Acoustic damping device

Abstract

Systems, apparatuses, articles, and methods for acoustic damping devices are disclosed herein. An example apparatus includes: a first channel defining a first volume, the first channel being 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 in a center of each disk to allow at least one of fluid or acoustic oscillations to move from the first end to the second end; the first channel includes a plurality of apertures dispersed along an outer wall of the first channel and located between the plurality of discs, the apertures facilitating transfer of at least one of a fluid or acoustic oscillation from the first channel to the second channel.

Description

[0001] This application is a divisional application of the invention patent application filed on January 20, 2025, with application number 202510085200.X and invention title "Acoustic Damping Device". Technical Field

[0002] This disclosure relates generally to acoustic damping, and more specifically to acoustic damping devices for gas turbine engines. Background Technology

[0003] Aircraft engines, car engines, generators, and other similar devices generate vibrations during operation. Vibration generating devices may include additional hardware structures to dissipate resonant frequencies caused by vibrations, as these frequencies can damage the vibration generating device. Attached Figure Description

[0004] Figure 1 This is a cross-sectional view of an example gas turbine engine from which the examples disclosed herein can be implemented.

[0005] Figure 2 This is a partial cross-sectional view of the first example acoustic damping device.

[0006] Figure 3 This is a partial cross-sectional view of the second example acoustic damping device.

[0007] Figure 4 This is a cross-sectional view of the third example acoustic damping device.

[0008] Figure 5 It is possible Figure 1 A schematic diagram of an example fuel manifold implemented on an example gas turbine engine, which uses Figure 2-4 Any example acoustic damping device.

[0009] Figures 6A-6C It shows Figure 2-4 Example acoustic damping devices in Figure 5 A schematic diagram of an example placement on an example fuel manifold.

[0010] Figure 7 yes Figure 1 A cross-sectional view of an example combustion section of an example gas turbine engine, which utilizes... Figure 2-4 Examples of acoustic damping devices for any of them.

[0011] Figure 8 It is possible Figure 1 Example quarter-wave tube combustion section implemented on an example gas turbine engine.

[0012] Figure 9 yes Figure 2-4 Acoustic damping device in Figure 8 The first example arrangement in the example quarter-wave tube combustion section.

[0013] Figure 10 yes Figure 2-4 Acoustic damping device in Figure 8 The second example arrangement in the example quarter-wave tube combustion section.

[0014] Figure 11 It shows that according to Figure 10 The second example arrangement Figure 2-4 An example cooling flow arrangement of an acoustic damping device. Detailed Implementation

[0015] Generally, the same reference numerals will be used throughout the accompanying drawings and written description to refer to the same or similar parts. The drawings are not necessarily drawn to scale. Instead, the thickness of layers or regions may be magnified in the drawings. Although the drawings show layers and regions with sharp lines and boundaries, some or all of these lines and / or boundaries may be idealized. In reality, boundaries and / or lines may be unobservable, mixed, and / or irregular.

[0016] "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.

[0017] 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.

[0018] As used herein, unless otherwise stated, the term "above" describes the relationship of two parts relative to the Earth. The first part is above the second part if at least one portion of the second part lies between the Earth and the first part. Similarly, as used herein, the first part is "below" the second part when the first part is closer to the Earth than the second part. As stated above, the first part can be above or below the second part, and may have one or more of the following: there are other parts between them, there are no other parts between them, the first part and the second part are in contact, or the first part and the second part are not in direct contact with each other.

[0019] As used herein, a connection reference (e.g., attachment, coupling, connection, and engagement) may include intermediate components between elements referenced by the connection reference and / or relative movement between these elements, unless otherwise stated. Therefore, a connection reference does not necessarily mean that two elements are directly connected and / or fixed to each other. As used herein, the definition of any part being "in contact" with another part means that there is no intermediate portion between the two parts.

[0020] Unless otherwise expressly stated, descriptors used herein, such as “first,” “second,” “third,” etc., do not assign or otherwise indicate any meaning of priority, physical order, listing arrangement, and / or any sorting, but are merely used as labels and / or arbitrary names to distinguish elements for the purpose of understanding the disclosed examples. In some examples, the descriptor “first” may be used to refer to an element in the detailed description, while in the claims, the same element may be referred to by different descriptors, such as “second” or “third.” In such cases, it should be understood that these descriptors are only used to clearly identify these elements in the context of the discussion (e.g., in the claims), where these elements may, for example, share the same name.

