Dome Integrated Acoustic Damper for Gas Turbine Combustor Applications

Abstract

A burner includes an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integral with the annular dome and is movable to adjust the volume of the cavity, thereby adjusting the frequency of each of the plurality of dampers to reduce the acoustic amplitude of the burner.

Description

Technical Field

[0001] The present disclosure relates generally to combustors, and in particular, to an acoustic damper integrated into a dome of a combustor and a combustor having an acoustic damper. Background Art

[0002] An engine, particularly a gas or combustion turbine engine, is a rotating engine that extracts energy from the flow of combustion gases through the engine onto a plurality of turbine blades. Turbine engines have been used for land and marine sports and for power generation. Turbine engines are commonly used in aviation applications, such as for aircraft, including helicopters and airplanes. In aircraft, turbine engines are used to propel the aircraft. In land applications, turbine engines are commonly used to generate electricity.

[0003] A turbine engine includes a fuel-air mixer assembly for mixing fuel and air in a combustion chamber of the turbine engine. The fuel-air mixer assembly includes an air swirler. The performance of the burner in the combustion chamber plays an important role in the overall performance of the gas turbine engine.

[0004] In the combustion of liquid fuel or gaseous fuel in the combustion chamber of a gas turbine, the fuel and combustion air are injected into the burner separately and mixed in the combustion chamber or injected as uniformly as possible and then fed into the combustion chamber. In order to take environmental factors into consideration, attention is paid to reducing the flame temperature by a large amount of excess air to reduce the formation of nitrogen oxides (NOx).

[0005] In the combustion chamber, air and fuel flow fluctuations occur due to the specific fuel and combustion system architecture. These fluctuations can cause the flame to respond and can establish a so-called thermoacoustic feedback loop. As a result, large oscillation amplitudes or vibration amplitudes can occur, where the gas turbine reaches the limits of its mechanical load or stability. To prevent this phenomenon, dampers are used to reduce the oscillation or vibration amplitude. The dampers act as Helmholtz resonators, which can be tuned in terms of damping frequency depending on the oscillation amplitude to be damped. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] The foregoing and other features and advantages will become apparent from the following more particular description of various exemplary embodiments as illustrated in the accompanying drawings, in which like reference numerals generally indicate identical, functionally similar, and / or structurally similar elements.

[0007] Figure 1 is a schematic diagram of a turbine engine according to an embodiment of the present disclosure.

[0008] Figure 2A is a cross-sectional view of a portion of a combustor of a combustor assembly of a turbine engine according to an embodiment of the present disclosure.

[0009] Figure 2Bis a cross-sectional view of a portion of a combustor of a combustor assembly of a turbine engine according to another embodiment of the present disclosure.

[0010] Figure 3 is a schematic front view of a segment of a combustor showing the locations of a plurality of dampers according to an embodiment of the present disclosure.

[0011] Figure 4 is a schematic rear view of a segment of a combustor showing the location of a damper according to an embodiment of the present disclosure.

[0012] Figure 5 is a schematic side (cross-sectional) view of a segment of a combustor showing the location of a damper among a plurality of dampers according to an embodiment of the present disclosure.

[0013] Figure 6 is a schematic side (cross-sectional) view of a segment of a combustor showing another position of a damper among a plurality of dampers according to an embodiment of the present disclosure.

[0014] Figure 7 is a generalized graph of the acoustic reflection coefficient of a cavity of a damper according to an embodiment of the present disclosure versus a target frequency of the damper for use as a Helmholtz resonator.

[0015] Figure 8 is a generalized graph of the acoustic reflection coefficient of a cavity of a damper versus a target frequency of the damper for use as a Helmholtz resonator for a particular volume of the cavity of the damper in accordance with an embodiment of the present disclosure.

[0016] Fig. 9 is a generalized graph of the acoustic pressure response of a combustor versus a target frequency with and without a plurality of dampers in accordance with an embodiment of the present disclosure. DETAILED DESCRIPTION

[0017] Additional features, advantages and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings and claims. In addition, it should be understood that the above overview and the following detailed description of the present disclosure are exemplary and are intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0018] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0019] In the following specification and claims, reference to the word "optional" or "optionally" means that the subsequently described event or circumstance may or may not occur, and that the description includes instances where the event occurs and instances where it does not.

