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

Technical Field

[0001] The present disclosure generally relates to acoustic damping and, more particularly, to an acoustic damping device for a gas turbine engine. Background Art

[0002] Aircraft engines, automotive engines, generators, etc. generate vibrations during operation. The vibration generating devices may include additional hardware structures to dissipate the resonance frequencies caused by the vibrations, as such frequencies may damage the vibration generating devices. Brief Description of the Drawings

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

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

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

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

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

[0008] Figures 6A - 6C Shows Figures 2 - 4 an exemplary placement of an exemplary acoustic damping device on an exemplary fuel manifold in Figure 5 .

[0009] Figure 7 is Figure 1 a cross-sectional view of an exemplary combustion section of an exemplary gas turbine engine in Figures 2 - 4 utilizing an exemplary acoustic damping device of any one of

[0010] Figure 8 is a quarter-wave tube combustion section that can be implemented on an exemplary gas turbine engine in Figure 1 .

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

[0012] Figure 10 is Figures 2 - 4The acoustic damping device is in Figure 8 The second exemplary arrangement in the exemplary quarter - wave tube combustion section of

[0013] Figure 11 Shows the Figure 10 Exemplary cooling flow arrangement of the acoustic damping device of the second exemplary arrangement according to Figures 2 - 4 Detailed Description

[0014] In general, the same reference numerals will be used throughout the drawings and the accompanying written description to refer to the same or similar components. The drawings are not necessarily to scale. Instead, the thickness of layers or regions may be exaggerated in the drawings. Although the drawings show layers and regions with clear lines and boundaries, some or all of these lines and / or boundaries may be idealized. In reality, the boundaries and / or lines may be unobservable, blended, and / or irregular.

[0015] "Comprising" and "including" (and all forms and tenses thereof) are used herein as open-ended terms. Thus, whenever a claim uses any form of "comprising" or "including" (e.g., comprises, includes, having, etc.) as a preamble or uses any form of "comprising" or "including" in any type of claim recitation, it should be understood that there may be other elements, terms, etc., without falling outside the scope of the corresponding claim or recitation. As used herein, when the phrase "at least" is used as a transitional term in, for example, the preamble of a claim, it is open-ended, 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 a structure, component, item, object, and / or thing, 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 a structure, component, item, object, and / or thing, 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 a process, instruction, action, activity, 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 a process, instruction, action, activity, 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 a plurality. As used herein, the term "a" or "an" object refers to one or more of that object. The terms "a" (or "an"), "one or more", and "at least one" are used interchangeably herein. Further, although listed separately, a plurality of devices, elements, or acts may be implemented by, for example, the same entity or object. Additionally, although individual features may be included in different examples or claims, these features may possibly be combined, and inclusion in different examples or claims does not imply that a combination of the features is not feasible and / or disadvantageous.

[0017] As used herein, unless otherwise specified, the term "above" describes the relationship of two parts relative to the Earth. The first part is above the second part if at least a portion of the second part is 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 described above, the first part may be above or below the second part and have one or more of the following: there are other parts therebetween, there are no other parts therebetween, 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.

[0018] As used herein, connection references (e.g., attach, couple, connect, and engage) can include an intermediate member between the elements referenced by the connection reference and / or relative movement between these elements, unless otherwise specified. Thus, a connection reference does not necessarily mean that the two elements are directly connected and / or fixed to each other. As used herein, the definition of stating that any part is "in contact" with another part means that there is no intermediate part between the two parts.

[0019] Unless otherwise expressly specified, descriptors such as "first", "second", "third", etc. used herein do not confer or otherwise indicate any meaning of priority, physical order, list arrangement, and / or order in any way, but are merely used as labels and / or arbitrary names to distinguish elements, for ease 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 a different descriptor, 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.

[0020] Turbine engines are one of the most widely used power generation technologies and are commonly used in applications such as aircraft and power generation. A turbine engine typically includes a fan located in front of a core, which in flow order includes 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 be configured in any number of different ways. For example, a turbine engine can include one or more compressors and turbines, single or multiple spools, ducted or unducted fans, a gear drive structure, etc. In some examples, the fan and the low-pressure compressor are on the same shaft as the low-pressure turbine, while the high-pressure compressor is on the same shaft as the high-pressure turbine.

