Acoustic damping device

Abstract

Systems, devices, articles, and methods for acoustic damping devices are disclosed herein. An example device includes a first channel defining a first volume, the first channel open at a first end and closed at a second end; a second channel surrounding the first channel and defining a second volume; and a plurality of disks oriented within the first channel, individual disks of the plurality of disks including an opening at a center of the individual disk to allow at least one of a fluid or an acoustic oscillation to move from the first end to the second end; the first channel including a plurality of holes dispersed along an outer wall of the first channel and positioned between the plurality of disks, the holes facilitating a transfer of the at least one of the fluid or the acoustic oscillation from the first channel to the second channel.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to acoustic damping, and more particularly to acoustic damping devices for gas turbine engines. BACKGROUND

[0002] Aircraft engines, automobile engines, electric generators, and the like can produce vibrations during operation. Vibration producing devices can include additional hardware structures to dissipate resonance frequencies caused by the vibrations, as such frequencies can damage the vibration producing devices. BRIEF DESCRIPTION OF DRAWINGS

[0003] Figure 1 is a cross-sectional view of an example gas turbine engine in which examples disclosed herein can be implemented.

[0004] Figure 2 is a partial cross-sectional view of a first example acoustic damping device.

[0005] Figure 3 is a partial cross-sectional view of a second example acoustic damping device.

[0006] Figure 4 is a cross-sectional view of a third example acoustic damping device.

[0007] Figure 5 is a schematic view of an example fuel manifold that can be implemented on the example gas turbine engine of Figure 1 uses any of the example acoustic damping devices of Figures 2-4 .

[0008] Figures 6A-6C shows a schematic view of an example placement of the example acoustic damping devices of Figures 2-4 on the example fuel manifold of Figure 5 .

[0009] Figure 7 is a cross-sectional view of an example combustion section of the example gas turbine engine of Figure 1 utilizing the example acoustic damping devices of any of Figures 2-4 .

[0010] Figure 8 is an example quarter-wave tube combustion section that can be implemented on the example gas turbine engine of Figure 1 .

[0011] Figure 9 is a first example arrangement of the acoustic damping devices of Figures 2-4 in the example quarter-wave tube combustion section of Figure 8 .

[0012] Figure 10 is a second example arrangement of the acoustic damping devices of Figures 2-4acoustic damping device of Figure 8 a second example arrangement in an example quarter-wave tube combustion section.

[0013] Figure 11 an example cooling flow arrangement for the acoustic damping device of Figure 10 a second example arrangement of Figures 2-4 an example cooling flow arrangement for the acoustic damping device of DETAILED DESCRIPTION

[0014] Generally, the same reference numbers will be used throughout the drawings and accompanying written description to refer to the same or like parts. Unless otherwise indicated, the drawings are not necessarily drawn to scale. Rather, the dimensions of the various layers and regions can be expanded or reduced for the purposes of this disclosure. Although the layers and regions are shown with clear lines and boundaries in the drawings, some or all of these lines and / or boundaries can be idealized. In reality, the boundaries and / or lines can be unobservable, blended, and / or irregular.

[0015] "Comprising" and "including" (and all forms and tenses thereof) are used herein as open-ended terms. Therefore, whenever a claim uses any form of "comprising" or "including" (e.g., including, comprising, having, etc.) in the preamble or in any type of claim statement, it should be understood that other elements, terms, etc., may be present without exceeding the scope of the corresponding claim or statement. As used herein, the phrase "at least" is open-ended when used as a transition word in, for example, the preamble of a claim, just as the terms "comprising" and "including" are open-ended. The term "and / or," when used in the form of, for example, A, B, and / or C, refers to any combination or subset of A, B, and C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, or (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to an implementation that includes any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to an implementation that includes any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, etc., the phrase "at least one of A and B" is intended to refer to an implementation that includes any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, etc., the phrase "at least one of A or B" is intended to refer to an implementation that includes any one of (1) at least one A, (2) at least one B, or (3) at least one A and at least one B.

[0016] As used herein, singular references (e.g., "a," "an," "first," "second," etc.) do not exclude plurals. As used herein, the term "a" or "an" refers to one or more of those objects. The terms "a" (or "an"), "one or more," and "at least one" are used interchangeably herein. Furthermore, although listed separately, multiple means, elements, or actions may be implemented by, for example, the same entity or object. Moreover, although individual features may be included in different examples or claims, these features may be combined, and inclusion in different examples or claims does not imply that the combination of features is not feasible and / or disadvantageous.

[0017] As used herein, the term“above” describes a relative position of two portions with respect to the Earth. A first portion is above a second portion if at least one portion of the second portion is between the Earth and the first portion. Likewise, as used herein, a first portion is“below” a second portion when the first portion is closer to the Earth than the second portion. As described above, a first portion can be above or below a second portion with one or more of: intervening portions therebetween, no intervening portions therebetween, the first and second portions in contact, or the first and second portions not in direct contact with one another.

[0018] As used herein, a connection reference (e.g., attached, coupled, connected, and joined) can include intervening members between the elements referenced by the connection reference and / or relative movement between such elements, unless otherwise specified. Thus, a connection reference does not necessarily imply that two elements are directly connected and / or in physical contact with one another. As used herein, a statement that a portion is“contacted” by another portion defines a first portion that is in physical contact with a second portion.

[0019] Unless specifically stated otherwise, descriptors used herein, such as“first,”“second,”“third,” etc., do not confer or otherwise imply priority, physical order, a listing order, and / or any meaning in any manner whatsoever, but are merely used as labels and / or arbitrary names to distinguish elements so as to facilitate an understanding of the disclosed examples. In some examples, a descriptor“first” can be used to refer to an element in the detailed description, while in the claims, the same element can be referred to with a different descriptor, such as“second” or“third.” In such cases, it is to be understood that the descriptors are used only to clearly identify the elements in the context of the discussion, e.g., in the claims, where the elements can, for example, share the same name.