[0020] As used throughout the specification and claims, approximate language may be applied to modify any quantitative representation that allows variation without causing a change in the basic function associated therewith. Therefore, the values ​​modified by terms such as "about", "approximately" and "substantially" are not limited to the precise values ​​specified. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Here and throughout the specification and claims, range limitations may be combined and / or interchanged. Unless the context or language indicates otherwise, such ranges are identified and include all subranges contained therein.

[0021] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of a turbine engine or combustor. In addition, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of a turbine engine or a fuel-air mixer assembly. In addition, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc around the centerline of a turbine engine or a fuel-air mixer assembly. As understood herein, a turbine engine includes, for example, a turbojet engine, a turboprop engine, a turbofan engine, or a turboshaft engine.

[0022] Embodiments of the present disclosure seek to effectively reduce acoustic pressure fluctuations by using a tuned air cavity in the form of a Helmholtz resonator. By using a tuned air cavity, unexpected high acoustic pressure oscillations in the combustion chamber can be reduced. As a result, the operational and structural robustness of the combustion chamber can be enhanced. In addition, by providing a small purge air flow, the damping performance of the damper cavity can be improved. The embedded damper cavity and damper neck can be fully integrated with the combustor dome structure. The design of the damper cavity makes the system flow naturally. That is, the damper cavity can be designed so that the air flow is not substantially affected by the presence of the damper cavity.

[0023] By integrating an adjustable damper cover and an embedded damper portion of the damper within a dome structure of the combustion chamber, fewer parts are used and the overall weight of the combustor can be reduced compared to conventional damper constructions. The integration can be achieved by utilizing unused space under the dome structure. The provided damper cover can be configured to enable tuning of the damper frequency within a specific frequency range. Based on the identified unstable frequencies, the damper target frequency can be adjusted and the acoustic pressure oscillations can be reduced.

[0024] Figure 1is a schematic diagram of a turbine engine 10 according to an embodiment of the present disclosure. The turbine engine 10 includes a fan assembly 12, a low pressure and / or booster compressor (LPC) assembly 14, a high pressure compressor (HPC) assembly 16, and a combustor assembly 18. The fan assembly 12, the booster compressor assembly 14, the high pressure compressor assembly 16, and the combustor assembly 18 are connected in flow communication. The turbine engine 10 also includes a high pressure turbine assembly 20 connected in flow communication with the combustor assembly 18 and a low pressure turbine (LPT) assembly 22. The fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26. The low pressure turbine assembly 22 is coupled to the fan assembly 12 and the booster compressor assembly 14 by a first drive shaft 28, and the high pressure turbine assembly 20 is coupled to the high pressure compressor assembly 16 by a second drive shaft 30. The turbine engine 10 has an air inlet 32 ​​and an exhaust port 34. Turbine engine 10 also includes a centerline (axis) 36 about which fan assembly 12 , boost compressor assembly 14 , high pressure compressor assembly 16 , and high pressure turbine assembly 20 and low pressure turbine assembly 22 rotate.

[0025] In operation, air entering turbine engine 10 through air intake 32 is directed through fan assembly 12 toward booster compressor assembly 14. Compressed air is discharged from booster compressor assembly 14 toward high pressure compressor assembly 16. The highly compressed air is directed from high pressure compressor assembly 16 toward combustor assembly 18, mixed with fuel, and the air and fuel mixture is combusted within combustor assembly 18. The high temperature combustion gases produced by combustor assembly 18 are directed toward high pressure turbine assembly 20 and low pressure turbine assembly 22. The combustion gases are then discharged from turbine engine 10 via exhaust 34.

[0026] Figure 2A According to the embodiment of the present disclosure Figure 1 1 is a cross-sectional view of a portion of a combustor 38 of a combustor assembly 18 of a turbine engine 10 of FIG. The combustor 38 defines a combustion chamber 40 in which fuel is mixed with compressed air and combusted. The combustor 38 includes an outer liner 42 and an inner liner 44. The outer liner 42 defines an outer boundary of the combustion chamber 40, and the inner liner 44 defines an inner boundary of the combustion chamber 40. An annular dome 46 is mounted upstream of the outer liner 42 and the inner liner 44 and defines an upstream end of the combustion chamber 40. One or more fuel injection systems 48 are positioned on the annular dome 46. In an embodiment, each fuel injection system 48 includes a fuel nozzle assembly 50 and a fuel-air mixer assembly 52 coupled to the fuel nozzle assembly 50. The fuel-air mixer assembly 52 includes an air swirler 53. The fuel-air mixer assembly 52 receives fuel from the fuel nozzle assembly 50 and receives air from the high pressure compressor assembly 16 ( Figure 1The combustor 38 is adapted to be used in a partially premixed system (TAPS).