[0021] Turbine engines are one of the most widely used power generation technologies, commonly used in aircraft and power generation applications. A turbine engine typically includes a fan located in front of a core, which, in flow order, comprises 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 employ any number of different configurations. For example, a turbine engine may include one or more compressors and turbines, single or multiple spools, ducted or non-ducted fans, geared structures, etc. In some examples, the fan and low-pressure compressor are located on the same shaft as the low-pressure turbine, while the high-pressure compressor and high-pressure turbine are located on the same shaft.

[0022] During operation, the fan's rotating blades draw air into the turbine engine and propel it 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.

[0023] 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.

[0024] 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).

[0025] 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.

[0026] 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 from 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.

[0027] 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 casing 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.

[0028] 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.

[0029] 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.

[0030] Figure 1 The operation of the turbine engine 100 can cause flow instabilities in the fuel line and / or acoustic oscillations due to pressure differences generated by the operation of the turbine engine 100. In some examples, the operation of the turbine engine 100 can cause the fuel flowing through the fuel line to vibrate. In some examples, fuel combustion in the combustion section 116 can generate acoustic oscillations due to the chemical reactions that ignite the fuel (e.g., pressure differences). It should be understood that many alternatives may result in... Figure 1 The turbine engine 100 generates vibrations during operation, and the preceding examples are only for providing background to place the disclosed systems, devices, articles of manufacture, and methods in an example setting.

[0031] In some examples, acoustic damping devices are set in Figure 1 The gas turbine engine 100 is located within its fuel manifold. In some examples, acoustic damping devices are disposed within the combustion section 116 of the gas turbine engine 100. In other examples, acoustic damping devices are disposed anywhere that generates dampable acoustic vibrations, such as within the LP compressor 112, HP compressor 114, exhaust section 122, bypass airflow passage 140, etc.

[0032] Figure 2 This 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 channel 204, and a second channel 206. Figure 2 In the example, the first channel 204 corresponds to the first volume 207. The first volume 207 is defined by the first channel wall 208 minus any internal structure, which extends circumferentially around the centerline 202 in a cylindrical orientation. The first channel wall 208 is also referred to herein as the outer wall of the first channel 204.

[0033] The second channel 206 surrounds the first channel 204 and corresponds to the second volume 209. In some examples, the second channel 206 is adjacent to the first channel 204. The second channel 206 includes an inner wall 210 and an outer wall 212. Figure 2As 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).

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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 disk outer edge 224 and a first disk inner edge 226. In the example disclosed herein, the first disk 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 disk outer edge 224 and a second radius 230 from the centerline 202 to the first disk 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.

[0039] In addition, Figure 2In the example, the second disc 232 includes an outer edge 234 and an inner edge 236. In the example disclosed herein, the outer edge 234 of the second disc is flush / aligned / connected to the first channel wall 208. The second disc 232 has a third radius 238, which is equal to the first radius 228, corresponding to the distance from the centerline 202 to the outer edge 234 of the second disc (e.g., 0.5 inches). The second disc 232 has a fourth radius 240 from the centerline 202 to the inner edge 236 of the second disc. Similar to the first disc 222 described above, the third radius 238 and the fourth radius 240 of the second disc 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 from 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 dimension of the fourth radius 240 is determined based on the location and configuration of the acoustic damping device 200. In some examples, the inner radius of disk 218 decreases linearly toward the second end 216. In other examples, the inner radius varies exponentially, quadratically, or otherwise.

[0040] In the examples disclosed herein, the dimensions of disk 218 correspond to the operating conditions experienced by the first example acoustic damping device 200. For example, acoustic oscillations vary depending on 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 / interference stormy weather, etc.), cruise, takeoff, climb, etc. During operation, as fluid / acoustic oscillations enter the first end 214 and proceed concurrently to the second end 216, disk 218 dissipates / eliminates the generated oscillations through the dimensions and spacing of disk 218 within the first channel 204. In some examples, the dimensions of the second radius 230 and the fourth radius 240 are determined according to mathematical relationships, such as linear functions, logarithmic functions, parabolic / power-law functions, etc.