[0020] Turbine engines are one of the most widely used power generation technologies, commonly used in aircraft and power generation applications, among others. Turbine engines generally include a fan located forward of a core that includes, in flow series, a compressor section (e.g., including one or more compressors), a combustion section, a turbine section (e.g., including one or more turbines), and an exhaust section. Turbine engines can take any number of different configurations. For example, turbine engines can include one or more compressors and turbines, single or multiple spools, ducted or unducted fans, gear reduction architectures, etc. In some examples, the fan and low pressure compressor are on a common shaft with the low pressure turbine, while the high pressure compressor is on a common shaft with the high pressure turbine.

[0021] During operation, the fan's rotating blades draw air into the turbine engine and propel the air downstream. At least a portion of the air enters the core, where it is compressed by the compressor's rotating blades, mixed with fuel, and ignited, producing a high-temperature, high-pressure gas stream (e.g., hot combustion gases), which is then delivered to the turbine section. The hot combustion gases expand as they flow through the turbine section, causing the turbine's rotating blades to spin. Each of these processes generates vibrations within the turbine engine, which are transmitted to the fuel flowing through the turbine engine and / or cause pressure fluctuations, leading to instability in fuel flow and / or acoustic oscillations within the turbine engine's combustion chamber.

[0022] Vibrations are also generated in platforms such as automobile engines and generators due to the operation of these platforms (e.g., by igniting fuel, rotating electric motors, etc.). Although the examples disclosed herein are directed to aircraft turbine engine platforms, the examples disclosed herein can be used to replace platforms to eliminate flow fluctuations and acoustic oscillations caused by any vibration-generating device.

[0023] This document discloses an acoustic damping device that dampens / eliminates flow instabilities and / or acoustic oscillations generated by vibration-generating devices (e.g., turbine engines, fuel manifolds, etc.). The acoustic damping device disclosed herein absorbs the generated flow instabilities and / or acoustic oscillations and dissipates them within the structure of the acoustic damping device to reduce / eliminate the impact of these flow instabilities and / or acoustic oscillations on the operability of components / devices. The structure / size and / or customization of the acoustic damping device disclosed herein are tailored to the wavelength frequency to dissipate or eliminate flow instabilities and / or acoustic oscillations (e.g., referred to as an acoustic black hole).

[0024] Figure 1 This is a schematic cross-sectional view of an exemplary high-bypass turbofan gas turbine engine 100. Although the example shown is a high-bypass turbofan engine, the principles of this disclosure are also applicable to other types of engines, such as low-bypass turbofan engines, turbojet engines, turboprop engines, etc. Figure 1 As shown, the turbine engine 100 defines a longitudinal or axial centerline axis 102 extending through it, for reference. Figure 1 It also includes annotated direction diagrams for the axial direction A, radial direction R, and circumferential direction C. Generally, as used herein, the axial direction A is a direction extending approximately parallel to the centerline axis 102, the radial direction R is a direction extending orthogonally outward from the centerline axis 102, and the circumferential direction C is a direction extending concentrically around the centerline axis 102.

[0025] Typically, the turbocharger engine 100 includes a core turbine 104 located downstream of a fan (e.g., a fan section) 106. The core turbine 104 includes a generally tubular housing 108 defining an annular inlet 110. The housing 108 may be formed by a single housing or multiple housings. The housing 108 surrounds a compressor section having a supercharger or low-pressure compressor 112 (“LP compressor 112”) and a high-pressure compressor 114 (“HP compressor 114”) in a series flow relationship; a combustion section 116; a turbine section having a high-pressure turbine 118 (“HP turbine 118”) and a low-pressure turbine 120 (“LP turbine 120”); and an exhaust section 122.

[0026] like Figure 1 As shown, fan 106 includes a plurality of fan blades 132 connected to and extending radially outward from a centerline axis 102. A nacelle 134 (also referred to as an annular fan housing 134) circumferentially surrounds at least a portion of fan 106 and / or core turbine 104. Nacelle 134 may be supported relative to core turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. Furthermore, a downstream section 138 of nacelle 134 may surround an outer portion of core turbine 104 to define a bypass airflow passage 140 therebetween.

[0027] like Figure 1 As shown, air 142 enters its inlet portion 144 during operation of the turbine engine 100. A first portion 146 of the air 142 flows into a bypass airflow passage 140, while a second portion 148 of the air 142 flows into the inlet 110 of the LP compressor 112. One or more successive stages of the LP compressor stator blades 150 and LP compressor rotor blades 152 progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 and toward the HP compressor 114. Next, one or more successive stages of the HP compressor stator blades 154 and HP compressor rotor blades 156 further compress the second portion 148 of the air 142 flowing through the HP compressor 114. This provides compressed air 158 to the combustion section 116, where the compressed air 158 is mixed with fuel and burned to provide combustion gases 160.

[0028] Like the gas turbine engine 100, the core turbine 104 plays a similar role and is exposed to a similar environment in land-based gas turbine engines, turbojet engines (where the ratio of the first portion 146 of air 142 to the second portion 148 of air 142 is less than that in turbofan engines), and ductless fan engines (where the fan 106 has no nacelle 134). In each of the turbofan engine, turbojet engine, and ductless engine, a reduction gear (e.g., reduction gear 130) may be included between any shaft and spool.

[0029] Figure 1 Operation of the turbine engine 100 in the Figure 1 vibration during operation of the turbine engine 100, and the preceding examples are merely provided to place the disclosed systems, devices, articles of manufacture, and methods in an example environment.

[0030] In some examples, the acoustic damping device is disposed within a fuel manifold of the gas turbine engine 100. In some examples, the acoustic damping device is disposed within the combustion section 116 of the gas turbine engine 100. In other examples, the acoustic damping device is disposed anywhere that acoustic vibrations can be generated that can be damped, such as within the LP compressor 112, the HP compressor 114, the exhaust section 122, the bypass airflow passage 140, etc. Figure 1

[0031] Figure 2 is a partial cross-sectional view of a first example acoustic damping device 200. The first example acoustic damping device 200 includes a centerline 202, a first passage 204, and a second passage 206. In Figure 2 In examples, the first passage 204 corresponds to a first volume 207. The first volume 207 is defined by the first passage wall 208, which extends circumferentially around the centerline 202 in a cylindrical orientation, less any internal structure. The first passage wall 208 is also referred to herein as an outer wall of the first passage 204.