[0027] Figure 2B According to another embodiment of the present disclosure Figure 1 1 is a cross-sectional view of a portion of a combustor 39 of a combustor assembly 18 of a turbine engine 10 of FIG. The combustor 39 is adapted for a rich-quick-lean (RQL) system. The combustor 39 defines a combustion chamber 41 in which fuel is mixed with compressed air and combusted. The combustor 39 includes an outer liner 43 and an inner liner 45. The outer liner 43 defines an outer boundary of the combustion chamber 40, and the inner liner 45 defines an inner boundary of the combustion chamber 41. An annular dome 47 extends between and is coupled to the outer liner 43 and the inner liner 45, and defines an upstream end of the combustion chamber 41. One or more fuel injection systems 49 are positioned on the annular dome 47. In an embodiment, each fuel injection system 49 includes a fuel nozzle assembly 51 and a fuel-air mixer assembly 55 coupled to the fuel nozzle assembly 51. The fuel-air mixer assembly 55 includes an air swirler 57. The fuel-air mixer assembly 55 receives fuel from the fuel nozzle assembly 51, receives air from the high pressure compressor assembly 16 (such as via a diffuser 59), and receives air from the high pressure compressor assembly 16 (such as via a diffuser 59). Figure 1 The dilution air is introduced into the combustion chamber 41 primarily through a plurality of circumferentially spaced dilution holes 58 extending through each of the outer liner 43 and the inner liner 45, as shown in FIG. Figure 2B As shown by the dotted arrow in the figure, the fuel-air mixture is further mixed with the fuel in the combustion chamber 41, and is ignited and burned in the combustion chamber 41.

[0028] Figure 3 is a schematic front view of a section 100 of a combustor 38 , 39 showing the locations of a plurality of dampers 102 , 104 , 106 according to an embodiment of the present disclosure. Figure 4 is a schematic rear view of a section 100 of a combustor 38 showing the locations of dampers 102 , 104 , 106 according to an embodiment of the present disclosure. Figure 3 and 4 The segment 100 shown in FIG. 2 depicts only the rear portion of the combustor 38 proximate the annular dome 46 (shown in FIG. 2 ). Figure 3 and 4The segment 100 shown in only represents half of the combustor 38. For clarity, the other half is not shown. The segment 100 of the combustor 38 has a plurality of heat shields 108. The plurality of heat shields 108 are positioned adjacent to each other. In an embodiment, the plurality of heat shields 108 have a trapezoidal shape, thereby forming an annular disk when assembled. Each of the plurality of heat shields 108 has a swirler 110. An example of a swirler 110 is shown in FIG. 2 as an air swirler 53. The air swirler 53 is a part of a fuel-air mixer assembly 52 coupled to a fuel nozzle assembly 50. The fuel nozzle assembly 50 and the fuel-air mixer assembly 52 are parts of a fuel injection system 48.

[0029] In an embodiment, the segment 100 of the combustor 38 includes a plurality of dampers 102. In an embodiment, the plurality of dampers 102 are positioned at a distal radial distance relative to a center 112 of the annular shape of the segment 100. In an embodiment, the plurality of dampers 102 are positioned at a distal radial distance relative to a center 112 of the annular domes 46, 47. In another embodiment, the segment 100 of the combustor 38 includes a plurality of dampers 106. In an embodiment, the plurality of dampers 106 are positioned at a proximal distance relative to a center 112 of the annular shape of the segment 100. In an embodiment, the plurality of dampers 102 are positioned at a proximal distance relative to a center 112 of the annular domes 46, 47. Each of the plurality of dampers 102 or the plurality of dampers 106 is disposed within each of the plurality of heat shields 108. In yet another embodiment, the segment 100 of the combustor 38 includes a plurality of dampers 104. In an embodiment, the plurality of dampers 104 are positioned at an intermediate distance relative to a center 112 of the annular shape of the segment 100. In an embodiment, the plurality of dampers 102 are located at an intermediate distance relative to a center 112 of the annular domes 46, 47 between two adjacent portions of the annular domes 46, 47. Each of the plurality of dampers 104 is disposed between two adjacent heat shields of the plurality of heat shields 108.