[0041] To further dissipate / eliminate these oscillations, a plurality of holes 242 are arranged within the first channel 204 along the first channel wall 208 and between the disks 218. The plurality of holes 242 allow fluid / acoustic oscillations to propagate between the first channel 204 and the second channel 206. In some examples, the holes 242 are circular, and their diameter is determined based on the location and configuration of the acoustic damping device 200 (e.g., in a turbine engine 100). For example, the diameter of the holes 242 is determined based on the spacing between the disks 218. In some examples, the spacing between the disks 218 may be expressed as a percentage of a first radius 228. In such examples, the spacing between the disks 218 can be from 10% to 120% of the first radius 228. Therefore, the diameter of the holes 242 is fitted within the distance between the disks 218. In some examples, the diameter of the plurality of holes 242 is 0.02 inches.

[0042] In operation, by providing additional volume that allows oscillations to dissipate, the fluid / acoustic oscillations are allowed to propagate between channels 204 and 206, thus improving the efficiency of dissipating / eliminating acoustic oscillations. For example, if the second channel 206 were not present, the acoustic damping device 200 would be 60% efficient in reducing the amplitude of acoustic oscillations. Adding the second channel 206 can increase the efficiency to, for example, 90% because of the additional volume where acoustic oscillations can be dissipated.

[0043] Figure 3 This is a partial cross-sectional view of a second example acoustic damping device 300. The second example acoustic damping device 300 includes a combination of Figure 2 The first example acoustic damping device 200 describes all the components and operates using the same physical process. However, as Figure 3 As shown, the second example acoustic damping device 300 includes a second plurality of disks 302 oriented within the second channel 206. As described above, the second volume 209 is defined by the volume of the second channel 206 minus any internal structure. Therefore, Figure 3 The second volume 209 in the example is the volume of the second channel 206 minus the volume occupied by the second disk 302.

[0044] exist Figure 3 In the example, the second disc 302 is in the shape of a washer and includes a larger... Figure 2 A larger second opening 304 is formed from the opening 220. The second opening 304 is located on the centerline 202, just like... Figure 2 The opening 220 is aligned with the center line 202 and extends radially outward from the center line 202 to the second disc 302. Figure 3 Example of the second plate 302 than Figure 2 The 218 is larger.

[0045] The second plate, 302, includes the outer edge 306 and the inner edge 308. In Figure 3 In the example, the outer edge 306 of the second disc 302 is flush / aligned / connected to the outer wall 212 of the second channel. The second disc 302 has a fifth radius 310 from the centerline 202 to the outer edge 306 of the second disc 302 and a sixth radius 312 from the centerline 202 to the inner edge 308 of the second disc 302. In the examples disclosed herein, the fifth radius 310 and the sixth radius 312 can be expressed as a ratio of the fifth radius 310 to the sixth radius 312. For example, the ratio of the fifth radius 310 to the sixth radius 312 can be from 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 position and configuration of the acoustic damping device 300. In some examples, the sixth radius 312 is equal to 0.7 inches, thereby allowing a gap between the inner edge 308 and the inner wall 210 of the second channel.

[0046] Including a second disk 302 in the second channel 206 allows for finer adjustment of the dissipation / cancellation response of the second example acoustic damping device 300. For example, increasing the number of disks (disk 218 or the second disk 302) increases control over the frequencies to be dissipated / cancelled because the surface available for capturing these oscillations is increased. As described above, the number of disks 218, 302 and their individual dimensions can be appropriately modified to adjust the vibration 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 acoustic oscillations (e.g., increasing efficiency from 60% to 70% or higher). Increasing the size of disks 218, 302 naturally increases the volume of the acoustic damping devices 200, 300, thereby covering the lower frequency range as described above. Decreasing the size of disks 218, 302 provides a lower volume, thereby covering the higher frequency range. Therefore, the number and size of discs 218 and 302 can be changed according to the frequency range that needs to be dissipated / eliminated and according to the required size of acoustic damping devices 200 and 300.

[0047] although Figure 3 The example shows that the individual discs in the second disc 302 are identical in size and shape, but it should be understood that the size and shape of the second disc 302 may be similar to that of disc 218 (e.g., presenting a funnel shape). Therefore, the examples disclosed herein are not limited to the examples shown, and may include combinations of the components disclosed herein.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] In some examples, Figure 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.

[0052] 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 Figure 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.

[0053] 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".

[0054] 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.

