Acoustic damper for a burner

Abstract

A combustor liner has an outer liner and an inner liner defining a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer and inner liners each have a converging-diverging section extending into the dilution zone of the combustion chamber and forming a throat therebetween. A bridge member extends through the converging-diverging sections to form a damper cavity therebetween. Each converging-diverging section includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member located on a downstream portion of the converging-diverging section, such that an acoustic damper is defined by the converging-diverging sections, the bridge, and the damper inlet feed. The acoustic damper suppresses the acoustic characteristics of the combustor.

Description

Technical Field

[0001] This disclosure relates to an acoustic damper for a combustor in a gas turbine engine. Background Technology

[0002] In the combustion section of a turbine engine, the fuel-air mixture is ignited to produce combustion products. In some combustors, air flows through an outer channel surrounding the outer liner and an inner channel surrounding the inner liner, and is transferred as dilution air into the combustion chamber through dilution orifices in the outer and inner liners. The combustion of the fuel-air mixture and the mixing of dilution air with combustion products can generate thermoacoustic oscillations in the combustor, leading to high noise levels and mechanical damage during turbine engine operation. Attached Figure Description

[0003] The features, advantages, and embodiments of this disclosure will become apparent from the following more specific description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar, and / or structurally similar elements.

[0004] Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine according to an embodiment of the present disclosure.

[0005] Figure 2 This is a cross-sectional side view of an exemplary combustion section according to an embodiment of the present disclosure.

[0006] Figure 3 A partial cross-sectional side view of an exemplary convergent-divergent portion of a burner bushing including an acoustic damper, according to aspects of this disclosure, is depicted.

[0007] Figure 4 An exemplary cross-section of a Helmholtz resonant damper according to aspects of this disclosure is depicted.

[0008] Figure 5 A partial cross-sectional side view of an exemplary convergent-divergent portion of a burner bushing including an acoustic damper, according to another aspect of this disclosure, is depicted.

[0009] Figure 6 Depicting aspects according to this disclosure in Figure 1 and Figure 2 A partial cross-sectional rear view of the annular burner taken at plane AA.

[0010] Figure 7 Depicting aspects according to this disclosure in Figure 1 and Figure 2 A partial cross-sectional rear view of the annular burner taken at plane AA.

[0011] Figure 8 It is a flowchart depicting the process steps of a method for operating the combustion zone according to aspects of this disclosure. Detailed Implementation

[0012] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0013] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from the spirit and scope of this disclosure.

[0014] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0015] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows out, while "downstream" is the direction in which it flows.

[0016] In the combustion section of a turbine engine, the fuel-air mixture is ignited to produce combustion products. In some combustors, air flows through an outer channel surrounding the outer liner and an inner channel surrounding the inner liner, and enters the combustion chamber as dilution air through dilution orifices in the outer and inner liners. The combustion of the fuel-air mixture and the mixing of dilution air with combustion products can generate thermoacoustic oscillations, resulting in high noise levels and mechanical damage during turbine engine operation.

[0017] This disclosure aims to suppress certain thermoacoustic characteristics by providing an outer and inner liner with an integrated Helmholtz resonant damper in a burner bushing having a convergent-divergent structure. According to one aspect of this disclosure, a burner including an annular burner bushing has an outer liner and an inner liner defining a combustion chamber therebetween, the combustion chamber having a dilution zone. Each outer and inner liner has a convergent-divergent section extending into the dilution zone of the combustion chamber and forming a throat therebetween. A bridge member extends through the convergent-divergent section to form a damper cavity therebetween. Each convergent-divergent section includes at least one dilution opening at the throat through the respective convergent-divergent section and includes a damper inlet supply member on a downstream portion of the convergent-divergent section. An acoustic damper is defined by the convergent-divergent section, the bridge, and the damper inlet supply. The acoustic damper suppresses acoustic oscillations in the combustion chamber. Therefore, a unique bushing structure can be used to form an integrated acoustic damper.

[0018] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10 (referred to herein as "engine 10"), which may be incorporated into various embodiments of this disclosure. Although further description is given below with reference to turbofan engines, this disclosure is also applicable to general turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, the engine 10 has a longitudinal or axial centerline axis 12 for reference purposes, which extends from an upstream end 98 through the engine 10 to a downstream end 99. Generally, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0019] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms a compressor section in a series flow relationship, the compressor section having a supercharger or low-pressure (LP) compressor 22, a high-pressure (HP) compressor 24; a combustion section 26; a turbine section including a high-pressure (HP) turbine 28, a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. A high-pressure (HP) rotor shaft 34 drivesly connects the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drivesly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In a specific embodiment, as... Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, for example, in an indirect drive configuration or a gear drive configuration. In other embodiments, although not shown, the engine 10 may also include an intermediate pressure (IP) compressor and a turbine that can rotate with the intermediate pressure shaft.

[0020] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan shroud or nacelle 44 circumferentially surrounds at least a portion of the fan assembly 14 and / or the core engine 16. In one embodiment, the nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. Furthermore, at least a portion of the nacelle 44 may extend externally above the core engine 16 to define a bypass airflow passage 48 therebetween.

[0021] Figure 2 Is it like this? Figure 1 A cross-sectional side view of an exemplary combustion section 26 of the core engine 16 shown. Figure 2As shown, combustion section 26 typically includes an annular combustor assembly 50 having a combustor bushing 51 and a dome assembly 56. The combustor bushing 51 includes an inner liner 52 and an outer liner 54, which together define a combustion chamber 62. Combustion chamber 62 may more specifically define various regions, including a primary combustion zone 70, where initial chemical reactions of the fuel-oxidant mixture and / or recirculation of combustion gases 86 may occur before further downstream flow to a dilution zone 72, where mixing and / or recirculation of combustion products and air may occur before flow to a secondary combustion zone 74, in which combustion products flow into the HP turbine 28 and the LP turbine 30. The dome assembly 56 extends radially between an upstream end 76 of the outer liner 54 and an upstream end 77 of the inner liner 52.