[0021] During operation, the rotating blades of the fan draw in the atmosphere into the turbomachine and push the air downstream. At least a portion of the air enters the core where the air is compressed by the rotating blades of the compressor, mixed with fuel and ignited to produce a high temperature and high pressure gas stream (e.g., hot combustion gases), which is delivered to the turbine section. The hot combustion gases expand as they flow through the turbine section, causing the rotating blades of the turbine to rotate. Each of these processes generates vibrations within the turbomachine, which are transmitted into the fuel flowing through the turbomachine and / or create pressure fluctuations, resulting in flow instabilities within the fuel and / or acoustic oscillations within the combustion chamber of the turbomachine.

[0022] In platforms such as automotive engines, generators, etc., vibrations are also generated due to the operation of these platforms (e.g., by igniting fuel, rotating an electric motor, etc.). Although the examples disclosed herein are directed to an aircraft turbomachine platform, the examples disclosed herein can be used in alternative platforms to eliminate flow fluctuations and acoustic oscillations generated by any vibration generating means.

[0023] Disclosed herein is an acoustic damping device that dampens / eliminates flow instabilities and / or acoustic oscillations generated by vibration generating means (e.g., turbomachine, fuel manifold, 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 is suitable for the wavelength frequency to dissipate or eliminate flow instabilities and / or acoustic oscillations (e.g., referred to as acoustic black holes).

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

[0025] Typically, a turbomachine 100 includes a core turbine 104 downstream of a fan (e.g., a fan section) 106. The core turbine 104 includes a generally tubular outer casing 108 that defines an annular inlet 110. The outer casing 108 may be formed by a single casing or multiple casings. The outer casing 108 circumscribes a compressor section in a series flow relationship, the compressor section having a booster or low-pressure compressor 112 ("LP compressor 112") and a high-pressure compressor 114 ("HP compressor 114"); 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] As Figure 1 shown, the fan 106 includes a plurality of fan blades 132 that are coupled to a centerline axis 102 and extend radially outwardly from the centerline axis 102. A nacelle 134 (also referred to as an annular fan housing 134) circumferentially surrounds at least a portion of the fan 106 and / or the core turbine 104. The nacelle 134 may be supported relative to the core turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. Additionally, a downstream section 138 of the nacelle 134 may circumscribe an outer portion of the core turbine 104 to define a bypass airflow passage 140 therebetween.

[0027] As Figure 1 shown, air 142 enters an inlet portion 144 of the turbomachine 100 during operation thereof. A first portion 146 of the air 142 flows into the bypass airflow passage 140, while a second portion 148 of the air 142 flows into an inlet 110 of the LP compressor 112. One or more successive stages of LP compressor stator vanes 150 and LP compressor rotor blades 152 progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 and flowing toward the HP compressor 114. Next, one or more successive stages of HP compressor stator vanes 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 combusted to provide combustion gases 160.

[0028] Like the gas turbine engine 100, the core turbine 104 functions similarly and is exposed to similar environments in land-based gas turbine engines, turbojet engines (where the ratio of the first portion 146 of the air 142 to the second portion 148 of the air 142 is less than the ratio in a turbofan engine), and ducted fan engines (where the fan 106 does not have a nacelle 134). In each of the turbofan engine, the turbojet engine, and the ducted fan engine, a reduction device (e.g., a reduction gear 130) may be included between any shaft and spool.

[0029] Figure 1 The operation of the turbine engine 100 therein can generate flow instabilities in the fuel line and / or acoustic oscillations due to the pressure differences generated by the operation of the turbine engine 100. In some examples, the operation of the turbine engine 100 causes the fuel flowing through the fuel line to vibrate. In some examples, the fuel combustion in the combustion section 116 can generate acoustic oscillations due to the chemical reaction (e.g., pressure difference) that ignites the fuel. It should be understood that many alternatives can cause Figure 1 vibrations during the operation of the turbine engine 100, and the previous examples are only provided for background to place the disclosed systems, devices, articles of manufacture, and methods in an example environment.

[0030] In some examples, an acoustic damping device is disposed within Figure 1 the 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 where acoustic vibrations that can be damped are generated, such as within the LP compressor 112, HP compressor 114, exhaust section 122, bypass air flow passage 140, etc.

[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 channel 204, and a second channel 206. In Figure 2 the example, the first channel 204 corresponds to a first volume 207. The first volume 207 is defined by subtracting any internal structures from the first channel wall 208 that 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.

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

[0033] In some examples, the first volume 207 is greater 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 based on a volume ratio to achieve a desired response to the 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 length 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 length of the first channel 204 and / or the second channel 206 is any value between 10 times the radius of the disk 218 and 50 times the radius of the disk 218.