[0055] like Figure 5As shown in the example, acoustic damping devices 200, 300, and 400 are oriented at the ends of fuel line 502. In the example disclosed herein, fuel line 502 is pressurized to facilitate fuel movement through fuel line 502. Therefore, the acoustic damping devices 200, 300, and 400 are oriented at the ends of fuel line 502 where the pressure is greatest due to fuel flow stagnation. At the same location, flow instability is also greatest due to the same fuel flow stagnation. Therefore, including acoustic damping devices 200, 300, and 400 at the ends of fuel line 502, according to the details disclosed herein, can provide improved damping characteristics and elimination of flow instability.

[0056] Figures 6A-6C It shows Figure 2-4 Examples of acoustic damping devices 200, 300, and 400 in [the text] Figure 5 A schematic diagram of an alternative example placement on the example fuel manifold 500. Figures 6A-6C In the example, acoustic damping devices 200, 300, and 400 are oriented along the fuel line 502 of the example fuel manifold 500. Figures 6A-6C As indicated by the arrow, fuel flows through fuel line 502 in one direction.

[0057] Figure 6A The T-joint orientation 600 is shown. Figure 6A The examples show acoustic damping devices 200, 300, and 400 at a 90-degree angle relative to the fuel flow through fuel line 502. T-joint orientation 600 allows fuel (or any resulting oscillations) to enter the acoustic damping devices 200, 300, and 400, dissipating vibrations / reducing pressure build-up before releasing fuel back into fuel line 502 to continue to fuel nozzle 504.

[0058] Figure 6B The acute-angle orientation 602 is shown. Figure 6B The examples show acoustic damping devices 200, 300, 400 at an angle of less than 90 degrees relative to the fuel flow through fuel line 502. Similarly, fuel can enter acoustic damping devices 200, 300, 400 at an acute angle 602 to dissipate / eliminate flow instability.

[0059] Figure 6C The obtuse angle orientation 604 is shown. Figure 6C Examples show acoustic damping devices 200, 300, 400 at an angle greater than 90 degrees relative to the fuel flow through fuel line 502.

[0060] Figure 6AThe example in -C is intended to illustrate the potential orientations of the acoustic damping 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 in a small footprint, the T-joint orientation 600 may not meet the size constraints. Therefore, an acute-angle orientation 602 or an obtuse-angle orientation 604 could be used to accommodate a smaller footprint.

[0061] In some examples, the example acoustic damping devices 200, 300, and 400 are oriented to combine the teachings disclosed herein with Helmholtz resonators along fuel lines, exhaust lines, etc. In such examples, the example acoustic damping devices 200, 300, and 400 provide structural improvements to dissipate / eliminate flow instabilities and acoustic oscillations, while providing improved noise reduction corresponding to the Helmholtz resonators.

[0062] Figure 7 yes Figure 1 A cross-sectional view of an example combustion section 116 of an example gas turbine engine 100, which utilizes Figure 2-4 Examples of acoustic damping devices 200, 300, and 400 are shown in the image. Figure 7 In the example, fuel nozzle 504 deposits fuel into combustion chamber 700. Ignition 702 ignites the fuel, ultimately producing thrust as described above.

[0063] When fuel is ignited, vibrations are generated due to the chemical reaction that ignites 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, in front of the fuel nozzle 504, and may affect surrounding structures.

[0064] exist Figure 7 In some examples, one or more acoustic damping devices 200, 300, 400 are positioned in front of the fuel nozzle 504 to dissipate / eliminate these generated oscillations. In some examples, the number of acoustic damping 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 damping devices 200, 300, 400 is fixed (e.g., one for each fuel nozzle 504, one every other fuel nozzle 504, etc.). In some examples, the acoustic damping devices 200, 300, 400 may be circumferentially positioned around the gas turbine engine 100 based on the combustion section 116 (e.g., through the circumferential combustion section). Although Figure 7 The examples show two of the acoustic damping devices 200, 300, and 400, but correspondingly, only one or more can be used.

[0065] Figure 8 It is possible Figure 1 An example quarter-wave tube combustion section 800 is implemented on an example gas turbine engine 100. The example quarter-wave tube combustion section 800 includes a plurality of combustion portions 802 circumferentially distributed around the quarter-wave tube combustion section 800. In operation, a quarter-wave tube 804 extends from the combustion portions 802 to dissipate vibrational frequencies generated by fuel ignition. The size and shape of the quarter-wave tube 804 are determined based on the expected frequency range experienced in the gas turbine engine 100. In operation, the quarter-wave tube 804 is tuned for a small range of frequencies (e.g., 100 Hz to 500 Hz).

