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US-12624661-B2 - Acoustic damping device

US12624661B2US 12624661 B2US12624661 B2US 12624661B2US-12624661-B2

Abstract

Systems, apparatus, articles of manufacture, and methods are disclosed for an acoustic damping device. An example apparatus includes a first channel defining a first volume, the first channel open on a first end and closed on a second end, a second channel surrounding the first channel and defining a second volume, and a plurality of discs oriented within the first channel, respective discs of the plurality of discs including an opening in a center of the respective disc to allow at least one of a fluid or acoustic oscillation to move from the first end to the second end, the first channel including a plurality of apertures dispersed along an outer wall of the first channel and between the plurality of discs, the apertures to facilitate transfer of at least one of the fluid or the acoustic oscillation from the first channel to the second channel.

Inventors

  • Hiranya Kumar Nath
  • Ravindra Shankar Ganiger
  • Kwanwoo Kim
  • Dharmaraj Pachaiappan
  • Vivekta Sharma

Assignees

  • GENERAL ELECTRIC COMPANY

Dates

Publication Date
20260512
Application Date
20241004

Claims (20)

  1. 1 . A fuel manifold of a gas turbine engine, the fuel manifold comprising: a fuel line; a fuel nozzle, the fuel line to transport fuel from a 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 a first end that is open and a second end that is closed, the first channel wall defining a first volume, the acoustic damping device including a first plurality of discs in the first volume and arranged along a centerline axis of the acoustic damping device, the first plurality of discs to damp at least one of a flow instability or an acoustic oscillation of the fuel; and 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 apertures to enable transfer of at least one of the fuel or the acoustic oscillation of the fuel from the first volume to the second volume.
  2. 2 . The fuel manifold of claim 1 , further including a second plurality of discs in the second volume and arranged along the centerline axis of the acoustic damping device, the second plurality of discs to further damp at least one of the flow instability or the acoustic oscillation of the fuel.
  3. 3 . The fuel manifold of claim 1 , wherein the acoustic damping device is located on a first end of the fuel line.
  4. 4 . The fuel manifold of claim 3 , wherein the acoustic damping device is a first acoustic damping device, the fuel manifold further including a second acoustic damping device located on a second end of the fuel line, the second end different than the first end.
  5. 5 . The fuel manifold of claim 1 , wherein the acoustic damping device is oriented at an angle between 0 degrees and 180 degrees with respect to a flow direction of the fuel in the fuel line.
  6. 6 . The fuel manifold of claim 1 , wherein each disc of the first plurality of discs has an outer edge and an inner edge, the outer edge and the inner edge defining a solid area of each disc therebetween, wherein each disc of the first plurality of discs has a continuously varying solid area.
  7. 7 . A turbine engine comprising: a nacelle; a combustion section within the nacelle; and a fuel manifold to transport fuel from a fuel tank to the combustion section, the combustion section to ignite the fuel, the fuel manifold including: a fuel line to transport the fuel from the fuel tank to one or more fuel nozzles; and an acoustic damping device fluidly coupled to a first portion of the fuel line, the acoustic damping device including: a first channel defining a first volume, the first channel open on a first end and closed on a second end; a second channel surrounding the first channel and defining a second volume; and a plurality of discs in the first channel, the plurality of discs to allow the fuel to move from the first end to the second end to damp at least one of a flow instability or an acoustic oscillation of the fuel.
  8. 8 . The turbine engine of claim 7 , wherein the acoustic damping device is a first acoustic damping device, further including a second acoustic damping device fluidly coupled to a second portion of the fuel line, the second portion different than the first portion.
  9. 9 . The turbine engine of claim 7 , wherein the first volume is larger than the second volume.
  10. 10 . The turbine engine of claim 7 , wherein the acoustic damping device is oriented at a 90 degree angle with respect to a flow direction of the fuel in the fuel manifold.
  11. 11 . The turbine engine of claim 7 , wherein the acoustic damping device is oriented at an angle between 0 degrees and 90 degrees with respect to a flow direction of the fuel in the fuel manifold.
  12. 12 . The turbine engine of claim 7 , wherein the acoustic damping device is oriented at an angle between 90 degrees and 180 degrees with respect to a flow direction of the fuel in the fuel manifold.
  13. 13 . The turbine engine of claim 7 , wherein the fuel line is to transport the fuel from the fuel tank to the one or more fuel nozzles that deposit the fuel into the combustion section, and the acoustic damping device is oriented at a first end of the fuel line.
  14. 14 . The turbine engine of claim 7 , wherein each respective disc of the plurality of discs include an opening in a center of the respective disc to allow the fuel 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 between the plurality of discs, the plurality of apertures to facilitate a transfer of the fuel from the first channel to the second channel.
  15. 15 . The turbine engine of claim 14 , wherein a first disc of the plurality of discs on the first end of the first channel has a first radius from an outer edge of the first disc to the center and a second radius from an inner edge of the first disc to the center, and a second disc of the plurality of discs on the second end of the first channel has a third radius from an outer edge of the second disc to the center and a fourth radius from an inner edge of the second disc to the center, wherein the first radius and the third radius are equal.
  16. 16 . The turbine engine of claim 15 , wherein the second radius is larger than the fourth radius.
  17. 17 . The turbine engine of claim 15 , wherein the second radius is smaller than the fourth radius.
  18. 18 . The turbine engine of claim 14 , wherein the plurality of discs is a first plurality of discs, the opening is a first opening, the center is a first center, further including a second plurality of discs oriented within the second channel, each respective disc of the second plurality of discs including a second opening in a second center of the respective disc, the first center and the second center aligned.
  19. 19 . The turbine engine of claim 18 , wherein a first disc of the second plurality of discs on a first end of the second channel has a first radius from an outer edge of the first disc to the second center and a second radius from an inner edge of the second opening of the first disc to the second center, and a second disc of the second plurality of discs on a second end of the second channel has a third radius from an outer edge of the second disc to the second center and a fourth radius from an inner edge of the second opening of the second disc to the second center, wherein the first radius and the third radius are equal.
  20. 20 . The turbine engine of claim 19 , wherein the second radius and the fourth radius are equal.