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

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

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

[0037] As Figure 2 shown, the disks 218 are funnel-shaped from the first end 214 towards 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 examples disclosed herein, the first disk outer edge 224 is flush / aligned / connected with 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., the turbine engine 100, internal combustion engine, etc.). In the examples 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, the second radius 230 is 0.43 inches, and the tolerance range is 0.05 inches.

[0038] In addition, in Figure 2In the example of, the second disk 232 includes a second disk outer edge 234 and a second disk inner edge 236. In the examples disclosed herein, the second disk outer edge 234 is flush / aligned / connected with the first channel wall 208. The second disk 232 has a third radius 238 that is equal to the first radius 228 and corresponds 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 the 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 size of the fourth radius 240 is determined according to the position and configuration of the acoustic damping device 200. In some examples, the inner radius of the disk 218 linearly decreases towards the second end 216. In other examples, the inner radius varies exponentially, quadratically, etc.

[0039] In the examples disclosed herein, the size of the disk 218 corresponds to the operating conditions to which the first example acoustic damping device 200 is subjected. 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 / disturbed stormy weather, etc.), cruise, takeoff, climb, etc. In operation, when fluid / acoustic oscillations enter the first end 214 and proceed to the second end 216, the disk 218 dissipates / eliminates the generated oscillations through the size and spacing of the disk 218 within the first channel 204. In some examples, the sizes 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 parabola / power law function, etc.

[0040] To further dissipate / eliminate these oscillations, a plurality of holes 242 are disposed 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 transfer between the first channel 204 and the second channel 206. In some examples, the holes 242 are circular and their diameter dimensions are determined according to the position and configuration of the acoustic damping device 200 (e.g., in the turbine engine 100). For example, the diameter dimensions of the holes 242 are 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 of the disks 218 can be from 10% of the first radius 228 to 120% of the first radius 228. Thus, the diameter dimensions of the holes 242 are sized to fit within the distance between the disks 218. In some examples, the diameter of the plurality of holes 242 is 0.02 inches.

[0041] In operation, by providing an additional volume that allows the oscillations to dissipate and allowing fluid / acoustic oscillations to transfer between the channels 204, 206, the efficiency of dissipating / eliminating the acoustic oscillations is increased. For example, if there is no second channel 206, it is assumed that the efficiency of the acoustic damping device 200 in reducing the amplitude of the acoustic oscillations is 60%. Adding the second channel 206 can increase the efficiency to, for example, 90% because there is an 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 channel 206. As described above, the second volume 209 is defined by the volume of the second channel 206 minus any internal structures. Thus, Figure 3 the second volume 209 of the example is the volume of the second channel 206 minus the volume occupied by the second disks 302.

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

[0044] The second disk 302 each includes an outer edge 306 and an inner edge 308. In Figure 3 the example of, the outer edge 306 of the second disk 302 is flush / aligned / connected with the outer wall 212 of the second channel. The second disk 302 has a fifth radius 310 from the centerline 202 to the outer edge 306 of the second disk 302 and a sixth radius 312 from the centerline 202 to the inner edge 308 of the second disk 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 and the sixth radius 312. For example, the ratio of the fifth radius 310 and 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, allowing a gap between the inner edge 308 and the inner wall 210 of the second channel.

[0045] Including the second disk 302 in the second channel 206 allows for a more refined adjustment of the dissipation / elimination response of the second example acoustic damping device 300. For example, increasing the number of disks (disk 218 or the second disk 302) can increase the control over the frequencies to be dissipated / eliminated because the surface available for capturing these oscillations increases. As described above, the number of disks 218, 302 and the respective dimensions of the disks 218, 302 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 the efficiency of damping acoustic oscillations (e.g., increasing the efficiency from 60% to 70% or higher). Increasing the size of the disks 218, 302 naturally increases the volume of the acoustic damping devices 200, 300, thus covering the lower frequency range as described above. Decreasing the size of the disks 218, 302 provides a lower volume, thus covering the higher frequency range. Therefore, the number of disks 218, 302 and the size of the disks 218, 302 can be changed according to the frequency range to be dissipated / eliminated and according to the size required for the acoustic damping devices 200, 300.

[0046] Although Figure 3 the example of shows that each disk in the second disk 302 is the same in size and shape, it should be understood that the size and shape of the second disk 302 can be similar to that of the disk 218 (e.g., presenting a funnel shape). Therefore, the examples disclosed herein are not limited to the examples shown and can include combinations of the components disclosed herein.