[0022] like Figure 2 As shown, the inner liner 52 and outer liner 54 can be encapsulated within the housing 64. A shroud 57 connects the upstream end 77 of the inner liner 52 and the upstream end 76 of the outer liner 54. An external flow passage 68 is defined between the housing 64 and the outer liner 54, and an internal flow passage 69 is defined between the housing 64 and the inner liner 52. The inner liner 52 can extend from the upstream end 77 of the dome assembly 56 to the turbine nozzle or HP turbine 28 (…). Figure 1 The inner liner 52 at the inlet of the turbine nozzle is located at its downstream end 67. The outer liner 54 may extend from the upstream end 76 of the dome assembly 56 to the downstream end 66 of the outer liner 54 at the turbine nozzle. Thus, the outer liner 54 and the inner liner 52 at least partially define the hot gas path between the combustor assembly 50 and the HP turbine 28.

[0023] like Figure 2 As will be further seen and described in more detail below, the outer liner 54 includes an outer convergent-divergent section 102, which may include a plurality of outer dilution openings 88 and at least one outer acoustic damper inlet supply member 101. The plurality of outer dilution openings 88 may be a plurality of outer dilution orifices through the outer liner 54. Similarly, the inner liner 52 includes an inner convergent-divergent section 104, which may include a plurality of inner dilution openings 90 and at least one inner acoustic damper inlet supply member 103. The plurality of inner dilution openings 90 may also be a plurality of inner dilution orifices through the inner liner 52. As will be described in more detail below, the outer dilution openings 88 and the inner dilution openings 90 provide a flow of compressed air 82(c) through which enters the combustion chamber 62. The compressed air flow 82(c) can thus be used to quench the combustion gases 86 in the dilution zone 72 downstream of the primary combustion zone 70, thereby producing diluted combustion gases 87 that are cooled before entering the turbine section.

[0024] like Figure 2As will be further seen and described in more detail below, the outer bridge member 92 provides a bridge across the outer convergent-divergent section 102, and the inner bridge member 94 provides a bridge across the inner convergent-divergent section 104. The outer bridge member 92 may include a plurality of outer bridge openings 93 therethrough, while the inner bridge member 94 may include a plurality of inner bridge openings 95 therethrough. An outer acoustic damper cavity 96 is defined between the outer bridge member 92 and the outer convergent-divergent section 102, and an inner acoustic damper cavity 97 is defined between the inner bridge member 94 and the inner convergent-divergent section 104. As will be discussed below... Figure 3 As discussed, the external acoustic damper cavity 96 defines the volume of the external acoustic damper 143 (described below), and the internal acoustic damper cavity 97 defines the volume of the internal acoustic damper 145 (described below). The external bridge opening 93 allows compressed air flow 82(c) to enter the external acoustic damper cavity 96 from the external flow passage 68 through the external bridge member 92, and then the compressed air flow enters the dilution zone 72 of the combustion chamber 62 through the external dilution opening 88. Similarly, the internal bridge opening 95 allows compressed air flow 82(c) to enter the internal acoustic damper cavity 97 from the internal flow passage 69, and then the compressed air flow enters the dilution zone 72 of the combustion chamber 62 through the internal dilution opening 90.

[0025] During the operation of engine 10, common reference Figure 1 and Figure 2 As indicated schematically by the arrows, a volume of air 73 enters the engine 10 from the upstream end 98 through the relevant inlet 75 of the nacelle 44 and / or fan assembly 14. As the volume of air 73 passes through the fan blades 42, a portion of the air (as indicated schematically by arrow 78) is directed into or routed to the bypass airflow passage 48, while another portion of the air (as indicated schematically by arrow 80) is directed into or routed to the LP compressor 22. The air portion 80 is gradually compressed as it flows through the LP and HP compressors 22, 24 towards the combustion section 26. Figure 2 As shown, the compressed air, schematically indicated by arrow 82, flows through the compressor outlet guide vane (CEGV) (not shown) and through the pre-diffuser (not shown) into the diffuser chamber 84 of the combustion section 26.

[0026] Compressed air 82 pressurizes diffuser cavity 84. As schematically indicated by arrow 82(a), a first portion of the compressed air 82 flows from diffuser cavity 84 through the opening of shroud 57 and into pressure chamber 65, where it is then swirled and mixed with fuel supplied by fuel nozzle assembly 58 and fuel-air mixer assembly 60 to produce a swirling fuel-air mixture, which is then ignited and burned to produce combustion gases 86 within the primary combustion zone 70 of combustion chamber 62. Typically, LP and HP compressors 22, 24 supply more compressed air to diffuser cavity 84 than is required for combustion. Therefore, as schematically indicated by arrow 82(b), a second portion of the compressed air 82 can be used for various purposes other than combustion. For example, as... Figure 2 As shown, compressed air 82(b) can be directed into the outer flow channel 68 and the inner flow channel 69. A portion of the compressed air 82(b) can then be directed through the outer bridge opening 93 into the outer acoustic damper cavity 96, and through the outer dilution opening 88 (schematically shown as compressed air 82(c)) into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gas 86 in the dilution zone 72, thereby producing diluted combustion gas 87. The compressed air 82(c) flowing into the dilution zone 72 can also provide turbulence to the combustion gas 86 flow to provide better mixing of the diluted oxidant gas (e.g., compressed air 82(c)) with the combustion gas 86. A similar compressed air flow 82(c) from the inner flow channel 69 flows through the inner bridge opening 95 into the inner acoustic damper cavity 97, and through the inner dilution opening 90 into the dilution zone 72 of the combustion chamber 62. Alternatively, at least a portion of the compressed air 82(b) can be directed out of the diffuser cavity 84. For example, a portion of the compressed air 82(b) may be directed through various flow channels to provide cooling air delivery to at least one of the HP turbine 28 or LP turbine 30.