[0032] The second passage 206 surrounds the first passage 204 and corresponds to a second volume 209. In some examples, the second passage 206 is adjacent to the first passage 204. The second passage 206 includes a second passage inner wall 210 and a second passage outer wall 212. As Figure 2 ​As shown in the examples, the second channel inner wall 210 and the first channel wall 204 represent opposite sides of a single wall structure. The distance between the first channel wall 204 and the second channel inner wall 210 represents the thickness of the wall structure. The second volume 209 is defined by the volume between the second channel inner wall 210 and the second channel outer wall 212 minus any internal structure within the second channel 206. In some examples, the distance between the second channel inner wall 210 and the second channel outer wall 212 is 0.36 inches, with a tolerance of 0.05 inches. Furthermore, in some examples, the length of the second channel 206 is equal to 1.2 inches, with a tolerance of 0.05 inches. In some examples, the length of the first channel 204 is shorter than the length of the second channel 206. In the examples disclosed herein, the second channel 206 is separated from the first channel 204 by the distance between the first channel wall 208 and the second channel inner wall 210 (e.g., the thickness of the wall structure).

[0033] In some examples, the first volume 207 is larger than the second volume 209. In some examples, the dimensions of the first plurality of disks 218, the corresponding first channel 204 and the second channel 206 are determined according to a volume ratio to achieve a desired response to generated vibrations. The volume ratio is defined as the relationship between the second volume 209 and the first volume 207. In the examples disclosed herein, the volume ratio ranges from 0.1 to 1.0, representing the ratio of the second volume 209 to the first volume 207. More generally, the lengths of the first channel 204 and / or the second channel 206 can be expressed as a function of the radius of the disk 218. In the examples disclosed herein, the lengths of the first channel 204 and / or the second channel 206 are any values ​​between 10 times and 50 times the radius of the disk 218.

[0034] The volume ratio is determined for certain frequencies and pressures experienced within the first example acoustic damping device 200. In some examples, a higher volume ratio (e.g., close to 1.0) results in lower frequency dissipation / cancellation. Similarly, a lower volume ratio (e.g., close to 0.1) results in higher frequency dissipation / cancellation.

[0035] like Figure 2 As shown, the first channel 204 includes a first end 214 and a second end 216. During operation, when... Figure 1 When implemented with the example gas turbine engine 100, fuel or acoustic oscillations enter the first example acoustic damping device 200 through the first end 214. The fuel / acoustic oscillations travel through the first channel 204 to the second end 216. In the example disclosed herein, the second end 216 is closed (e.g., sealed), and the fuel / acoustic oscillations do not leave the first example acoustic damping device 200 through the second end 216.

[0036] exist Figure 2In the example, the first plurality of disks 218 are oriented within the first channel 204. Figure 2 In the example, nine disks 218 are shown. However, it should be understood that more or fewer disks 218 may be present. The disks 218 extend from the second end 216 of the first channel 204 to the first end 214 of the first channel 204. Figure 2 In the example, disk 218 is washer-shaped (e.g., circular) and includes an opening 220 centered on and extending radially outward from centerline 202 toward disk 218. As described above, the first volume 207 is defined by the volume of the first channel 204 minus any internal structure. Therefore, the first volume 207 is the volume of the first channel 204 minus the volume occupied by disk 218.

[0037] like Figure 2 As shown, disk 218 is funnel-shaped from the first end 214 toward the second end 216. For example, the first disk 222 includes a first outer edge 224 and a first inner edge 226. In the example disclosed herein, the first outer edge 224 is flush / aligned / connected to the first channel wall 208. The first disk 222 has a first radius 228 from the centerline 202 to the first outer edge 224 and a second radius 230 from the centerline 202 to the first inner edge 226. In some examples, the dimensions of the first radius 228 and the second radius 230 are determined according to the position and configuration of the acoustic damping device 200 (e.g., turbine engine 100, internal combustion engine, etc.). In the example disclosed herein, the first radius 228 and the second radius 230 can be expressed as the ratio of the second radius 230 to the first radius 228. For example, the ratio of the second radius 230 to the first radius 228 can be from 0.04 to 0.97. In some examples, the first radius 228 is 0.5 inches and the second radius 230 is 0.43 inches, with a tolerance range of 0.05 inches.

[0038] In addition, Figure 2In the example of FIG. 2, the second disk 232 includes a second disk outer edge 234 and a second disk inner edge 236. In examples disclosed herein, the second disk outer edge 234 is flush / aligned / connected with the first passage wall 208. The second disk 232 has a third radius 238 equal to the first radius 228, corresponding to the distance from the centerline 202 to the second disk outer edge 234 (e.g., 0.5 inches). The second disk 232 has a fourth radius 240 from the centerline 202 to the second disk inner edge 236. Similar to the first disk 222 described above, the third radius 238 and the fourth radius 240 of the second disk 232 can be expressed as a ratio of the fourth radius 240 to the third radius 238. For example, the ratio of the fourth radius 240 to the third radius 238 can be 0.04 to 0.97. In some examples, the fourth radius 240 is equal to 0.33 inches with a tolerance range of 0.05 inches. In other examples, the size of the fourth radius 240 is determined according to the location and configuration of the acoustic damping device 200. In some examples, the inner radius of the disk 218 decreases linearly toward the second end 216. In other examples, the inner radius varies exponentially, as a quadratic function, etc.

[0039] In examples disclosed herein, the size of the disk 218 corresponds to the operating conditions experienced by the first example acoustic damping device 200. For example, the acoustic oscillations vary according to the environmental conditions, performance, and / or flight phase of the gas turbine engine 100. Such examples include higher operating speeds of the gas turbine engine 100, higher operating temperatures (e.g., low altitude flight, hot or cold weather, high pressure / disturbance stormy weather, etc.), cruise, takeoff, climb, etc. In operation, as the fluid / acoustic oscillations enter the first end 214 and travel to the second end 216, the disk 218 dissipates / eliminates the resulting oscillations by the size and spacing of the disk 218 within the first passage 204. In some examples, the size of the second radius 230 and the fourth radius 240 are determined according to a mathematical relationship, such as a linear function, a logarithmic function, a parabolic / powder law function, etc.