[0047] Figure 4It is a cross-sectional view of a third exemplary acoustic damping device 400. The third exemplary acoustic damping device 400 includes all the components described in connection with Figure 2 the first exemplary acoustic damping device 200 and operates using the same physical processes. However, as Figure 4 shown, the shape and dimensions of the third exemplary acoustic damping device 400 are different.

[0048] As Figure 4 shown, the first radius 228 of the first disk 222 is not equal to the third radius 238 of the second disk 232. In Figure 4 the example, the second radius 230 of the first disk 222 is equal to the fourth radius 240 of the second disk 232 (e.g., 0.06 inches), and the third radius 238 is greater than the first radius 228 (e.g., the third radius 238 is equal to 0.33 inches and the first radius 228 is equal to 0.1 inches). This example reflects an inverted funnel shape where the first channel 204 gets larger closer to the second end 216. Different from the first channel 204, Figure 4 the second channel 206 in the example gets smaller closer to the second end 216.

[0049] As described above, the size and shape of the disks 218, 302 are determined based on the desired response to the vibration frequencies experienced (e.g., any frequency between 100 Hertz (Hz) and 4,000 Hz). At the lower end of the frequency range experienced (e.g., 100 - 1,000 Hz), the disks 218, 302 are smaller in size than those that can handle a higher frequency range (e.g., 1,000 - 2,000 Hz). For example, to increase the volume ratio to handle the lower frequency range (as disclosed in connection with Figure 2 ), the disk 218 has a smaller radius to reduce the first volume 207 corresponding to the first channel 204. Alternatively, to reduce the volume ratio to handle the higher frequency range, the disk 218 has a larger radius to increase the first volume 207 corresponding to the first channel 204. Figure 4 The example of

[0050] provides an alternative arrangement of the disk 218 that can be used interchangeably with any example provided herein. Figures 2 - 4 In some examples, Figure 11 the acoustic damping devices 200, 300, 400 are made of metallic materials such as aluminum, steel, titanium, etc. It is noted that the placement of the acoustic damping devices 200, 300, 400 within the gas turbine engine 100 may change the materials used to manufacture the acoustic damping devices 200, 300, 400. For example, if the acoustic damping devices 200, 300, 400 are disposed at the rear of the combustion section 116, the material can be titanium to withstand the heat generated from igniting the fuel. Alternatively, cooling methods can be implemented to protect the acoustic damping devices 200, 300, 400 (see below Figure 11)。In other cases where not too much heat is generated, the materials of the acoustic damping devices 200, 300, 400 can be 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, 400.

[0051] Figure 5 is implementable as Figure 1 a schematic view of an exemplary fuel manifold 500 implemented as part of an exemplary gas turbine engine 100, which uses Figures 2 - 4 any of the exemplary acoustic damping devices 200, 300, 400 in Figure 1 as disclosed. As described above, the operation of the gas turbine engine 100 may cause flow instability in the fuel delivered through the fuel line 502, thereby affecting the operation of the fuel manifold 500 (e.g., reduced efficiency of delivering fuel, damage to the fuel line 502, etc.). In an exemplary environment (such as the exemplary gas turbine engine 100), multiple fuel lines 502 can be used independently of each other.

[0052] The exemplary fuel manifold 500 includes a fuel line fitting 506 for connecting a siphon 508 to the 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 fitting 506 allows a portion of the fuel to be supplied into the siphon 508 while allowing the remaining portion of the fuel to continue through the fuel line 502. In some examples, the siphon 508 is also referred to as a "tail pipe".

[0053] In Figure 5 the example of

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

[0055] Figures 6A - 6C shows Figures 2 - 4 an alternative example placement of the exemplary acoustic damping devices 200, 300, 400 on the exemplary fuel manifold 500 in Figure 5 . In Figures 6A - 6C the example of, the acoustic damping devices 200, 300, 400 are oriented along the fuel line 502 of the exemplary fuel manifold 500. As Figures 6A - 6C shown by the arrows in, the fuel flows through the fuel line 502 in one direction.

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

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

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

[0059] Figure 6AThe examples of -C are intended to illustrate the potential orientations of the acoustic damping devices 200, 300, 400 on the exemplary fuel manifold 500 due to dimensional constraints in any given environment. For example, if the fuel manifold 500 is to be installed in a smaller footprint, the T-joint orientation 600 may not meet the dimensional constraints. Thus, an acute angle orientation 602 or an obtuse angle orientation 604 can be used to accommodate the smaller footprint.