[0066] Figure 9 yes Figure 2-4 Acoustic damping devices 200, 300, 400 in Figure 8 The first example arrangement 900 in the example quarter-wave tube combustion section 800. Figure 9 The example shows Figure 8 The cross-section of one of the combustion sections 802 includes a quarter-wave tube 804. With Figure 7 Similarly, in the combustion section 802, the fuel is ignited in the ignition zone 902 within the combustion chamber 700. The reaction of igniting the fuel produces vibrational waves or acoustic oscillations that propagate throughout the combustion section 802, including the front and rear sections.

[0067] like Figure 9 As shown in the example, acoustic damping devices 200, 300, and 400 are disposed within a quarter-wave tube 804 in front of the combustion chamber 700 to dissipate generated oscillations. In some examples, the quarter-wave tube 804 is omitted, and only acoustic damping devices 200, 300, and 400 are implemented to dissipate oscillations. Such an arrangement may be necessary when replacing combustion sections 116 and 800 is difficult, time-consuming, or expensive, and inserting acoustic damping devices 200, 300, and 400 into the existing structure can improve performance. This approach also reduces / eliminates the need to redesign the existing platform to accommodate performance improvements.

[0068] Figure 10 yes Figure 2-4 The acoustic damping devices 200, 300, and 400 in the middle Figure 8 The second example arrangement 1000 is shown in the example quarter-wave tube combustion section 800. Figure 10 The example shows Figure 8 The cross-section of one of the combustion sections 802 includes a quarter-wave tube 804. (As...) Figure 10 As shown, acoustic damping devices 200, 300, and 400 are located downstream (e.g., at the rear) of the ignition zone 902 and adjacent to the combustion chamber 700.

[0069] 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).

[0070] 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 that according to Figure 10 The second example arrangement is an example cooling flow arrangement 1100 of acoustic damping devices 200, 300, and 400.

[0071] 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... Figure 2-4 Any of the example acoustic damping devices 200, 300, 400 can be used here.

[0072] 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, and 400. This process of cooling the hot gas 1106 allows the acoustic damping devices 200, 300, and 400 to operate in the ignition section 902 ( Figure 9 and 10 (The operation is performed afterward.)

[0073] 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.

[0074] This article discloses example acoustic damping devices and their related usage methods. Further examples and combinations are provided in the following sections:

[0075] An acoustic damping device includes: a first channel defining a first volume, the first channel being 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 of the plurality of disks including an opening at its center 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 distributed along an outer wall of the first channel and located between the plurality of disks, the holes facilitating the transfer of at least one of the fluid or the acoustic vibration from the first channel to the second channel.

[0076] According to the acoustic damping device described in the preceding clause, wherein: the first disk of the plurality of disks at the first end of the first channel has a first radius from the outer edge of the first disk to the center and a second radius from the inner edge of the first disk to the center; and the second disk of the plurality of disks at the second end of the first channel has a third radius from the outer edge of the second disk to the center and a fourth radius from the inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0077] According to any of the preceding clauses, the acoustic damping device wherein the second radius is greater than the fourth radius.

[0078] The acoustic damping device according to any of the preceding clauses, wherein the second radius is smaller than the fourth radius.

[0079] According to any of the preceding clauses, the plurality of disks are a first plurality of disks, the opening is a first opening, the center is a first center, and the acoustic damping device further includes a second plurality of disks oriented within the second channel, each of the second plurality of disks including a second opening at a second center of the respective disk, the first center being aligned with the second center.

[0080] According to any of the preceding clauses, the acoustic damping device comprises: a first disk of the second plurality of disks at a first end of the second channel having a first radius from the outer edge of the first disk to the second center and a second radius from the edge of the second opening of the first disk to the second center; and a second disk of the second plurality of disks at a second end of the second channel having a third radius from the outer edge of the second disk to the second center and a fourth radius from the edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0081] The acoustic damping device according to any of the preceding clauses, wherein the second radius and the fourth radius are equal.

[0082] The acoustic damping device according to any of the preceding clauses, wherein the first volume is larger than the second volume.

[0083] According to any of the preceding clauses, the volume ratio of the second volume to the first volume ranges from 0.1 to 1.0 in the acoustic damping device.

[0084] A turbine engine with a centerline axis includes: a nacelle; a combustion section surrounded by the nacelle, the combustion section including a combustion chamber located at the rear of the combustion section along the centerline axis; and an acoustic damping device within the combustion section, the acoustic damping device including: a first channel defining a first volume, the first channel being 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 of the plurality of disks including an opening at the center of the disk to allow acoustic vibrations to move from the first end to the second end, the first channel including a plurality of holes distributed along the outer wall of the first channel and located between the plurality of disks, the holes facilitating the transmission of the acoustic vibrations from the first channel to the second channel.