[0040] To further dissipate / eliminate these oscillations, a plurality of holes 242 are arranged within the first passage 204 along the first passage wall 208 and between the disks 218. The plurality of holes 242 allow the fluid / acoustic oscillations to pass between the first passage 204 and the second passage 206. In some examples, the holes 242 are circular in shape with a diameter size determined based on the location and configuration of the acoustic damping device 200 (e.g., in the turbine engine 100). For example, the diameter size of the holes 242 is determined based on the spacing between the disks 218. In some examples, the spacing between the disks 218 can be expressed as a percentage of the first radius 228. In such examples, the spacing between the disks 218 can be 10% of the first radius 228 to 120% of the first radius 228. Accordingly, the diameter size of the holes 242 is fit within the distance between the disks 218. In some examples, the plurality of holes 242 are 0.02 inches in diameter.

[0041] In operation, by providing additional volume that allows the oscillations to dissipate, the efficiency of dissipating / eliminating the acoustic oscillations is improved by allowing the fluid / acoustic oscillations to pass between the passages 204, 206. For example, if the second passage 206 did not exist, the efficiency of the acoustic damping device 200 in reducing the amplitude of the acoustic oscillations can be 60%. Adding the second passage 206 can improve the efficiency to, for example, 90% because of the additional volume where the acoustic oscillations can dissipate.

[0042] Figure 3 is a partial cross-sectional view of a second example acoustic damping device 300. The second example acoustic damping device 300 includes all of the components described in connection with Figure 2 the first example acoustic damping device 200 and operates using the same physical processes. However, as Figure 3 shown, the second example acoustic damping device 300 includes a second plurality of disks 302 oriented within the second passage 206. As described above, the second volume 209 is defined by the volume of the second passage 206 minus any internal structures. Accordingly, Figure 3 the second volume 209 of the second example is the volume of the second passage 206 minus the volume occupied by the second disks 302.

[0043] In Figure 3 the example, the second disks 302 are in the shape of a washer and include a second opening 304 that is larger than the opening 220 of Figure 2 the first example. The second opening 304 is located on the centerline 202, just like the opening 220 of Figure 2 the first example is aligned with the centerline 202 and extends radially outward from the centerline 202 to the second disk 302. Figure 3 the second disk 302 of the second example is larger than the disk 218 of Figure 2 the first example.

[0044] Each of the second disks 302 includes an outer edge 306 and an inner edge 308. In Figure 3 In examples, the outer edge 306 of the second disks 302 is flush / aligned / connected with the second channel outer wall 212. The second disks 302 have a fifth radius 310 from the centerline 202 to the outer edge 306 of the second disks 302 and a sixth radius 312 from the centerline 202 to the inner edge 308 of the second disks 302. In examples disclosed herein, the fifth radius 310 and the sixth radius 312 can be expressed as a ratio of the fifth radius 310 and the sixth radius 312. For example, the ratio of the fifth radius 310 and the sixth radius 312 can be 0.04 to 0.97. In some examples, the fifth radius 310 is 0.88 inches. In other examples, the size of the fifth radius 310 is determined according to the location and configuration of the acoustic damping device 300. In some examples, the sixth radius 312 is equal to 0.7 inches, allowing for a gap between the inner edge 308 and the second channel inner wall 210.

[0045] Inclusion of the second disks 302 in the second channel 206 allows for more fine-tuned adjustment of the dissipation / cancellation response of the second example acoustic damping device 300. For example, increasing the number of disks (disks 218 or second disks 302) can increase control over the frequencies to be dissipated / cancelled as the surface available to capture these oscillations is increased. As described above, the number of disks 218, 302 and the individual dimensions of the disks 218, 302 can be modified as appropriate to adjust the vibrational response accordingly. For example, increasing the number of disks 218, 302 increases the frequency range that can be covered (e.g., increasing the maximum frequency from 1,000 Hz to 2,000 Hz or decreasing the minimum frequency from 500 Hz to 100 Hz) and provides efficiency in damping the acoustic oscillations (e.g., increasing the efficiency from 60% to 70% or more). Increasing the size of the disks 218, 302 naturally increases the volume of the acoustic damping device 200, 300, covering a lower frequency range as described above. Decreasing the size of the disks 218, 302 provides a lower volume, covering a higher frequency range. Thus, the number of disks 218, 302 and the size of the disks 218, 302 can be varied according to the frequency range desired to be dissipated / cancelled and according to the size desired for the acoustic damping device 200, 300.

[0046] Although Figure 3 While examples of the second disks 302 show each of the second disks 302 to be identical in size and shape, it should be understood that the second disks 302 can be similar in size and shape to the disks 218 (e.g., presenting a funnel shape). Thus, examples disclosed herein are not limited solely to the examples shown and can include combinations of the components disclosed herein.

[0047] Figure 4This is a cross-sectional view of the third example acoustic damping device 400. The third example acoustic damping device 400 includes a combination of... Figure 2 The first example acoustic damping device 200 describes all its components and operates using the same physical process. However, as Figure 4 As shown, the third example acoustic damping device 400 has a different shape and size.

[0048] like Figure 4 As shown, the first radius 228 of the first plate 222 is not equal to the third radius 238 of the second plate 232. Figure 4 In the example, the second radius 230 of the first tray 222 is equal to the fourth radius 240 of the second tray 232 (e.g., 0.06 inches), and the third radius 238 is larger than the first radius 228 (e.g., the third radius 238 equals 0.33 inches, and the first radius 228 equals 0.1 inches). This example reflects an inverted funnel shape, where the first channel 204 increases in size as it approaches the second end 216. Unlike the first channel 204, Figure 4 In the example, the second channel 206 is smaller the closer it is to the second end 216.