[0027] Still refer to Figure 1 and Figure 2 Combustion gases 86 generated in combustion chamber 62 flow from burner assembly 50 into HP turbine 28, causing HP rotor shaft 34 to rotate, thereby supporting the operation of HP compressor 24. Figure 1 As shown, combustion gases 86 are also guided through the LP turbine 30, causing the LP rotor shaft 36 to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gases 86 are then exhausted through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0028] As will be described in more detail below, the burner bushing 51 includes a burner bushing convergence-divergence section 100. The burner bushing convergence-divergence section 100 includes an outer convergence-divergence section 102 in the dilution zone 72 of the combustion chamber 62 and an inner convergence-divergence section 104 in the dilution zone 72 of the combustion chamber 62. One purpose of the burner bushing convergence-divergence section 100 is to provide better quenching of the deeper combustion gases 86 within the dilution zone 72 to reduce NOx emissions. Additionally, as will be discussed below... Figure 3 As described, the outer convergent-divergent section 102 forms part of the outer acoustic damper 143, and the inner convergent-divergent section 104 forms part of the inner acoustic damper 145. The outer acoustic damper 143 and the inner acoustic damper 145 are typically arranged as Helmholtz acoustic dampers to suppress the acoustic characteristics of the burner 50.

[0029] Figure 3 This is a partial cross-sectional side view of a burner bushing convergence-divergence section 100 with an acoustic damper according to an aspect of this disclosure. The burner bushing convergence-divergence section 100 includes an outer convergence-divergence segment 102 and an inner convergence-divergence segment 104, each of which will be described in more detail below. Both the outer convergence-divergence segment 102 and the inner convergence-divergence segment 104 extend circumferentially about the burner centerline 112 and also extend longitudinally L relative to the burner centerline 112. Here, the burner centerline 112 may be the same as the engine centerline 12. A dilution zone 72 is defined between the outer convergence-divergence segment 102 and the inner convergence-divergence segment 104.

[0030] from Figure 3 As can be seen, the outer convergence-divergence section 102 (hereinafter referred to as the "OCD section") extends from the upstream end 108 of the OCD section 102 to the downstream end 120 of the OCD section 102. The OCD section 102 also extends radially inward and downstream along the longitudinal direction relative to the burner centerline 112, and then radially outward and downstream along the longitudinal direction relative to the burner centerline 112. Similarly, the inner convergence-divergence section 104 (hereinafter referred to as the "ICD section") generally extends from the upstream end 128 of the ICD section 104 to the downstream end 138 of the ICD section 104. The ICD section 104 also extends radially outward and downstream along the longitudinal direction relative to the burner centerline 112, and then radially inward and downstream along the longitudinal direction relative to the burner centerline 112. Specific portions of the outer liner 54 and inner liner 52 that may form the OCD section 102 and the ICD section 104 will be described in more detail below. Both OCD section 102 and ICD section 104 extend into the dilution zone 72 of combustion chamber 62 and are generally radially opposite each other across combustion chamber 62.

[0031] OCD section 102 includes at least one external dilution opening 88 defined through OCD section 102 for providing an oxidant flow (i.e., compressed air 82(c)) through OCD section 102 to dilution zone 72 of combustion chamber 62. Similarly, ICD section 104 includes at least one internal dilution opening 90 defined through ICD section 104 for providing an oxidant flow (i.e., compressed air 82(c)) through ICD section 104 to dilution zone 72 of combustion chamber 62.

[0032] Still referencing Figure 3 The OCD section 102 can generally be considered as a continuous topography becoming part of the outer liner 54, and can be considered as comprising three general parts: a converging part, a diverging part, and a transition part. More specifically, the OCD section 102 includes an OCD section converging part 106 that converges radially inward and longitudinally downstream relative to the burner centerline 112 from the upstream end 108 of the OCD section 102 to the upstream end 110 of the OCD section transition part 114 into the combustion chamber 62. The OCD section converging part 106 may be semi-circular in shape, with its center 111 located within the combustion chamber 62. Alternatively, the OCD section converging part 106 may have a parabolic or linear shape. The OCD section 102 also includes an OCD section diverging part 116 that extends radially outward and longitudinally downstream relative to the burner centerline 112 from the downstream end 118 of the OCD section transition part 114 to the downstream end 120 of the OCD section 102. The OCD section diverging portion 116 may also have a semi-circular shape, with its center 113 located within the combustion chamber 62. Alternatively, the OCD section diverging portion 116 may have a parabolic or straight shape. The OCD section transition portion 114 connects the downstream end 122 of the OCD section converging portion 106 and the upstream end 124 of the OCD section diverging portion 116. The OCD section transition portion 114 may have a parabolic shape, with its focus 107 located radially outward from the burner centerline 112. The parabolic shape of the OCD section transition portion 114 may have a width-to-depth ratio of 1:4. Alternatively, the OCD section transition portion 114 may have a semi-circular or straight shape. Therefore, the upstream portion 121 of the OCD segment 102, defined by at least a portion of the OCD segment convergence portion 106 and the OCD segment transition portion 114, extends radially inward and downstream relative to the burner centerline 112, and the downstream portion 123 of the OCD segment 102, defined by at least a portion of the OCD segment transition portion 114 and the OCD segment divergence portion 116, extends radially outward and downstream relative to the burner centerline 112.

[0033] exist Figure 3 In the image, the outer bridge component 92 can be seen connected to the outer liner 54. (The last sentence appears to be incomplete and unrelated to the preceding text.) Figure 3 In the aspects of this disclosure shown, the outer bridge member 92 is connected to the radially outer surface 152 of the outer liner 54 and is configured to bridge the OCD segment 102. The outer bridge member 92 may be brazed or welded to the radially outer surface 152 at an upstream weld joint 154 and a downstream weld joint 156 of the outer liner-bridge. Alternatively, instead of brazing or welding to the radially outer surface 152, the outer bridge may be attached to the OCD segment 102 via a plurality of outer bridge support members 222. The outer bridge support members 222 may be brazed or welded to the outer bridge member 92 and may also be brazed or welded to the OCD segment 102, such that the upstream and downstream ends of the outer bridge member 92 float freely along the radially outer surface 152. As described above, the outer bridge member 92 includes a plurality of outer bridge openings 93 passing through the outer bridge member 92. The outer bridge opening 93 is arranged to provide a compressed air flow 82(c) from the outer flow channel 68 formed in the OCD section 102 to the outer acoustic damper cavity 96.