[0030] like Figure 3 As shown, in an embodiment, a plurality of dampers 102, 104, 106 have circular openings 102A, 104A, 106A, respectively, on the front side of the section 100 of the combustor 38 (i.e., the side of the combustor 38 that faces the combustion chamber 40 (shown in FIG. 2 ) of the combustor 38). Figure 4As shown, in an embodiment, a plurality of dampers 102, 104, 106 have polygonal (e.g., rectangular) openings 102B, 104B, 106B, respectively, on the rear side of the segment 100 of the combustor 38 (i.e., the side of the combustor 38 facing the diffuser 54 (shown in FIG. 2 )). It is understood that any configuration using a plurality of dampers 102, a plurality of dampers 104, or a plurality of dampers 106 may be used. For example, in a first embodiment, a plurality of dampers 102 are used. In a second embodiment, a plurality of dampers 106 are used. In a third embodiment, a plurality of dampers 104 are used. However, in other embodiments, any combination of a plurality of dampers 102, a plurality of dampers 104, or a plurality of dampers 106 may be used.

[0031] Figure 5 According to the embodiment of the present disclosure Figure 3 and Figure 4 2 is a schematic side (cross-sectional) view of a section 100 of a combustor 38, showing the location of a damper 103 among a plurality of dampers 102. The damper 103 defines a damper cavity 103C that is integral with the annular dome 46 (also shown in FIG. 2 ). Figure 5 As shown, the damper 103 is located at a radial distance above the swirler 110. Figure 5 As shown, each of the plurality of heat shields 108 is coupled to the annular dome 46. In an embodiment, the plurality of heat shields 108 are located on the hot front side of the annular dome 46. The damper 103 has a damper neck 103A, which is arranged to pass through the annular dome 46 and each of the plurality of heat shields 108. The damper neck 103A opens to the front side of the downstream of the swirler 110, i.e., the side of the burner 38 facing the combustion chamber 40 of the burner 38, through an opening 103F. In an embodiment, the opening 103F of the damper neck 103A has a circular shape, such as Figure 4 As shown. However, the damper neck 103A can have any other shape (e.g., elliptical, polygonal, etc.). The damper 103 has a damper portion 103D that is integral with the annular dome 46. The damper 103 has a damper cover 103B mounted to the damper portion 103D. Therefore, the damper cover 103B is mounted to the annular dome 46. The damper cover 103B is disposed on the cold rear side of the combustor 38 facing the diffuser 54. The damper cover 103B together with the damper portion 103D define a damper chamber 103C of the damper 103. The damper cover 103B of the damper 103 is adjustable to modify the total volume of the damper chamber 103C of the damper 103. The damper chamber 103C of the damper 103 is connected to the combustor cold side through one or more purge air holes 103E (only one is shown) provided in the damper cover 103B.

[0032] Figure 6According to the embodiment of the present disclosure Figure 3 and Figure 4 FIG. 1 is a schematic side (cross-sectional) view of a section 100 of a combustor 38 of FIG. 1 , showing another location of a damper 103 in a plurality of dampers 102. Figure 6 As shown, the damper cover 103B can be extended to a first position P1 to define a first volume of the damper chamber 103C. Figure 6 As shown, the damper cover can be extended to a second position P2 to define a second volume greater than the first volume of the damper cavity 103C. By adjusting the volume of the damper cavity 103C, the frequency of the damper 103 acting as a Helmholtz resonator can be adjusted, which will be explained in further detail in the following paragraphs.

[0033] Figure 7 According to the embodiment of the present disclosure Figure 5 and Figure 6 A general graph of the relationship between the acoustic reflection coefficient of the damper 103 and the target frequency of the damper 103 used as a Helmholtz resonator. Curve "V1" corresponds to the relationship between the acoustic reflection coefficient and the target frequency of the damper 103 when the damper chamber 103C has a first volume V1. Curve "V2" corresponds to the relationship between the acoustic reflection coefficient and the target frequency of the damper 103 when the damper chamber 103C has a second volume V2. Curve "V3" corresponds to the relationship between the acoustic reflection coefficient and the target frequency of the damper 103 when the damper chamber 103C has a third volume V3. Volume V3 is greater than volume V2, and volume V2 is greater than volume V1 (i.e., V3>V2>V1). Curves "V1", "V2" and "V3" show the minimum values ​​of the acoustic reflection coefficient at a certain target frequency. The minimum value of curve "V1" of volume V1 occurs at frequency F1. The minimum value of the curve "V2" of volume V2 occurs at frequency F2. The minimum value of the curve "V3" of volume V3 occurs at frequency F3. Frequency F1 is greater than frequency F2, and frequency F2 is greater than frequency F3 (i.e., F1>F2>F3). Therefore, the larger the volume of the cavity 103C of the damper 103, the lower the frequency of the damper 103.