[0049] As described above, the size and shape of disks 218 and 302 are determined based on the desired response to the experienced vibration frequencies (e.g., any frequency between 100 Hz and 4,000 Hz). At the lower end of the experienced frequency range (e.g., 100–1,000 Hz), disks 218 and 302 are smaller than those that can handle higher frequency ranges (e.g., 1,000–2,000 Hz). For example, to increase the volume ratio for handling lower frequency ranges (e.g., combined with… Figure 2 As disclosed, disk 218 has a smaller radius to reduce the first volume 207 corresponding to the first channel 204. Alternatively, in order to reduce the volume ratio to handle a higher frequency range, disk 218 has a larger radius to increase the first volume 207 corresponding to the first channel 204. Figure 4 The example provides an alternative arrangement of disk 218, which can be used interchangeably with any of the examples provided in this article.

[0050] In some examples, Figures 2-4 The acoustic damping devices 200, 300, and 400 are made of metallic materials, such as aluminum, steel, and titanium. It is worth noting that the placement of the acoustic damping devices 200, 300, and 400 within the gas turbine engine 100 may alter the materials used in their manufacture. For example, if the acoustic damping devices 200, 300, and 400 are located at the rear of the combustion section 116, the material could be titanium to withstand the heat generated by fuel ignition. Alternatively, cooling methods can be implemented to protect the acoustic damping devices 200, 300, and 400 (see below). Figure 11In other cases where excessive heat is not generated, the acoustic damping devices 200, 300, and 400 can be made of cheaper materials, such as aluminum or steel. In some examples, weight is an important consideration, and lighter materials (such as aluminum) are used to reduce the weight distribution of the acoustic damping devices 200, 300, and 400.

[0051] Figure 5 It can be used as Figure 1 A schematic diagram of an example fuel manifold 500 implemented as a part of an example gas turbine engine 100, which uses Figures 2-4 Any example acoustic damping device 200, 300, 400. Example fuel manifold 500 includes fuel line 502 for delivering fuel from a fuel tank (not shown) to fuel nozzle 504. Fuel nozzle 504 deposits fuel into combustion section 116 to ignite the fuel, as in combination. Figure 1 As disclosed above, operation of the gas turbine engine 100 may cause instability in the flow of fuel delivered through the fuel line 502, thereby affecting the operation of the fuel manifold 500 (e.g., reduced efficiency in fuel delivery, damage to the fuel line 502, etc.). In the example environment (e.g., example gas turbine engine 100), multiple fuel lines 502 may be used independently of each other.

[0052] Example fuel manifold 500 includes a fuel line connector 506 for connecting a siphon 508 to a fuel nozzle 504. The siphon 508 delivers an appropriate amount of fuel from the fuel line 502 to the fuel nozzle 504. The fuel line connector 506 allows partial fuel supply to the siphon 508 while allowing the remaining fuel to continue through the fuel line 502. In some examples, the siphon 508 is also referred to as a "tailpipe".

[0053] exist Figure 5 In one example, the sample fuel manifold 500 includes a tubular damping device 510 oriented along the fuel line 502 and the siphon 508 to suppress oscillations caused by flowing fuel. In some examples, the tubular damping device 510 utilizes existing damping techniques to suppress flow instabilities within the fuel line caused by the operation of the gas turbine engine 100.

[0054] like Figure 5The example acoustic damping devices 200, 300, 400 are oriented at the end of the fuel line 502. In the examples disclosed herein, the fuel line 502 is pressurized to facilitate movement of fuel through the fuel line 502. Accordingly, the acoustic damping devices 200, 300, 400 are oriented at the end of the fuel line 502 where the pressure is greatest due to stagnation of the fuel flow. At the same location, the flow instability is also greatest due to the same stagnation of the fuel flow. Accordingly, in accordance with the details disclosed herein, including the acoustic damping devices 200, 300, 400 at the end of the fuel line 502 can provide improved damping characteristics and flow instability elimination.

[0055] Figures 6A-6C An example acoustic damping device 200, 300, 400 is shown in Figures 2-4 An example schematic of an alternative example placement of the example acoustic damping devices 200, 300, 400 on the example fuel manifold 500 in Figure 5 In the example of Figures 6A-6C The acoustic damping devices 200, 300, 400 are oriented along the fuel line 502 of the example fuel manifold 500. As indicated by the arrow in Figures 6A-6C Fuel flows in one direction through the fuel line 502 as indicated by the arrow in

[0056] Figure 6A A T-junction orientation 600 is shown. Figure 6A The example of The acoustic damping devices 200, 300, 400 are oriented at a 90 degree angle relative to the fuel flow through the fuel line 502. The T-junction orientation 600 allows the fuel (or any oscillations generated) to enter the acoustic damping devices 200, 300, 400 and dissipate the vibrations / reduce pressure build-up before releasing the fuel back into the fuel line 502 to continue on to the fuel nozzle 504.

[0057] Figure 6B An acute angle orientation 602 is shown. Figure 6B The example of The acoustic damping devices 200, 300, 400 are oriented at an angle less than 90 degrees relative to the fuel flow through the fuel line 502. Similarly, the fuel can enter the acoustic damping devices 200, 300, 400 at the acute angle orientation 602 to dissipate / eliminate flow instability.

[0058] Figure 6C An obtuse angle orientation 604 is shown. Figure 6C The example of The acoustic damping devices 200, 300, 400 are oriented at an angle greater than 90 degrees relative to the fuel flow through the fuel line 502.

[0059] Figure 6AExamples of -C are intended to illustrate potential orientations of the acoustic dampening devices 200, 300, 400 on the example fuel manifold 500 due to size constraints in any given environment. For example, if the fuel manifold 500 is to be installed within a smaller footprint, the T-junction orientation 600 can not meet the size constraints. Accordingly, the acute orientation 602 or the obtuse orientation 604 can be used to accommodate the smaller footprint.

[0060] In some examples, the example acoustic dampening devices 200, 300, 400 are oriented to combine the teachings disclosed herein with a Helmholtz resonator along a fuel line, exhaust line, etc. In such examples, the example acoustic dampening devices 200, 300, 400 provide structural improvements to dissipate / eliminate flow instabilities as well as acoustic oscillations while providing improved noise reduction corresponding to the Helmholtz resonator.