[0034] ICD segment 104 is similar to OCD segment 102 and is more or less a mirror image of OCD segment 102, such as Figure 3As shown, the ICD section 104 can be continuously shaped as part of the liner 52. Therefore, the ICD section 104 includes an ICD section convergence portion 126 that converges radially outward and longitudinally downstream relative to the burner centerline 112 from the upstream end 128 of the ICD section 104 to the upstream end 130 of the ICD section transition portion 132 into the combustion chamber 62. The ICD section convergence portion 126 may have a semi-circular shape, with its center 115 located within the combustion chamber 62. Alternatively, the ICD section convergence portion 126 may have a parabolic or straight shape. The ICD section 104 includes an ICD section divergence portion 134 that extends radially inward and longitudinally downstream relative to the burner centerline 112 from the downstream end 136 of the ICD section transition portion 132 to the downstream end 138 of the ICD section 104. The ICD section diverging portion 134 may have a semi-circular shape, with its center 117 located within the combustion chamber 62. Alternatively, the ICD section diverging portion 134 may have a parabolic or straight shape. The ICD section transition portion 132 connects the downstream end 140 of the ICD section converging portion 126 and the upstream end 142 of the ICD section diverging portion 134. The ICD section transition portion 132 may have a parabolic shape, with its focal point 109 located radially inward relative to the burner centerline 112. The parabolic shape of the ICD section transition portion 132 may have a width-to-depth ratio of 1:4. Alternatively, the ICD section transition portion 132 may have a semi-circular or straight shape. Therefore, the upstream portion 125 of the ICD segment 104, defined by at least a portion of the ICD segment convergence portion 126 and the ICD segment transition portion 132, extends radially outward and downstream relative to the burner centerline 112, and the downstream portion 127 of the ICD segment 104, defined by at least a portion of the ICD segment transition portion 132 and the ICD segment divergence portion 134, extends radially inward and downstream relative to the burner centerline 112.

[0035] exist Figure 3 In this context, the inner bridge member 94 is similar to the outer bridge member 92 and is considered to be connected to the inner liner 52. For example... Figure 3In the aspects of this disclosure shown, the inner bridge member 94 is connected to the radially inner surface 158 of the liner 52 and is configured to span the ICD section 104. The inner bridge member 94 may be brazed or welded to the radially inner surface 158 of the liner 52 at an upstream weld joint 160 and a downstream weld joint 162. Similar to the OCD section 102, the inner bridge member 94 may be connected to the ICD section 104 via a plurality of inner bridge support members (not shown), which may be identical to the outer bridge support member 222. As described above, the inner bridge member 94 includes a plurality of inner bridge openings 95 passing through the inner bridge member 94. The inner bridge openings 95 are arranged to provide a compressed air flow 82(c) from the inner flow passage 69 to an inner acoustic damper cavity 97 formed within the ICD section 104.

[0036] like Figure 2 and Figure 3 As shown, both OCD section 102 and ICD section 104 have a generally smoothly transitioning sinusoidal shape to provide aerodynamic flow of combustion gas 86 within combustion chamber 62. However, either or both of OCD section 102 and ICD section 104 can be formed as a trapezoidal structure with straight segments, rather than a smoothly curved sinusoidal shape. OCD section transition portion 114 and ICD section transition portion 132 form a throat 119 between them, and an outer dilution opening 88 and an inner dilution opening 90 are disposed through the transition portion to provide dilution airflow in the throat 119.

[0037] Still referencing Figure 3 The external dilution opening 88 is shown as being defined through the OCD segment transition portion 114, and the dilution opening 90 is shown as being defined through the ICD segment transition portion 132. However, dilution openings may be implemented in other portions of the OCD segment 102 and the ICD segment 104. Furthermore, although in Figure 3 Not shown in the middle, below about Figure 5 As described, the OCD section 102 may include, for example, a plurality of cooling holes 210 extending through the OCD section convergence portion 106. The cooling holes 210 may typically have a smaller size than the external dilution opening 88 and supply surface cooling air from the external acoustic damper cavity 96 to the inner surface of the OCD section 102 within the combustion chamber 62. Furthermore, although... Figure 3 The cross-sectional view shows a single external dilution opening 88 passing through the OCD section transition portion 114, but it will be readily understood that multiple external dilution openings 88 may be included. For example, multiple external dilution openings 88 may be circumferentially spaced around the outer liner 54. Similarly, multiple internal dilution openings 90 may be circumferentially spaced around the inner liner 52. Furthermore, although the external dilution openings 88 and internal dilution openings 90 are shown directly opposite each other across the combustion chamber 62, they may be circumferentially or longitudinally offset from each other.

[0038] exist Figure 3 In this design, the outer dilution opening 88 and the inner dilution opening 90 are typically shown as circular or cylindrical openings generally perpendicular to the burner centerline 112. Other shapes, such as squares, ellipses, racetrack shapes, triangles, etc., may, however, be implemented for the outer dilution opening 88 and the inner dilution opening 90. Furthermore, although the outer dilution opening 88 and the inner dilution opening 90 are shown arranged generally perpendicular to the burner centerline 112, alternatively, they may be angled. For example, the outer dilution opening 88 may be arranged at a radial angle of 144 or a radial angle of 146, where the radial angle 144 may be in the range from zero to -30 degrees, and the radial angle 146 may be in the range from zero to +30 degrees. Similarly, the inner dilution opening 90 may be angled at a radial angle of 148 or a radial angle of 150, where the radial angle 148 may be in the range from zero to +30 degrees, and the radial angle 150 may be in the range from zero to -30 degrees. Of course, the aforementioned range is merely exemplary, and other angular ranges may be implemented alternatively to obtain the desired dilution flow rate of air through the dilution opening.