[0085] The turbine engine according to any of the preceding clauses, wherein the acoustic damping device is located at the front of the combustion section along the centerline axis.

[0086] According to any of the preceding clauses, the turbine engine wherein the acoustic damping device is located at the rear of the combustion section and adjacent to the combustion chamber along the centerline axis.

[0087] The turbine engine according to any of the preceding clauses further includes at least one quarter-wave tube located in the rear or front portion of the combustion section, wherein the acoustic damping device is disposed within the quarter-wave tube of the combustion section.

[0088] According to any of the preceding clauses of the turbine engine, wherein the first disk of the plurality of disks at the first end of the first channel has a first radius from the outer edge of the first disk to the center and a second radius from the inner edge of the first disk to the center; and the second disk of the plurality of disks at the second end of the first channel has a third radius from the outer edge of the second disk to the center and a fourth radius from the inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0089] The turbine engine according to any of the preceding clauses, wherein the second radius is greater than the fourth radius.

[0090] The turbine engine according to any of the preceding clauses, wherein the second radius is smaller than the fourth radius.

[0091] The turbine engine according to any of the preceding clauses, wherein the plurality of disks are a first plurality of disks, the opening is a first opening, the center is a first center, and further includes a second plurality of disks oriented within the second channel, each of the second plurality of disks including a second opening at a second center of the respective disk, the first center being aligned with the second center.

[0092] According to any of the preceding clauses of the turbine engine, the first disk of the second plurality of disks at the first end of the second channel has a first radius from the outer edge of the first disk to the second center and a second radius from the edge of the second opening of the first disk to the second center; and the second disk of the second plurality of disks at the second end of the second channel has a third radius from the outer edge of the second disk to the second center and a fourth radius from the edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0093] The turbine engine according to any of the preceding clauses, wherein the second radius and the fourth radius are equal.

[0094] The turbine engine according to any of the preceding clauses, wherein the first volume is larger than the second volume.

[0095] The turbine engine according to any of the preceding clauses, wherein the volume ratio of the second volume to the first volume ranges from 0.1 to 1.0.

[0096] A turbine engine includes a nacelle; a combustion section within the nacelle; and a fuel manifold that delivers fuel from a fuel tank to the combustion section, the combustion section igniting the fuel, the fuel manifold including fuel nozzles to deposit the fuel into the combustion section; a fuel line that delivers the fuel from the fuel tank to the fuel nozzles; and an acoustic damping device coupled to a first portion of the fuel line, the acoustic damping device including a first channel defining a first volume, the first channel being 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 of the plurality of disks including an opening at the center of the disk to allow fluid to move from the first end to the second end, the first channel including a plurality of orifices dispersed along the outer wall of the first channel and located between the plurality of disks, the orifices facilitating the transfer of fluid from the first channel to the second channel.

[0097] The turbine engine according to any of the preceding clauses, wherein the acoustic damping device is a first acoustic damping device, and further includes a second acoustic damping device connected to a second portion of the fuel line, the second portion being different from the first portion.

[0098] According to any of the preceding clauses of the turbine engine, wherein the first disk of the plurality of disks at the first end of the first channel has a first radius from the outer edge of the first disk to the center and a second radius from the inner edge of the first disk to the center, and the second disk of the plurality of disks at the second end of the first channel has a third radius from the outer edge of the second disk to the center and a fourth radius from the inner edge of the second disk to the center, wherein the first radius and the third radius are equal.

[0099] The turbine engine according to any of the preceding clauses, wherein the second radius is greater than the fourth radius.

[0100] The turbine engine according to any of the preceding clauses, wherein the second radius is smaller than the fourth radius.

[0101] The turbine engine according to any of the preceding clauses, wherein the plurality of disks are a first plurality of disks, the opening is a first opening, the center is a first center, and further includes a second plurality of disks oriented within the second channel, each of the second plurality of disks including a second opening at a second center of the respective disk, the first center being aligned with the second center.

