Vibration Damping Element 304 Span tip vibration damping element 306 Casing 308 Mass 309 Fluid Chamber 310 Main Unit 312 Annular member 314 First thickness 316 Second thickness 318 First fluid portion 320 First Aspect 322 First central section 324 First accumulator section 326 First connection section 328 Second fluid portion 330 Second Aspect 332 Second central section 334 Second accumulator section 336 Second connection section 338 Mountain 340 Valley 342 Waveform section 344 Straight section 345 Free end 350 Part 1 352 Part 2 354 The path of the first waveform 356 Second waveform path 358 First bellows tube 360 Second bellows tube 362 Primary passage 364 Secondary passage 400 Vibration damping element 402 Direction of vibration 406 Casing 408 Mass 409 Fluid Chamber 410 Main Unit 412 components 418 First fluid part 420 First Aspect 424 First accumulator section 428 Second fluid portion 430 Second Aspect 434 Second accumulator section 450 Primary passage 452 Secondary passage

Claims

1. A vibration damping element (300) attached to a turbine component and configured to adjust the amplitude of vibration of the turbine component, A mass (308) having a main body (310) and a member (312) extending from the main body (310), A casing (306) enclosing the aforementioned mass (308), A fluid chamber (309) is defined between the mass (308) and the casing (306) and is filled with fluid, The first fluid portion (318) of the fluid chamber (309) includes a first accumulator portion (324) positioned between the first side surface (320) of the mass (308) and the casing (306), and extending along the member (312), A second fluid portion (328) is provided, which is located between the second side surface (330) of the mass (308) and the casing (306), and includes a second accumulator portion (334) extending along the member (312), wherein the first accumulator portion (324) is in fluid-related communication with the second accumulator portion (334), A primary passage (362) extending between the first fluid portion (318) and the second fluid portion (328) Equipped with, The member (312) is an annular member (312) surrounding the main body (310) of the mass (308), A vibration damping element (300) further comprising a first bellows tube (358) extending between the first side surface (320) of the member (312) and the casing (306), and a second bellows tube (360) extending between the second side surface (330) of the member (312) and the casing (306).

2. The vibration damping element (300) according to claim 1, wherein the primary passage (362) extends along the axial centerline of the vibration damping element (300).

3. The vibration damping element (300) according to claim 1, further comprising a plurality of secondary passages (364) arranged at intervals from each other in the circumferential direction, wherein each of the plurality of secondary passages (364) extends through the member (312) from the first accumulator portion (324) to the second accumulator portion (334).

4. A vibration damping element (300) attached to a turbine component and configured to adjust the amplitude of vibration of the turbine component, A mass (308) having a main body (310) and a member (312) extending from the main body (310), A casing (306) enclosing the aforementioned mass (308), A fluid chamber (309) is defined between the mass (308) and the casing (306) and is filled with fluid, The first fluid portion (318) of the fluid chamber (309) includes a first accumulator portion (324) positioned between the first side surface (320) of the mass (308) and the casing (306), and extending along the member (312), A second fluid portion (328) is provided, which is located between the second side surface (330) of the mass (308) and the casing (306), and includes a second accumulator portion (334) extending along the member (312), wherein the first accumulator portion (324) is in fluid-related communication with the second accumulator portion (334), A primary passage (362) extending between the first fluid portion (318) and the second fluid portion (328) Equipped with, The member (312) is a vibration damping element (300) which is a corrugated annular member (312) surrounding the main body (310) of the mass (308) such that the mass (308) has a circular cross-section.

5. The vibration damping element (300) according to claim 1, wherein the mass (308) is suspended in the fluid by the first bellows tube (358) and the second bellows tube (360).

6. The vibration damping element (300) according to claim 1, wherein the primary passage (362) is oriented generally in line with the direction of vibration of the turbine component.

7. Platform (66) and A shank (51) extending radially inward from the platform (66), The airfoil section (52) extends radially outward from the root (64) to the tip (68) connected to the platform (66) and A rotor blade (50) comprising a vibration damping element (300) attached to the rotor blade (50) and configured to adjust the amplitude of vibration of the rotor blade (50), wherein the vibration damping element (300) A mass (308) having a main body (310) and a member (312) extending from the main body (310), A casing (306) enclosing the aforementioned mass (308), A fluid chamber (309) is defined between the mass (308) and the casing (306) and is filled with fluid, The first fluid portion (318) of the fluid chamber (309) includes a first accumulator portion (324) positioned between the first side surface (320) of the mass (308) and the casing (306), and extending along the member (312), The first accumulator portion (324) includes a second fluid portion (328) which is in fluid-related communication with the second accumulator portion (334), and is positioned between the second side surface (330) of the mass (308) and the casing (306) and extends along the member (312), and the first accumulator portion (324) includes a second fluid portion (328) which is in fluid-related communication with the second accumulator portion (334), A primary passage (362) extending between the first fluid portion (318) and the second fluid portion (328) Equipped with, The member (312) is an annular member (312) surrounding the main body (310) of the mass (308), A rotor blade (50) further comprising a first bellows tube (358) extending between the first side surface (320) of the member (312) and the casing (306), and a second bellows tube (360) extending between the second side surface (330) of the member (312) and the casing (306).

8. Platform (66) and A shank (51) extending radially inward from the platform (66), The airfoil section (52) extends radially outward from the root (64) to the tip (68) connected to the platform (66) and A rotor blade (50) comprising a vibration damping element (300) attached to the rotor blade (50) and configured to adjust the amplitude of vibration of the rotor blade (50), wherein the vibration damping element (300) A mass (308) having a main body (310) and a member (312) extending from the main body (310), A casing (306) enclosing the aforementioned mass (308), A fluid chamber (309) is defined between the mass (308) and the casing (306) and is filled with fluid, The first fluid portion (318) of the fluid chamber (309) includes a first accumulator portion (324) positioned between the first side surface (320) of the mass (308) and the casing (306), and extending along the member (312), The first accumulator portion (324) includes a second fluid portion (328) which is in fluid-related communication with the second accumulator portion (334), and is positioned between the second side surface (330) of the mass (308) and the casing (306) and extends along the member (312), and the first accumulator portion (324) includes a second fluid portion (328) which is in fluid-related communication with the second accumulator portion (334), A primary passage (362) extending between the first fluid portion (318) and the second fluid portion (328) Equipped with, The rotor blade (50) is a corrugated annular member (312) surrounding the main body (310) of the mass (308) such that the mass (308) defines a circular cross-section.

9. The rotor blade (50) according to claim 7, wherein the primary passage (362) extends along the axial centerline of the vibration damping element (300).

10. Multiple secondary passages (364) are arranged with spaces between them in the circumferential direction. Furthermore, The rotor blade (50) according to claim 7, wherein each of the plurality of secondary passages (364) extends through the member (312) from the first accumulator portion (324) to the second accumulator portion (334).

11. The rotor blade (50) according to claim 7, wherein the mass (308) is suspended in the fluid by the first bellows tube (358) and the second bellows tube (360).

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