[0039] Still referencing Figure 3 It can be seen that the OCD section 102 includes an external acoustic damper inlet supply member 101. The external acoustic damper inlet supply member 101 is located downstream of the throat 119 and, specifically, is arranged to pass through the divergence portion 116 of the OCD section. Similarly, it can be seen that the ICD section 104 includes an internal acoustic damper inlet supply member 103 located downstream of the throat 119 and arranged to pass through the divergence portion 134 of the ICD section. The external acoustic damper 143 is at least partially defined by the outer bridge member 92, the OCD section 102, and the external acoustic damper inlet supply member 101, with the outer bridge member 92 and the OCD section 102 forming an external acoustic damper cavity 96 having an external dilution opening 88 therebetween. The internal acoustic damper 145 is defined at least in part by an inner bridge member 94 and an ICD section 104, as well as an internal acoustic damper inlet supply member 103, with the inner bridge member 94 and the ICD section 104 forming an internal acoustic damper cavity 97 having an internal dilution opening 90 therebetween. A general description of the Helmholtz acoustic damper will now be provided, as it is applicable to both the external acoustic damper 143 and the internal acoustic damper 145.

[0040] Figure 4 A schematic diagram depicts an example of the components that typically form the Helmholtz acoustic damper 164. Figure 4 The schematic diagram is merely a general representation of the Helmholtz acoustic damper and is not intended to be a precise representation of the acoustic damper implemented in the burner of this disclosure. Instead, instructions on how to apply the various elements of the disclosed burner will be provided below. Figure 4 A description of the overall schematic diagram. In Figure 4In this design, the Helmholtz acoustic damper 164 may include a cavity 166 having a volume V. The Helmholtz acoustic damper 164 may include an opening 172 allowing air P to flow into the cavity 166. The Helmholtz acoustic damper 164 may include a neck 168 located between the cavity 166 and a neck inlet orifice 170. The neck inlet orifice 170 may have a cross-sectional area S and the neck 168 may have a length L′. The frequencies that the Helmholtz acoustic damper 164 can suppress can be calculated using Equation 1 below, where c is the speed of sound, S is the cross-sectional area of ​​the neck inlet orifice 170, V is the volume of the cavity 166, and L′ is the length of the neck 168. In an example including multiple neck inlet orifices 170, the area S may be the sum of the cross-sectional areas of all the neck inlet orifices 170.

[0041]

[0042] As mentioned above Figure 4 The described embodiments are applicable to this disclosure. For the external acoustic damper 143, the external acoustic damper 143 may correspond to the Helmholtz acoustic damper 164. The external acoustic damper inlet supply member 101 may correspond to the neck 168 having a length L′ and the cross-sectional area S of the neck inlet orifice 170. The external acoustic damper cavity 96 may correspond to the cavity 166 having a volume V, and the opening 172 may correspond to the outer bridge opening 93. Therefore, the external acoustic damper neck may be referred to as 168(o), and the external acoustic damper neck inlet orifice may be referred to as 170(o), while the internal acoustic damper neck may be referred to as 168(i), and the internal acoustic damper neck inlet orifice may be referred to as 170(i). The external acoustic damper inlet supply member 101 (i.e., the length L′ and cross-sectional area S of the outer neck 168(o) and the outer aperture 170(o)) can be configured to have frequencies (f) ranging from 200 Hz to 800 Hz, or from 800 Hz to 1600 Hz. This also applies to the frequency tuning of the internal acoustic damper 145, such that the dimensions of the various elements of the internal acoustic damper inlet supply member 103 (e.g., the inner neck 168(i) and the inner inlet aperture 170(i)) can be designed such that the internal acoustic damper has frequencies ranging from 200 Hz to 800 Hz, or from 800 Hz to 1600 Hz. Furthermore, the external acoustic damper 143 and the internal acoustic damper 145 can be configured to suppress different frequency ranges. For example, the external acoustic damper can be configured to have frequencies in the range of 200 Hz to 800 Hz, and the internal acoustic damper can be configured to have frequencies in the range of 800 Hz to 1600 Hz. With this arrangement, the dampers can be individually configured to suppress different frequencies within the burner, thereby providing even better suppression of the burner's acoustic characteristics.

[0043] Figure 5This is a partial cross-sectional side view of the convergent-divergent portion 100 of a burner bushing with an acoustic damper, according to another aspect of this disclosure. Figure 5 In this aspect, the burner bushing convergent-divergent section 100 includes an external acoustic damper 194 and an internal acoustic damper 196, similar to... Figure 3 External acoustic damper 143 and internal acoustic damper 145. However, in Figure 5 In this configuration, the OCD segment 102 is not continuously formed within the outer liner 54, but rather as a separate OCD segment 202 connected to the outer liner 54 on its radially inner surface 186 (i.e., on the surface of the outer liner 54 adjacent to the combustion chamber 62). The outer liner 54 is a continuous, straight (or slightly curved) liner along the longitudinal direction, and the individual OCD segments 202 can be brazed or welded to the outer liner 54. For example, the individual OCD segments 202 can be brazed or welded to the radially inner surface 186 of the outer liner 54 at the upstream weld joint 174 and the downstream weld joint 176 of the OCD segment. Thus, when the OCD segments 202 are connected to the outer liner 54, an external damper cavity 190 is formed therebetween. The external acoustic damper cavity 190 may be similar to... Figure 3 External acoustic damper cavity 96.

[0044] In addition, with Figure 3 The arrangement shown is similar; the outer liner 54 may include an outer liner opening 182 similar to the outer bridge opening 93, which allows compressed air flow 82(c) to pass through the outer flow channel 68 from the outer liner 54 into the outer damper cavity 190. The OCD section 202 includes an outer dilution opening 198, which may be similar to... Figure 3 An external dilution opening 88 allows compressed air 82(c) to flow from the external damper cavity 190 into the dilution zone 72 of the combustion chamber 62. Furthermore, the OCD section 202 includes an external acoustic damper inlet supply member 206, which can be connected to a reference... Figure 3 The described external acoustic damper inlet supply member 101 is similar. Therefore, the outer liner 54 having an outer liner opening 182, the OCD section 202 coupled to the outer liner 54, and the external acoustic damper inlet supply member 206 form an external acoustic damper 194, which can be similar to the external acoustic damper 143. The external acoustic damper 194 can be tuned similarly to the external acoustic damper 143, as described above.