Description

RELATED APPLICATION This patent arises from a continuation of U.S. patent application Ser. No. 18/420,337, filed on Jan. 23, 2024. U.S. patent application Ser. No. 18/420,337 is hereby incorporated herein by reference in its entirety. Priority to U.S. patent application Ser. No. 18/420,337 is hereby claimed. FIELD OF THE DISCLOSURE This disclosure relates generally to acoustic damping and, more particularly, to an acoustic damping device for a gas turbine engine. BACKGROUND During operation, aircraft engines, automobile engines, generators, etc., produce vibrations. Vibration-producing devices can include additional hardware structures to dissipate resonant frequencies caused by the vibrations, as such frequencies can cause damage to the vibration-producing device. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a cross-sectional view of an example gas turbine engine in which examples disclosed herein may be implemented. FIG. 2 is a partial cross-sectional view of a first example acoustic damping device. FIG. 3 is a partial cross-sectional view of a second example acoustic damping device. FIG. 4 is a cross-sectional view of a third example acoustic damping device. FIG. 5 is a schematic drawing of an example fuel manifold that can be implemented on the example gas turbine engine of FIG. 1 using any of the example acoustic damping devices of FIGS. 2-4. FIGS. 6A-6C show schematic drawings of example placements of the example acoustic damping devices of FIGS. 2-4 on the example fuel manifold of FIG. 5. FIG. 7 is a cross-sectional view of an example combustion section of the example gas turbine engine of FIG. 1 utilizing the example acoustic damping device of any of FIGS. 2-4. FIG. 8 is an example quarter wave tube combustion section which can be implemented on the example gas turbine engine of FIG. 1 FIG. 9 is a first example arrangement of the acoustic damping device of FIGS. 2-4 in the example quarter wave tube combustion section of FIG. 8. FIG. 10 is a second example arrangement of the acoustic damping device of FIGS. 2-4 in the example quarter wave tube combustion section of FIG. 8. FIG. 11 illustrates an example cooling flow arrangement of the acoustic damping device of FIGS. 2-4 according to the second example arrangement of FIG. 10. DETAILED DESCRIPTION In general, the same reference numbers will be used throughout the drawing(s) and accompanying written description to refer to the same or like parts. The figures are not necessarily to scale. Instead, the thickness of the layers or regions may be enlarged in the drawings. Although the figures show layers and regions with clean 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. “Including” and “comprising” (and all forms and tenses thereof) are used herein to be open ended terms. Thus, whenever a claim employs any form of “include” or “comprise” (e.g., comprises, includes, comprising, including, having, etc.) as a preamble or within a claim recitation of any kind, it is to be understood that additional elements, terms, etc., may be present without falling outside the scope of the corresponding claim or recitation. As used herein, when the phrase “at least” is used as the transition term in, for example, a preamble of a claim, it is open-ended in the same manner as the term “comprising” and “including” are open ended. The term “and/or” when used, for example, in a form such as A, B, and/or C refers to any combination or subset of A, B, C such as (1) A alone, (2) B alone, (3) C alone, (4) A with B, (5) A with C, (6) B with C, or (7) A with B and with 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 implementations including any 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 implementations including any 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 implementations including any 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 implementations including any 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, singular references (e.g., “a”, “an”, “first”, “second”, etc.) do not exclude a plurality. The term “a” or “an” object, a