[0061] Figure 7 is Figure 1 a cross-sectional view of an example combustion section 116 of an example gas turbine engine 100 in Figures 2-4 the example acoustic dampening devices 200, 300, 400. In Figure 7 examples, the fuel nozzles 504 deposit fuel into the combustion chamber 700. The igniters 702 ignite the fuel, ultimately producing thrust as described above.

[0062] When the fuel is ignited, vibrations are produced due to the chemical reactions that ignite the fuel. These vibrations (e.g., acoustic oscillations) propagate throughout the combustion section 116 and the rest of the gas turbine engine 100. Notably, the oscillations propagate upstream, forward of the fuel nozzles 504, and can impact surrounding structures.

[0063] In Figure 7 examples, one or more acoustic dampening devices 200, 300, 400 are disposed forward of the fuel nozzles 504 to dissipate / eliminate these oscillations that are produced. In some examples, the number of acoustic dampening devices 200, 300, 400 disposed in the combustion section 116 is determined based on the size of the combustion section 116. In other examples, the number of acoustic dampening devices 200, 300, 400 is fixed (e.g., one per fuel nozzle 504, one every other fuel nozzle 504, etc.). In some examples, the acoustic dampening devices 200, 300, 400 can be placed circumferentially around the gas turbine engine 100 based on the combustion section 116 (e.g., by a circumferential combustion section). Although Figure 7 examples show two of the acoustic dampening devices 200, 300, 400, only one or more than two can be used accordingly.

[0064] Figure 8 is available inFigure 1 An example quarter wave tube combustion section 800 implemented on an example gas turbine engine 100 of

[0065] Figure 9 is Figures 2-4 The acoustic damping device 200, 300, 400 of Figure 8 A first example arrangement 900 in the example quarter wave tube combustion section 800 of Figure 9 An example shows Figure 8 A cross section of one of the combustion sections 802 of including a quarter wave tube 804. As Figure 7 The example quarter wave tube combustion section 800 of

[0066] As shown in the example quarter wave tube combustion section 800 of Figure 9 The acoustic damping device 200, 300, 400 is disposed within the quarter wave tube 804 forward of the combustion chamber 700 to dampen the generated oscillations. In some examples, the quarter wave tube 804 is omitted and only the acoustic damping device 200, 300, 400 is implemented to dampen the oscillations. Such an arrangement can be desirable when replacing the combustion section 116, 800 is difficult, time consuming, expensive, etc. and inserting the acoustic damping device 200, 300, 400 within the existing structure can improve performance. This approach also reduces / eliminates the need to redesign the existing platform to accommodate the performance improvement.

[0067] Figure 10 is Figures 2-4 The acoustic damping device 200, 300, 400 in the example quarter wave tube combustion section 800 of Figure 8 A second example arrangement 1000 in the example quarter wave tube combustion section 800 of Figure 10 An example shows Figure 8 A cross section of one of the combustion sections 802 of including a quarter wave tube 804. As Figure 10 shown, the acoustic damping device 200, 300, 400 is disposed downstream (e.g., aft) of the ignition section 902 and adjacent to the combustion chamber 700.

[0068] Figure 10The second example arrangement 1000 dissipates / eliminates combustion zone 116 ( Figure 1 The vibration frequency on the hot side (e.g., after fuel ignition). Figure 10 The example allows for additional frequency response control corresponding to the oscillations generated by fuel ignition. The first device 900 and the second device 1000 can be used independently or in combination to achieve the desired oscillation dissipation (e.g., reducing overall vibration effects and / or improving the efficiency of damped acoustic oscillations).

[0069] During operation, the ignited fuel produces hot gases (e.g., exceeding 2,000 degrees Fahrenheit), which are then expelled from exhaust section 122. Figure 1 These hot gases can damage downstream components that are not made of materials capable of withstanding such temperatures. Figure 11 It shows according to Figure 10 The second example arrangement is an example cooling flow arrangement 1100 of acoustic damping devices 200, 300, and 400.

[0070] Therefore, the second arrangement 1000 can be configured to mix cold, unignited air with ignited gas to protect the acoustic damping devices 200, 300, and 400. Although Figure 11 The example shows a second example acoustic damping device 300, but it should be understood that... Figures 2-4 Any of the example acoustic damping devices 200, 300, 400 can be used here.

[0071] like Figure 11 As shown, cold, unburned air 1102 enters the second channel 206 through the second channel opening 1104. The cold air 1102 then enters the first channel 204 through multiple holes 242. Hot, ignited gas 1106 enters the first channel 204 through the first end 214. The cold air 1102 mixes with the hot gas 1106 in the first channel 204 (corresponding to arrow 1108) to produce a mixed gas 1110. The mixed gas 1110 consists of the hot gas 1106 cooled by the cold air 1102. The mixed gas 1110 then exits from the acoustic damping devices 200, 300, 400. This process of cooling the hot gas 1106 allows the acoustic damping devices 200, 300, 400 to operate in the ignition section 902 ( Figure 9 and 10 (The operation is performed afterward.)

[0072] As can be understood from the foregoing, example systems, devices, articles, and methods have been disclosed for using acoustic damping devices or acoustic black holes to dissipate and / or eliminate vibration frequencies, acoustic oscillations, and flow instabilities caused by vibration-generating devices. Failure to dissipate and / or eliminate vibration frequencies may result in damage to components within the environment. Such damage may lead to environmental inoperability and / or performance degradation.

[0073] Disclosed herein are example acoustic damping devices and related methods of use thereof. The subject matter of the following clauses provides further examples and combinations:

[0074] An acoustic damping device comprising: a first channel defining a first volume, the first channel open at a first end and closed at a second end; a second channel surrounding the first channel and defining a second volume; and a plurality of disks oriented within the first channel, each disk of the plurality of disks including an opening at a center of the each disk to allow at least one of a fluid or an acoustic vibration to move from the first end to the second end, the first channel including a plurality of holes dispersed along an outer wall of the first channel and positioned between the plurality of disks, the holes facilitating a transfer of the at least one of the fluid or the acoustic vibration from the first channel to the second channel.