[0045] Similarly, in Figure 5In this configuration, the ICD segment 104 is not continuously formed within the liner 52, but rather consists of separate ICD segments 204 connected to the liner 52 on its radially outer surface 188 (i.e., on the surface of the liner 52 adjacent to the combustion chamber 62). The liner 52 comprises a continuous, straight (or slightly curved) liner along the longitudinal direction, and the individual ICD segments 204 can be brazed or welded to the liner 52. For example, individual ICD segments 204 can be brazed or welded to the radially outer surface 188 of the liner 52 at upstream weld joint 178 and downstream weld joint 180. Thus, when the ICD segments 204 are connected to the liner 52, an internal damper cavity 192 is formed between them. The internal acoustic damper cavity 192 can be similar to... Figure 3 The internal acoustic damper cavity 97.

[0046] In addition, with Figure 3 The arrangement shown is similar; the liner 52 may include a liner opening 184 similar to the inner bridge opening 95, which allows compressed air flow 82(c) to pass through the inner flow channel 69 from the liner 52 into the inner damper cavity 192. The ICD section 204 includes a plurality of inner dilution openings 200, which may be similar to... Figure 3 An internal dilution opening 90 allows compressed air 82(c) to flow from the internal damper cavity 192 into the dilution zone 72 of the combustion chamber 62. Furthermore, the ICD section 204 includes an internal acoustic damper inlet supply member 208, which is similar to the reference [reference missing]. Figure 3 The internal acoustic damper inlet supply member 103 is described. Therefore, the liner 52 having an inner liner opening 184, the ICD section 204 coupled to the liner 52, and the internal acoustic damper inlet supply member 208 form an internal acoustic damper 196, which can be similar to the internal acoustic damper 145. The internal acoustic damper 196 can be tuned similarly to the internal acoustic damper 145, as described above.

[0047] Still referencing Figure 5 The OCD section 202 shown also includes a plurality of cooling holes 210 passing through the OCD section 202. The cooling holes 210 may be smaller than the outer dilution opening 198 and are arranged to provide a compressed air flow 82(c) from the outer damper cavity 190 through the OCD section 202 to provide surface cooling to the radially inner surface 212 of the OCD section 202. The cooling holes 210 may be arranged through the convergent portion 211 of the OCD section, corresponding to… Figure 3 The OCD segment convergence portion 106, and / or the OCD segment transition portion 213, corresponding to Figure 3 The OCD section transition portion 114. Although Figure 5 Not depicted in the text, the corresponding cooling holes 210 can also be arranged in a substantially mirror-image manner, passing through the ICD section 204. Additionally, although in Figure 3 (Not shown in the diagram) The cooling hole 210 can also be arranged to pass through... Figure 3 OCD segment 102 and ICD segment 104, in conjunction with Figure 5 The cooling hole 210 shown is similar.

[0048] exist Figure 5 In this design, the internal acoustic damper 196 is also shown as including multiple damping cavity shields located within the internal damping cavity 192, including damping cavity shield 214 and damping cavity shield 216. It can be seen that damping cavity shield 214 includes multiple damping cavity shield openings 218, and that damping cavity shield 216 includes multiple damping cavity shield openings 220 passing through it. The multiple damping cavity shield openings 218 and 220 allow airflow within the internal damping cavity 192 to pass through and reach the internal dilution opening 200. Damping cavity shields 216 and 214 provide a multi-layered arrangement of a Helmholtz resonator, which can be used to suppress a wider range of frequencies. Each of the damper cavity shield 216 and damper cavity shield 214 can be brazed or welded to the liner 52 at the upstream weld joint 178 and the downstream weld joint 180 of the ICD section, just like the ICD section 204. Although in Figure 5 Not shown, the corresponding damper cavity shield 216 and the corresponding damper cavity shield 214 can also be arranged in a substantially mirror-image manner within the outer damper cavity 190 of the OCD section 202. Additionally, although in Figure 3 Not shown in the diagram, the damper cavity shield can be connected with... Figure 5 The damper cavity shield shown is implemented in a similar manner within the outer acoustic damper cavity 96 and / or the inner acoustic damper cavity 97.

[0049] refer to Figure 6 and Figure 7 , which shows in Figure 1 A partial cross-sectional view of an example of annular burner 50 taken at plane AA. Figure 6 and Figure 7 middle, Figure 2 A partial cross-sectional view of the burner 50 can be seen taken from plane 2-2. Figure 6 and Figure 7 As can be seen, the annular burner 50 includes an outer liner 54, which is an annular outer liner 54 extending circumferentially around the burner centerline 112. Furthermore, the annular burner 50 includes an inner liner 52, which is an annular inner liner 52 extending circumferentially around the burner centerline 112. Figure 6In this configuration, the outer bridge member 92 is considered an annular outer bridge member 92, which extends circumferentially around the burner centerline 112 along the radial outer surface 152 of the annular outer liner 54. Therefore, the outer damper cavity 96 is considered an annular outer damper cavity 96 extending circumferentially around the burner centerline 112. Similarly, the inner bridge member 94 is considered an annular inner bridge member 94 extending circumferentially around the burner centerline 112 along the radial inner surface 158 of the annular inner bridge member 94. Therefore, the inner acoustic damper cavity 97 is considered an annular inner acoustic damper cavity extending circumferentially around the burner centerline 112.

[0050] Figure 6 The annular outer bridge member 92 includes an outer bridge member opening 93, and as... Figure 6 As shown, multiple outer bridge member openings 93 can pass through the annular outer bridge member 92 and are circumferentially spaced around the burner centerline 112. It can also be seen that the annular outer liner 54 includes multiple circumferentially spaced outer dilution openings 88 passing through the annular outer liner 54 around the burner centerline 112. Additionally, it can be seen that the annular outer liner 54 includes multiple circumferentially spaced outer acoustic damper inlet supply members 101 around the burner centerline 112. Therefore, in Figure 6 In the middle, the external acoustic damper 143 is arranged as a ring-shaped external acoustic damper. Similarly, Figure 6 The annular inner bridge member 94 includes an inner bridge member opening 95, and as... Figure 6 As shown, multiple inner bridge member openings 95 can pass through the annular inner bridge member 94 and are circumferentially spaced around the burner centerline 112. It can also be seen that the annular liner 52 includes multiple circumferentially spaced inner dilution openings 90 passing through the annular liner 52 around the burner centerline 112. Furthermore, it can be seen that the annular liner 52 includes multiple circumferentially spaced inner acoustic damper inlet supply members 103 around the burner centerline 112. Therefore, as... Figure 6 As shown, the internal acoustic damper 145 is arranged as a ring-shaped internal acoustic damper.