[0102] According to any of the preceding clauses of the turbine engine, wherein the first disk of the second plurality of disks at the first end of the second channel has a first radius from the outer edge of the first disk to the second center and a second radius from the edge of the second opening of the first disk to the second center, and the second disk of the second plurality of disks at the second end of the second channel has a third radius from the outer edge of the second disk to the second center and a fourth radius from the edge of the second opening of the second disk to the second center, wherein the first radius and the third radius are equal.

[0103] The turbine engine according to any of the preceding clauses, wherein the second radius and the fourth radius are equal.

[0104] The turbine engine according to any of the preceding clauses, wherein the first volume is larger than the second volume.

[0105] The turbine engine according to any of the preceding clauses, wherein the volume ratio of the second volume to the first volume is between 0.1 and 1.0.

[0106] According to any of the preceding clauses, the turbine engine wherein the acoustic damping device is oriented at a 90-degree angle relative to the direction of fuel flow in the fuel manifold.

[0107] According to any of the preceding clauses of the turbine engine, wherein the acoustic damping device is oriented at an angle between 0 and 90 degrees relative to the direction of fuel flow in the fuel manifold.

[0108] According to any of the preceding clauses of the turbine engine, wherein the acoustic damping device is oriented at an angle between 90 degrees and 180 degrees relative to the direction of fuel flow in the fuel manifold.

[0109] According to any of the preceding clauses, the turbine engine wherein the acoustic damping device is located at the first end of the fuel line.

[0110] The following claims are incorporated herein by reference. Although certain example systems, devices, articles of manufacture, and methods have been disclosed herein, the scope of this patent is not limited thereto. Rather, this patent covers all systems, devices, articles of manufacture, and methods that fall fully within the scope of the claims of this patent.

Claims

1. A fuel manifold for a gas turbine engine, characterized in that, The fuel manifold includes: Fuel pipelines; Fuel nozzle, the fuel line for delivering fuel from the fuel tank to the fuel nozzle; and An acoustic damping device fluidly coupled to the fuel line, the acoustic damping device including a first channel wall having an open first end and a closed second end, the first channel wall defining a first volume, the acoustic damping device including a first plurality of disks arranged in the first volume and along the central axis of the acoustic damping device, the first plurality of disks for damping at least one of the acoustic oscillations of the fuel or the fuel.

2. The fuel manifold according to claim 1, characterized in that, The acoustic damping device includes a second channel wall surrounding the first channel wall and defining a second volume between the first channel wall and the second channel wall, wherein the first channel wall includes a plurality of holes that allow at least one of the fuel or the acoustic oscillations of the fuel to be transmitted from the first volume to the second volume.

3. The fuel manifold according to claim 2, characterized in that, It further includes a second plurality of disks arranged in the second volume and along the central axis of the acoustic device, the second plurality of disks being used to further dampen at least one of the fuel or the acoustic oscillations of the fuel.

4. The fuel manifold according to claim 1, characterized in that, The acoustic damping device is located at the first end of the fuel line.

5. The fuel manifold according to claim 4, characterized in that, The acoustic damping device is a first acoustic damping device, and the fuel manifold further includes a second acoustic damping device located at a second end of the fuel line, the second end being different from the first end.

6. The fuel manifold according to claim 1, characterized in that, The acoustic damping device is oriented at an angle between 0 degrees and 180 degrees relative to the flow direction of the fuel in the fuel line.

7. A turbine engine, characterized in that, include: cabin; Combustion zone, the combustion zone being located within the engine compartment; as well as A fuel manifold for delivering fuel from a fuel tank to the combustion zone, the combustion zone for igniting the fuel, the fuel manifold comprising: A fuel line for delivering the fuel from the fuel tank to one or more fuel nozzles; and An acoustic damping device, fluidly connected to a first portion of the fuel line, the acoustic damping device comprising: A first channel, the first channel defining a first volume, the first channel being open at a first end and closed at a second end; A second channel, the second channel surrounding the first channel and defining a second volume; and A plurality of disks located in the first channel, the plurality of disks being configured to allow the fuel to move from the first end to the second end to dampen at least one of the fuel or acoustic oscillations of the fuel.

8. The turbine engine according to claim 7, characterized in that, The acoustic damping device is a first acoustic damping device, and further includes a second acoustic damping device fluidly connected to a second portion of the fuel line, the second portion being different from the first portion.

9. The turbine engine according to claim 7, characterized in that, The first volume is larger than the second volume.

10. The turbine engine according to claim 7, characterized in that, The acoustic damping device is oriented at a 90-degree angle relative to the flow direction of the fuel in the fuel manifold.

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