[0075] The acoustic damping device of any preceding clause, wherein: a first disk of the plurality of disks on the first end of the first channel has a first radius from an outer edge of the first disk to the center and a second radius from an inner edge of the first disk to the center; and a second disk of the plurality of disks on the second end of the first channel has a third radius from an outer edge of the second disk to the center and a fourth radius from an inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0076] The acoustic damping device of any preceding clause, wherein the second radius is greater than the fourth radius.

[0077] The acoustic damping device of any preceding clause, wherein the second radius is less than the fourth radius.

[0078] The acoustic damping device of any preceding clause, wherein the plurality of disks is a first plurality of disks, the opening is a first opening, the center is a first center, and the acoustic damping device further comprises a second plurality of disks oriented within the second channel, each disk of the second plurality of disks including a second opening at a second center of the each disk, the first center aligned with the second center.

[0079] The acoustic damping device of any preceding clause, wherein: a first disk of the second plurality of disks on the first end of the second passage has a first radius from an outer edge of the first disk to the second center and a second radius from an edge of the second opening of the first disk to the second center; and a second disk of the second plurality of disks on the second end of the second passage has a third radius from an outer edge of the second disk to the second center and a fourth radius from an edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0080] The acoustic damping device of any preceding clause, wherein the second radius and the fourth radius are equal.

[0081] The acoustic damping device of any preceding clause, wherein the first volume is greater than the second volume.

[0082] The acoustic damping device of any preceding clause, wherein a volume ratio of the second volume to the first volume ranges from 0.1 to 1.0.

[0083] A turbine engine having a centerline axis, comprising: a nacelle; a combustion section surrounded by the nacelle, the combustion section including a combustion chamber located at a rear of the combustion section along the centerline axis; and an acoustic damping device within the combustion section, the acoustic damping device comprising: a first passage defining a first volume, the first passage open at a first end and closed at a second end; a second passage surrounding the first passage and defining a second volume; and a plurality of disks oriented within the first passage, each disk of the plurality of disks including an opening at a center of the each disk to allow acoustic vibrations to move from the first end to the second end, the first passage including a plurality of holes dispersed along an outer wall of the first passage and located between the plurality of disks, the holes facilitating the transfer of the acoustic vibrations from the first passage to the second passage.

[0084] The turbine engine of any preceding clause, wherein the acoustic damping device is located at a front of the combustion section along the centerline axis.

[0085] The turbine engine of any preceding clause, wherein the acoustic damping device is located at a rear of the combustion section along the centerline axis and adjacent to the combustion chamber.

[0086] The turbine engine of any preceding clause, further comprising a quarter wave tube located in at least one of the rear or the front of the combustion section, wherein the acoustic damping device is placed within the quarter wave tube of the combustion section.

[0087] The turbine engine according to any preceding clause, wherein a first disk of the plurality of disks on the first end of the first passage has a first radius from an outer edge of the first disk to the center and a second radius from an inner edge of the first disk to the center; and a second disk of the plurality of disks on the second end of the first passage has a third radius from an outer edge of the second disk to the center and a fourth radius from an inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0088] The turbine engine according to any preceding clause, wherein the second radius is greater than the fourth radius.

[0089] The turbine engine according to any preceding clause, wherein the second radius is less than the fourth radius.

[0090] The turbine engine according to any preceding clause, wherein the plurality of disks is a first plurality of disks, the opening is a first opening, the center is a first center, further comprising a second plurality of disks oriented within the second passage, each disk of the second plurality of disks including a second opening at a second center of the each disk, the first center aligned with the second center.

[0091] The turbine engine according to any preceding clause, wherein a first disk of the second plurality of disks on a first end of the second passage has a first radius from an outer edge of the first disk to the second center and a second radius from an edge of the second opening of the first disk to the second center; and a second disk of the second plurality of disks on a second end of the second passage has a third radius from an outer edge of the second disk to the second center and a fourth radius from an edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0092] The turbine engine according to any preceding clause, wherein the second radius and the fourth radius are equal.

[0093] The turbine engine according to any preceding clause, wherein the first volume is greater than the second volume.

[0094] The turbine engine according to any preceding clause, wherein a volume ratio of the second volume to the first volume ranges from 0.1 to 1.0.

[0095] A turbine engine comprising a nacelle; a combustion section within the nacelle; and a fuel manifold to deliver fuel from a fuel tank to the combustion section, the combustion section igniting the fuel, the fuel manifold comprising a fuel nozzle to deposit the fuel into the combustion section, a fuel line to deliver the fuel from the fuel tank to the fuel nozzle, and an acoustic damper coupled to a first portion of the fuel line, the acoustic damper comprising a first passage defining a first volume, the first passage open at a first end and closed at a second end; a second passage surrounding the first passage and defining a second volume, and a plurality of disks oriented within the first passage, individual disks of the plurality of disks comprising an opening at a center of the individual disk to allow fluid to move from the first end to the second end, the first passage comprising a plurality of holes dispersed along an outer wall of the first passage and between the plurality of disks, the holes to facilitate passing the fluid from the first passage to the second passage.

[0096] The turbine engine of any preceding paragraph, wherein the acoustic damper is a first acoustic damper, further comprising a second acoustic damper coupled to a second portion of the fuel line, the second portion different from the first portion.

[0097] The turbine engine of any preceding paragraph, wherein a first disk of the plurality of disks on the first end of the first passage has a first radius from an outer edge of the first disk to the center and a second radius from an inner edge of the first disk to the center, and a second disk of the plurality of disks on the second end of the first passage has a third radius from an outer edge of the second disk to the center and a fourth radius from an inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0098] The turbine engine of any preceding paragraph, wherein the second radius is greater than the fourth radius.

[0099] The turbine engine of any preceding paragraph, wherein the second radius is less than the fourth radius.

[0100] The turbine engine of any preceding paragraph, wherein the plurality of disks is a first plurality of disks, the opening is a first opening, the center is a first center, further comprising a second plurality of disks oriented within the second passage, individual disks of the second plurality of disks comprising a second opening at a second center of the individual disk, the first center aligned with the second center.