[0034] Figure 8 is a general graph of the acoustic reflection coefficient of the total volume of the damper cavity 103C of the damper 103 versus the target frequency of the damper 103 used as a Helmholtz resonator for a specific volume of the damper cavity 103C of the damper 103 according to an embodiment of the present disclosure. The graph represents the damper performance as a function of frequency. The curve "V1" in the graph corresponds to the acoustic reflection coefficient versus the target frequency of the damper 103 when the damper cavity 103C has a first volume V1. The minimum of the curve "V1" for volume V1 occurs at frequency F1. The minimum of the acoustic reflection response indicates that the acoustic vibration is maximally damped at frequency F1.

[0035] Fig. 9 is a diagram of an embodiment of the present disclosure with and without multiple dampers 102 Figure 3 and Figure 4 1 is a general numerical plot of the acoustic pressure response of the combustor 38 versus a target frequency. The curve labeled "No Damper" corresponds to the pressure response of the combustor 38 as a function of frequency without the use of the plurality of dampers 102. The curve labeled "Damper" corresponds to the pressure response of the combustor 38 as a function of frequency when the plurality of dampers 102 are used. The plurality of dampers 102 are tuned to a frequency F1. As shown in FIG. Figure 8 As shown, when multiple dampers 102 are used, the acoustic pressure P' may be reduced. Although the pressure or acoustic response reduction in the combustor 38 is shown when multiple dampers 102 are used, multiple dampers 104 and / or multiple dampers 106 may perform similarly and may be used to reduce pressure fluctuations in the combustor 38. In an embodiment, the reduction observed using multiple dampers 102, 104, and / or 106 may be as high as 50% of the unstable pressure oscillations, i.e., between 0% and 50%.

[0036] As can be appreciated from the above paragraphs, the plurality of dampers 102, 104, 106 acting as Helmholtz resonators allow for reduction of acoustic pressure oscillations. By using the tuned air cavities of the plurality of dampers 102, 104, 106, unexpected occurrences of high acoustic pressure oscillations in the combustion chamber can be reduced. As a result, the operational and structural robustness of the combustor 38 can be enhanced. In addition, by providing air flow through the damper neck 103A in each of the one or more purge air holes 103E of the dampers 102, 104, 106, the damping performance of the damper cavity 103C can be improved. Figures 3 to 6 As shown, the damper neck 103A that provides additional purge air flow may be fully integrated with the annular dome 46 .

[0037] Compared with the conventional damper structure, the cavity 103C of the damper 103, the damper neck 103A and the damper cover 103B are integrated into the annular dome 46 (see Figure 2A ), fewer parts are used and the overall weight of the combustor 38 can be reduced. Integration can be achieved by utilizing the unused space below the annular dome 46. In addition to the adjustability of the volume of the damper cavity 103C (provided by the adjustability of the volume within the damper cap 103B) to tune the frequency response of the damper 103, the additional purge air flow provided by the damper neck 103A can also be configured to be able to tune the frequency within a specific frequency range. Based on the identified unstable frequency, the damper target frequency can be adjusted and the acoustic pressure oscillations can be reduced.

[0038] The plurality of dampers 102, 104, 106 may be integrated into Figure 3 and Figure 4 The plurality of dampers 102, 104, 106 may be fully integrated with the annular domes 46, 47 as a structural part thereof. This construction is light and compact, and is convenient for use in aircraft engines. In addition, tuning of the plurality of dampers may be easily achieved by varying or changing the volume of the damper chamber 103C of each damper 103 in the plurality of dampers 102, 104, 106 (i.e., by changing the volume within the damper cover 103B by moving the damper cover 103B relative to the fixed damper portion 103D). The volume of the damper chamber 103C may be tuned or changed by moving the damper cover 103B relative to the damper portion 103D. The damper chamber 103C of the damper 103 is located on the "cooler" side of the annular dome 46, while the damper 103 is connected to the "hotter" side of the annular dome 46 via the damper neck 103A to provide a link between the sound source and the reduction or damping of the sound amplitude in the combustion chamber 40 of the combustor 38. Adding multiple dampers 102, 104, 106 to the combustor 38 extends the life of the combustor 38 while providing an additional, more mechanically rigid annular dome 46 or 47. The above configuration may be incorporated into an existing operating engine or provided in a newly manufactured engine.