[0051] and Figure 6 The arrangement of the annular outer damper and the annular inner damper is opposite. Figure 7 An arrangement is shown comprising a plurality of external acoustic dampers 143 arranged circumferentially around a burner centerline 112 and a plurality of internal acoustic dampers 145 arranged circumferentially around a burner centerline 112. Figure 7In this configuration, the outer damper bridge member 92 does not necessarily extend annularly along the entire radial outer surface 152 of the outer liner 54 (although it may), but may extend partially around the radial outer surface 152. Therefore, to form the outer acoustic damper 143, a plurality of outer acoustic damper sidewalls 224 are configured to extend from the upstream end 108 of the OCD segment to the downstream end 120 of the OCD segment between the outer acoustic damper bridge member 92 and the outer liner 54. Thus, the outer damper cavity 96 is formed by the outer damper bridge member 92, the OCD segment 102, and the outer damper sidewalls 224, wherein the outer acoustic damper inlet supply member 101 provides acoustic oscillations to the outer damper cavity 96. Similarly, the inner damper bridge member 94 does not extend annularly along the entire radial inner surface 158 of the inner liner 52 (although it may), but may extend partially around the radial inner surface 158. Therefore, in order to form the internal acoustic damper 145, a plurality of internal acoustic damper sidewalls 226 are disposed between the internal acoustic damper bridge member 94 and the liner 52, extending from the upstream end 128 of the ICD section to the downstream end 138 of the ICD section. Thus, the internal damper cavity 97 is formed by the internal damper bridge member 94, the ICD section 104, and the internal damper sidewalls 226, wherein the internal acoustic damper inlet supply member 103 provides acoustic oscillations to the internal damper cavity 97. Figure 7 In this arrangement, a plurality of external undamped portions 228 may be defined between successive external acoustic dampers 143, wherein each external undamped portion 228 may include an external dilution opening 88 passing through it. Similarly, a plurality of internal undamped portions 230 are defined between successive internal acoustic dampers 145, wherein each internal undamped portion 230 may include an internal dilution opening 90 passing through it.

[0052] As Figure 7 In an alternative arrangement, the external damper bridge member 92 can extend around the entire circumference of the outer liner 54, such as... Figure 6 As shown, but similar implementations are possible. Figure 7 The sidewall of the sidewall. As an example, Figure 7 An arrangement is shown in which the outer bridge member 92 extends circumferentially to be shared by a first outer damper 232, a second outer damper 234, and a third outer damper 238. A first common sidewall 236 may be implemented between the first outer damper 232 and the second outer damper 234, while a second common sidewall 240 may be disposed between the second outer damper 234 and the third outer damper 238. This arrangement of shared common sidewalls may be implemented around the entire circumference of the annular outer liner 54 to define multiple outer dampers around the outer liner 54. Each outer damper in this type of arrangement may have different dimensions to suppress different frequencies. For example, as Figure 7As shown, the first external damper 232 and the third external damper 238 can have the same size, while the second external damper 234 can be smaller than the first external damper 232 and the third external damper 238. Of course, although... Figure 7 As not shown, the liner 52 may include a similar arrangement in which the inner bridge member 94 extends circumferentially around the burner centerline 112, but provides a shared common sidewall to define multiple inner dampers.

[0053] While the foregoing description pertains to annular burners with inner and outer liners, this disclosure is equally applicable to other types of burners. For example, OCD section 102 may be implemented as a single annular bushing as part of a canister burner. It can also be readily understood that, through Figure 5 As shown, existing non-convergent-divergent bushings can be easily modified to include an external convergent-divergent portion 143 and an internal convergent-divergent portion 145, and thus include an external acoustic damper 194 and an internal acoustic damper 196.

[0054] Now for reference Figure 8 The flowchart illustrates the steps of a method for operating the combustion section 26 of a gas turbine engine 10. The method according to this aspect is essentially the same as described above. Figures 1 to 7 The operation comprises a combustion section 26 having any of the aforementioned configurations as shown and described above. Thus, in one aspect, the method operates a combustion section 26 including a burner 50 having a burner bushing 51 including an outer liner 54, including an OCD section 102 having an outer dilution opening 88 and an outer acoustic damper inlet supply member 101 passing through the OCD section 102. The burner bushing 51 also includes an inner liner 52 having an ICD section 104 and an inner acoustic damper inlet supply member 103, the ICD section 104 having an inner dilution opening 90 passing through it. The burner assembly 50 also includes an outer bridge member 92 defining a bridge across the OCD section 102, and the outer bridge member 92 having at least one outer bridge opening 93 passing through it, wherein the outer bridge member 92 and the OCD section 102 having the outer acoustic damper inlet supply member 101 at least partially define an outer acoustic damper 143. In addition, the burner assembly 50 has an inner bridge member 94 defining a bridge across the ICD section 104, wherein the inner bridge member 93 includes at least one inner bridge opening 95 passing through it, and wherein the inner bridge member 93 and the ICD section 104 having an inner acoustic damper inlet supply member 103 at least partially define an inner acoustic damper 145.

[0055] Combustion section 26 for the disclosed method also includes an outer housing 64 surrounding the burner liner 51, an inner oxidizer flow channel 68 / 69 defined between the burner liner 51 and the outer housing 64, and an air mixer assembly 60 connected to the upstream end of the burner liner 51, wherein the combustion chamber 62 is defined between the outer liner 54 and the inner liner 52 of the burner liner 51.

[0056] With the combustion zone 26 configured as described above, the method of operating the combustion zone 26 will now be described. (Refer to...) Figure 8 The first step 800 of the disclosed method requires dispersing a fuel-air mixture stream from the fuel-air mixer assembly 60 into the primary combustion zone 70 of the combustion chamber 62, and the second step 801 includes igniting the fuel-air mixture stream in the primary combustion zone 70 of the combustion chamber 62 to produce combustion gases 86. As described above, the first portion of the compressed air 82 (such as...) Figure 2 Arrow 82(a) schematically indicates that fuel flows from diffuser cavity 84 through opening of shroud 57 and into pressure chamber 65, where fuel is swirled by fuel nozzle assembly 58 and fuel-air mixer assembly 60 to produce swirling fuel-air mixture, which is then ignited and burned to produce combustion gases 86 in primary combustion zone 70 of burner assembly 50.