[0060] In some examples, the exemplary acoustic damping devices 200, 300, 400 are oriented to combine the teachings disclosed herein with Helmholtz resonators along fuel lines, exhaust lines, etc. In such examples, the exemplary acoustic damping 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 resonators.

[0061] Figure 7 is Figure 1 A cross-sectional view of an exemplary combustion section 116 of an exemplary gas turbine engine 100 in Figures 2 - 4 utilizing the exemplary acoustic damping devices 200, 300, 400 in Figure 7 In an example of

[0062] When the fuel is ignited, vibrations are generated due to the chemical reaction of the ignited 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 the surrounding structures.

[0063] In Figure 7 an example of Figure 7 one or more acoustic damping devices 200, 300, 400 are disposed 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 per fuel nozzle 504, one per every other fuel nozzle 504, etc.). In some examples, the acoustic damping devices 200, 300, 400 can be placed circumferentially around the gas turbine engine 100 based on the combustion section 116 (e.g., via a circumferential combustion section). Although Figure 7 the example of

[0064] Figure 8 is available inFigure 1 An example quarter-wave tube combustion section 800 implemented on an example gas turbine engine 100. The example quarter-wave tube combustion section 800 includes a plurality of combustion parts 802 that are circumferentially dispersed around the quarter-wave tube combustion section 800. In operation, quarter-wave tubes 804 extend from the combustion parts 802 to dissipate the vibration frequencies generated by fuel ignition. The size and shape of the quarter-wave tubes 804 are determined according to the expected frequency range experienced in the gas turbine engine 100. In operation, the quarter-wave tubes 804 are tuned for a small range of frequencies (e.g., 100 Hz to 500 Hz).

[0065] Figure 9 is Figures 2 - 4 The acoustic damping devices 200, 300, 400 in 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 parts 802 of Figure 7 which includes a quarter-wave tube 804. Similar to the example of

[0066] As Figure 9 shown in the example of

[0067] Figure 10 is Figures 2 - 4 The acoustic damping devices 200, 300, 400 in 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 parts 802 of Figure 10 which includes a quarter-wave tube 804. As

[0068] Figure 10The second example arrangement 1000 in Figure 1 ) dissipates / eliminates the vibration frequency on the hot side of the combustion section 116 (e.g., behind the 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 amount of oscillation dissipation (e.g., reducing the overall vibration effect and / or increasing the efficiency of damping acoustic oscillations).

[0069] During operation, the ignited fuel generates hot gases (e.g., exceeding 2,000 degrees Fahrenheit), which are subsequently ejected into the 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 Shows an example cooling flow arrangement 1100 of the acoustic damping devices 200, 300, 400 according to the second example arrangement 1000 of Figure 10 .

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

[0071] any example acoustic damping device 200, 300, 400 in Figure 11 can be used here. Figure 9 and 10 ).

[0072] From the above, it can be understood that example systems, devices, articles, and methods have been disclosed for dissipating and / or eliminating vibration frequencies, acoustic oscillations, and flow instabilities caused by vibration generating devices using acoustic damping devices or acoustic black holes. The inability to dissipate and / or eliminate vibration frequencies can lead to damage to components within the environment. Such damage can result in the inoperability of the environment and / or a decrease in performance.

[0073] This disclosure provides example acoustic damping devices and related methods of use. 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 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 respective disk to permit at least one of fluid or acoustic vibrations 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 transfer of at least one of the fluid or the acoustic vibrations from the first channel to the second channel.

[0075] The acoustic damping device according to the preceding clause, wherein: a first disk of the plurality of disks at 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 at 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 according to any of the preceding clauses, wherein the second radius is greater than the fourth radius.

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

[0078] The acoustic damping device 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 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.

[0079] The acoustic damping device according to any one of the preceding clauses, wherein: a first disk among 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 a second disk among 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.

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

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

[0082] The acoustic damping device according to any one of the preceding clauses, wherein the 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 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 opening 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 each disk to allow acoustic vibrations to move from the first end to the second end, the first channel including a plurality of holes dispersed along the outer wall of the first channel and located between the plurality of disks, the holes facilitating transfer of the acoustic vibrations from the first channel to the second channel.

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

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

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

[0087] A turbine engine according to any one of the preceding clauses, wherein a first disk of the plurality of disks at 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 at 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] A turbine engine according to any one of the preceding clauses, wherein the second radius is greater than the fourth radius.

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

[0090] A turbine engine according to any one of the preceding clauses, wherein the plurality of disks is 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 passage, each disk of the second plurality of disks includes a second opening at a second center of each disk, and the first center is aligned with the second center.