[0101] The turbine engine of any preceding paragraph, wherein a first disk of the second plurality of disks on the first end of the second passage has a first radius from an outer edge of the first disk to the second center and a second radius from an edge of the second opening of the first disk to the second center, and a second disk of the second plurality of disks on the second end of the second passage has a third radius from an outer edge of the second disk to the second center and a fourth radius from an edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0102] The turbine engine of any preceding paragraph, wherein the second radius and the fourth radius are equal.

[0103] The turbine engine of any preceding paragraph, wherein the first volume is greater than the second volume.

[0104] The turbine engine of any preceding paragraph, wherein a volume ratio of the second volume to the first volume is between 0.1 and 1.0.

[0105] The turbine engine of any preceding paragraph, wherein the acoustic damper device is oriented at a 90 degree angle relative to a direction of fuel flow in the fuel manifold.

[0106] The turbine engine of any preceding paragraph, wherein the acoustic damper device is oriented at an angle between 0 degrees and 90 degrees relative to a direction of fuel flow in the fuel manifold.

[0107] The turbine engine of any preceding paragraph, wherein the acoustic damper device is oriented at an angle between 90 degrees and 180 degrees relative to a direction of fuel flow in the fuel manifold.

[0108] The turbine engine of any preceding paragraph, wherein the acoustic damper device is positioned at a first end of the fuel line.

[0109] The following claims are incorporated into this detailed description by reference. Although certain example systems, devices, articles, and methods have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, devices, articles, and methods falling within the scope of the claims.

Claims

1. An acoustic damping device, characterized by, comprising: a first passage defining a first volume, the first passage being open at a first end and closed at a second end; a second passage surrounding the first passage and defining a second volume; and a plurality of disks oriented within the first passage, each disk of the plurality of disks including an opening at a center of the each disk to allow at least one of a fluid or an acoustic oscillation to move from the first end to the second end, the first passage including a plurality of holes dispersed along an outer wall of the first passage and positioned between the plurality of disks, the holes facilitating a transfer of the at least one of the fluid or the acoustic oscillation from the first passage to the second passage. wherein:

2. The acoustic damping device of claim 1, wherein, a first disk of the plurality of disks on the first end of the first passage has a first radius from an outer edge of the first disk to the center and a second radius from an inner edge of the first disk to the center; and a second disk of the plurality of disks on the second end of the first passage has a third radius from an outer edge of the second disk to the center and a fourth radius from an edge of the second opening of the second disk to the center, wherein the first radius is equal to or less than the third radius. wherein the second radius is greater than the fourth radius.

3. The acoustic damping device of claim 2, wherein, wherein the first radius is less than the third radius.

4. The acoustic damping device of claim 2, wherein, wherein the plurality of disks is a first plurality of disks, the opening is a first opening, the center is a first center, and the acoustic damping device further comprises a second plurality of disks oriented within the second passage, each disk of the second plurality of disks including a second opening at a second center of the each disk, the first center being aligned with the second center.

5. The acoustic damping device of claim 1, wherein, wherein:

6. The acoustic damping device of claim 5, wherein, a first disk of the second plurality of disks on a first end of the second passage has a first radius from an outer edge of the first disk to the second center and a second radius from an edge of the second opening of the first disk to the second center; and a second disk of the second plurality of disks on a second end of the second passage has a third radius from an outer edge of the second disk to the second center and a fourth radius from an edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal. wherein the second radius and the fourth radius are equal.

7. The acoustic damping device of claim 6, wherein, wherein the first volume is greater than the second volume.

8. The acoustic damping device of claim 1, wherein, wherein a volume ratio of the second volume to the first volume is greater than or equal to 0.1 and less than 1.

0.

9. The acoustic damping device of claim 8, wherein, The turbine engine comprises:

10. A turbine engine having a centerline axis, characterized by, a nacelle; a combustion section surrounded by the nacelle, the combustion section including a combustion chamber located within the combustion section along the centerline axis; and an acoustic damping device within the combustion section, the acoustic damping device comprising: a first passage defining a first volume, the first passage being open at a first end and closed at a second end; a second passage surrounding the first passage and defining a second volume; and ​ a plurality of disks oriented within the first channel, each disk of the plurality of disks including an opening at a center of the each disk to allow acoustic oscillations to move from the first end to the second end, the first channel including a plurality of holes dispersed along an outer wall of the first channel and located between the plurality of disks, the holes facilitating the transfer of the acoustic oscillations from the first channel to the second channel.

11. The turbine engine of claim 10, wherein, wherein the acoustic damping device is located at a front of the combustion section along the centerline axis.

12. The turbine engine of claim 10, wherein, wherein the acoustic damping device is located at a rear of the combustion section along the centerline axis and adjacent to the combustion chamber.

13. The turbine engine of claim 10, wherein, wherein: a first disk of the plurality of disks on the first end of the first channel has a first radius from an outer edge of the first disk to the center and a second radius from an inner edge of the first disk to the center; and a second disk of the plurality of disks on the second end of the first channel has a third radius from an outer edge of the second disk to the center and a fourth radius from an inner edge of the second disk to the center, wherein the first radius is equal to or less than the third radius.

14. The turbine engine of claim 13, wherein, wherein the second radius is greater than the fourth radius.

15. The turbine engine of claim 13, wherein, wherein the first radius is less than the third radius.

16. The turbine engine of claim 10, wherein, wherein the plurality of disks are a first plurality of disks, the opening is a first opening, the center is a first center, further comprising a second plurality of disks oriented within the second channel, each disk of the second plurality of disks including a second opening at a second center of the each disk, the first center aligned with the second center.

17. The turbine engine of claim 16, wherein, wherein: a first disk of the second plurality of disks on a first end of the second channel has a first radius from an outer edge of the first disk to the second center and a second radius from an edge of the second opening of the first disk to the second center; and a second disk of the second plurality of disks on a second end of the second channel has a third radius from an outer edge of the second disk to the second center and a fourth radius from an edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

18. The turbine engine of claim 17, wherein, wherein the second radius and the fourth radius are equal.

19. The turbine engine of claim 10, wherein, wherein the first volume is greater than the second volume.

20. The turbine engine of claim 19, wherein, wherein a volume ratio of the second volume to the first volume is greater than or equal to 0.1 and less than 1.0.

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