[0039] As can be appreciated from the above discussion, a burner is provided. The burner includes an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integrated with the annular dome and is movable to adjust the volume of the cavity, thereby adjusting the frequency of each of the plurality of dampers to reduce the acoustic amplitude of the burner.

[0040] A combustor as recited in the preceding clause, wherein said plurality of dampeners are located at a distal radial distance relative to a center of said annular dome.

[0041] A burner as in any preceding clause, wherein the plurality of dampers are located at a proximal distance relative to a centre of the annular dome.

[0042] A burner as claimed in any preceding clause, wherein the plurality of dampers are located at an intermediate distance relative to the centre of the annular dome between two adjacent portions of the annular dome.

[0043] The combustor of any preceding clause, wherein the combustor further comprises a plurality of heat shields coupled to the annular dome and located on a hotter front side of the annular dome.The damper neck is disposed through a heat shield of the plurality of heat shields.

[0044] A burner according to any preceding clause, wherein the damper neck has an opening opening towards the hotter front side of the annular dome.

[0045] A burner as claimed in any preceding clause wherein the damper cover is located at a cooler rear side of the burner.

[0046] A burner as claimed in any preceding clause, wherein the larger the volume of the cavity, the lower the frequency of the damper.

[0047] The combustor according to any preceding clause, further comprising an inner liner and an outer liner defining a boundary of the combustion chamber. The annular dome is mounted upstream of the outer liner and the inner liner and defines an upstream end of the combustion chamber.

[0048] The combustor according to any of the above clauses, further comprising one or more fuel injection systems positioned on the annular dome, the one or more fuel injection systems comprising a fuel nozzle assembly and a fuel-air mixer assembly coupled to the fuel nozzle assembly. The fuel-air mixer assembly receives fuel from the fuel nozzle assembly, receives air, and discharges the fuel-air mixture into the combustion chamber where the fuel-air mixture is ignited and combusted.

[0049] According to another aspect of the present disclosure, a turbine engine includes a combustor having an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integral with the annular dome and is movable to adjust the volume of the cavity, thereby adjusting the frequency of each of the plurality of dampers to reduce the acoustic amplitude of the combustor.

[0050] A turbine engine as recited in the preceding clause, wherein said plurality of dampers are located at a distal radial distance relative to a center of said annular dome.

[0051] A turbine engine as claimed in any preceding clause, wherein the plurality of dampers are located at a proximal distance relative to a centre of the annular dome.

[0052] A turbine engine as claimed in any preceding clause, wherein the plurality of dampers are located at an intermediate distance relative to the centre of the annular dome between two adjacent portions of the annular dome.

[0053] The turbine engine of any preceding clause, the combustor further comprising a plurality of heat shields coupled to the annular dome and located on a hotter front side of the annular dome. The damper neck is disposed through a heat shield of the plurality of heat shields.

[0054] A turbine engine according to any preceding clause, wherein the damper neck has an opening opening towards the hotter front side of the annular dome.

[0055] A turbine engine as claimed in any preceding clause, wherein the damper cover is located on a cooler rear side of the combustor.

[0056] A turbine engine as claimed in any preceding clause, wherein the larger the volume of the cavity, the lower the frequency of the damper.

[0057] The turbine engine according to any preceding clause, further comprising an inner liner and an outer liner defining the boundaries of the combustion chamber. The annular dome is mounted upstream of the outer liner and the inner liner and defines an upstream end of the combustion chamber.

[0058] The turbine engine of any preceding clause, further comprising one or more fuel injection systems positioned on the annular dome, the one or more fuel injection systems comprising a fuel nozzle assembly and a fuel-air mixer assembly coupled to the fuel nozzle assembly. The fuel-air mixer assembly receives fuel from the fuel nozzle assembly, receives air, and discharges the fuel-air mixture into the combustion chamber where the fuel-air mixture is ignited and combusted.