[0091] A turbine engine according to any one of the preceding clauses, wherein a first disk of the second plurality of disks at 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 at 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.

[0092] A turbine engine according to any one of the preceding clauses, wherein the second radius and the fourth radius are equal.

[0093] A turbine engine according to any one of the preceding clauses, wherein the first volume is greater than the second volume.

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

[0095] 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 passage that defines a first volume, the first passage opening at a first end and closed at a second end; a second passage that surrounds the first passage and defines a second volume, and a plurality of disks oriented within the first passage, each of the plurality of disks including an opening at a center of the respective disk to permit fluid 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 transfer of the fluid from the first passage to the second passage.

[0096] The turbine engine according to any one of the preceding clauses, wherein the acoustic damping device is a first acoustic damping device, further comprising a second acoustic damping device coupled to a second portion of the fuel line, the second portion being different from the first portion.

[0097] The turbine engine according to any one of the preceding clauses, wherein a first one of the plurality of disks at 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 one of the plurality of disks at 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 according to any one of the preceding clauses, wherein the second radius is greater than the fourth radius.

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

[0100] The turbine engine according to any one 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, further comprising a second plurality of disks oriented within the second passage, 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.

[0101] A turbine engine according to any of the preceding clauses, wherein a first disc of the second plurality of discs at a first end of the second passage has a first radius from an outer edge of the first disc to the second center and a second radius from an edge of the second opening of the first disc to the second center, and a second disc of the second plurality of discs at a second end of the second passage has a third radius from an outer edge of the second disc to the second center and a fourth radius from an edge of the second opening of the second disc to the second center, wherein the first radius and the third radius are equal.

[0102] A turbine engine according to any of the preceding clauses, wherein the second radius and the fourth radius are equal.

[0103] A turbine engine according to any of the preceding clauses, wherein the first volume is greater than the second volume.

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

[0105] A turbine engine according to any of the preceding clauses, wherein the acoustic damping device is oriented at a 90-degree angle with respect to a fuel flow direction in the fuel manifold.

[0106] A turbine engine according to any of the preceding clauses, wherein the acoustic damping device is oriented at an angle between 0 degrees and 90 degrees with respect to a fuel flow direction in the fuel manifold.

[0107] A turbine engine according to any of the preceding clauses, wherein the acoustic damping device is oriented at an angle between 90 degrees and 180 degrees with respect to a fuel flow direction in the fuel manifold.

[0108] A turbine engine according to any of the preceding clauses, wherein the acoustic damping device is positioned at a first end of the fuel line.

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

Claims

1. An acoustic damping device, characterized in that, Comprising: A first channel that defines a first volume, the first channel being open at a first end and closed at a second end; A second channel that surrounds the first channel and defines 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 respective disk to permit at least one of fluid or acoustic oscillations to move from the first end to the second end, the first channel including a plurality of holes dispersed along the outer wall of the first channel and located between the plurality of disks, the holes facilitating transfer of at least one of the fluid or the acoustic oscillations from the first channel to the second channel.

2. The acoustic damping device according to claim 1, characterized in that, Wherein: A 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 A 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.

3. The acoustic damping device according to claim 2, wherein, Wherein the second radius is greater than the fourth radius.

4. The acoustic damping device according to claim 2, characterized in that Wherein the first radius is less than the third radius.

5. The acoustic damping device according to claim 1, characterized in that, Wherein 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.

6. The acoustic damping device according to claim 5, characterized in that, Wherein: A 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 A 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.

7. The acoustic damping device according to claim 6, characterized in that Wherein the second radius and the fourth radius are equal.

8. The acoustic damping device according to claim 1, characterized in that, Wherein the first volume is greater than the second volume.

9. The acoustic damping device according to claim 8, characterized in that, Wherein the volume ratio of the second volume to the first volume ranges from 0.1 to 1.

0.

10. A turbine engine having a centerline axis, characterized in that, The turbomachine 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 a centerline axis; and An acoustic damping device within the combustion section, the acoustic damping device comprising: A first channel that defines a first volume, the first channel being open at a first end and closed at a second end; A second channel that surrounds the first channel and defines a second volume; and Multiple disks, the multiple disks being oriented within the first channel, each of the multiple disks including an opening at the center of each disk to permit acoustic oscillations to move from the first end to the second end, the first channel including a plurality of holes dispersed along the outer wall of the first channel and located between the multiple disks, the holes facilitating transfer of the acoustic oscillations from the first channel to the second channel.

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