[0059] Although the foregoing description is directed to preferred embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that: include: Ring-shaped dome; as well as a plurality of dampers integral with the annular dome, each of the plurality of dampers comprising an adjustable damper cover and a damper portion integral with the annular dome and defining a cavity having a volume, wherein the adjustable damper cover is mounted to the damper portion and is movable to adjust the volume of the cavity to adjust the frequency of each of the plurality of dampers to reduce the acoustic amplitude of the combustor, and wherein the adjustable damper cover includes one or more purge holes connecting the cavity to a cold side of the combustor.

2. The burner according to claim 1, characterized in that in, The plurality of dampeners are located at a distal radial distance relative to a center of the annular dome.

3. The burner according to claim 1, characterized in that in, The plurality of dampeners are located at a proximal distance relative to a center of the annular dome.

4. The burner according to claim 1, characterized in that in, The plurality of dampers are located at an intermediate distance relative to a center of the annular dome between two adjacent portions of the annular dome.

5. The burner according to claim 1, characterized in that in, The damper cover is located at the rear side of the burner.

6. The burner according to claim 1, characterized in that in, The larger the volume of the cavity, the lower the frequency of the damper.

7. The burner according to claim 1, characterized in that Further included is a plurality of heat shields coupled to the annular dome and located on a front side of the annular dome, wherein the damper neck is disposed through a heat shield of the plurality of heat shields.

8. The burner according to claim 7, characterized in that in, The damper neck has an opening that opens toward the front side of the annular dome.

9. The burner according to claim 1, characterized in that Further included are an inner liner and an outer liner defining a boundary of a combustion chamber, wherein the annular dome is mounted upstream of the outer liner and the inner liner and defines an upstream end of the combustion chamber.

10. The burner according to claim 9, characterized in that Further comprising one or more fuel injection systems positioned on the annular dome, the one or more fuel injection systems comprising a fuel nozzle assembly and a fuel-air mixer assembly coupled to the fuel nozzle assembly, wherein the fuel-air mixer assembly receives fuel from the fuel nozzle assembly, receives air, and discharges the fuel-air mixture into the combustion chamber where the fuel-air mixture is ignited and combusted.

11. A turbine engine, characterized in that: include: A burner, comprising: (a) Annular dome; as well as (b) a plurality of dampers integral with the annular dome, each of the plurality of dampers comprising an adjustable damper cover and a damper portion integral with the annular dome and defining a cavity having a volume, wherein the adjustable damper cover is mounted to the damper portion and is movable to adjust the volume of the cavity to adjust the frequency of each of the plurality of dampers to reduce the acoustic amplitude of the combustor, and wherein the adjustable damper cover includes one or more purge holes connecting the cavity to a cold side of the combustor.

12. The turbine engine according to claim 11, characterized in that in, The plurality of dampeners are located at a distal radial distance relative to a center of the annular dome.

13. The turbine engine according to claim 11, characterized in that in, The plurality of dampeners are located at a proximal distance relative to a center of the annular dome.

14. The turbine engine according to claim 11, characterized in that in, The plurality of dampers are located at an intermediate distance relative to a center of the annular dome between two adjacent portions of the annular dome.

15. The turbine engine according to claim 11, characterized in that in, The damper cover is located at the rear side of the burner.

16. The turbine engine according to claim 11, characterized in that in, The larger the volume of the cavity, the lower the frequency of the damper.

17. The turbine engine according to claim 11, characterized in that Further included is a plurality of heat shields coupled to the annular dome and located on a front side of the annular dome, wherein the damper neck is disposed through a heat shield of the plurality of heat shields.

18. The turbine engine according to claim 17, characterized in that in, The damper neck has an opening that opens toward the front side of the annular dome.

19. The turbine engine according to claim 11, characterized in that Further included are an inner liner and an outer liner defining a boundary of a combustion chamber, wherein the annular dome is mounted upstream of the outer liner and the inner liner and defines an upstream end of the combustion chamber.

20. The turbine engine according to claim 19, characterized in that Further comprising one or more fuel injection systems positioned on the annular dome, the one or more fuel injection systems comprising a fuel nozzle assembly and a fuel-air mixer assembly coupled to the fuel nozzle assembly, wherein the fuel-air mixer assembly receives fuel from the fuel nozzle assembly, receives air, and discharges the fuel-air mixture into the combustion chamber where the fuel-air mixture is ignited and combusted.

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