[0057] Step 802 of the method requires that an oxidant (e.g., compressed air 82(c)) flow from an external flow passage 68 through at least one external dilution opening 88 of the OCD section 102 into the dilution zone 72 of the combustion chamber 62, and that a diluted oxidant gas (e.g., compressed air 82(c)) flow from an internal flow passage 69 through at least one internal dilution opening 90 of the ICD section 104 into the dilution zone 72 of the combustion chamber 62. Step 803 of the method requires that the oxidant flow passing through at least one external dilution opening 88 and the oxidant flow passing through at least one internal dilution opening 90 be mixed with combustion gas 86 from the primary combustion zone 70 in the dilution zone 72 of the combustion chamber 62 to produce diluted combustion gas 87. For steps 802 and 803, as described above regarding... Figure 2 The second part of the compressed air 82, as described and schematically indicated by arrow 82(b), can be used for various purposes other than combustion. For example, as... Figure 2As shown, compressed air 82(b) can be routed into the outer flow channel 68 and the inner flow channel 69. A portion of the compressed air 82(b) can then be guided through the outer bridge opening 93 into the outer acoustic damper cavity 96 and through the outer dilution opening 88 (schematically shown as compressed air 82(c)) into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gas 86 in the dilution zone 72, thereby producing diluted combustion gas 87, and can also provide turbulence to the combustion gas 86 flow to provide better mixing of the diluted oxidant gas (e.g., compressed air 82(c)) with the combustion gas 86. A similar flow of compressed air 82(c) from the inner flow channel 69 flows through the inner bridge opening 95 into the inner acoustic damper cavity 97 and through the inner dilution opening 90 into the dilution zone 72 of the combustion chamber 62.

[0058] The next part of the method involves suppressing the acoustic characteristics of the combustion zone 26 generated by the combustion process. Damping occurs via the operation of the external acoustic damper 143 and the internal acoustic damper 145. Therefore, in operation, step 804 requires that a portion of the acoustic oscillation wave propagate through at least one external acoustic damper inlet supply member 101, arranged on the downstream portion of the OCD zone 102, into the external acoustic damper cavity 96 of the external acoustic damper 143 to suppress the acoustic characteristics of the burner. Similarly, step 804 also requires that a portion of the acoustic oscillation wave propagate through at least one internal acoustic damper inlet supply member 103, located on the downstream portion of the ICD zone 104, into the internal acoustic damper cavity 97 of the internal acoustic damper 145 to suppress the acoustic characteristics of the burner. In step 804, the external acoustic damper 143 suppresses the acoustic characteristics of the burner assembly 50 at a first frequency, and the internal acoustic damper 145 suppresses the acoustic characteristics of the burner assembly 50 at a second frequency. In the exemplary burner 50 of this disclosure, the acoustic characteristics range from 200 Hz to 1600 Hz. Of course, acoustic characteristics at other frequencies may also be present in the burner, and the aforementioned range is merely exemplary. Therefore, for the aforementioned exemplary frequency range, the external acoustic damper 143 can be configured such that the first frequency has a range from 200 Hz to 800 Hz, while the internal acoustic damper 145 can be configured such that the second frequency has a range from 800 Hz to 1600 Hz. With this arrangement, each damper can be tuned to suppress different acoustic characteristic frequencies. Of course, the external acoustic damper 143 can alternatively be configured to have a first frequency in the range of 800 Hz to 1600 Hz, and the internal acoustic damper 145 can be configured to have a second frequency in the range of 200 Hz to 800 Hz.

[0059] While the foregoing description generally pertains to gas turbine engines, it will be readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, this disclosure is not limited to use in aircraft.

[0060] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0061] A combustor bushing for a gas turbine combustor, the combustor bushing comprising: an outer liner; and an inner liner defining a combustion chamber therebetween, wherein at least one of the outer liner and the inner liner comprises: (a) a convergent-divergent (CD) section extending into the combustion chamber and including at least one dilution opening through the CD section, the CD section further including at least one acoustic damper inlet supply member extending through a downstream portion of the CD section, and (b) a bridge member defining a bridge extending across the CD section, the bridge member including at least one bridge opening therethrough, the bridge member and the CD section defining an acoustic damper.

[0062] According to the burner described in the foregoing clauses, both the outer liner and the inner liner include the CD section and the bridge member. The CD section of the outer liner includes an outer convergent-divergent (OCD) section. The at least one acoustic damper inlet supply member of the outer liner includes at least one outer acoustic damper inlet supply member. The upstream portion of the OCD section extends radially inward and downstream relative to the burner centerline in the longitudinal direction, and the downstream portion of the OCD section extends radially outward and downstream relative to the burner centerline in the longitudinal direction. The CD section of the inner liner includes an inner convergent-divergent (ICD) section. The at least one acoustic damper inlet supply member of the inner liner includes at least one inner acoustic damper inlet supply member. The upstream portion of the ICD section... The outer liner's bridge member extends radially outward and downstream relative to the burner centerline along the longitudinal direction, and the downstream portion of the ICD section extends radially inward and downstream relative to the burner centerline along the longitudinal direction. The bridge member of the outer liner includes an outer bridge member that extends at least partially in the longitudinal direction and defines a bridge across the ICD section, the outer bridge member including at least one outer bridge opening therethrough, the outer bridge member and the ICD section defining an outer acoustic damper; and the inner liner's bridge member includes an inner bridge member that extends at least partially in the longitudinal direction and defines a bridge across the ICD section, the inner bridge member including at least one inner bridge opening therethrough, the inner bridge member and the ICD section defining an inner acoustic damper.

[0063] The burner bushing according to any one of the preceding clauses, wherein the external acoustic damper includes at least one external damping cavity shield, the at least one external damping cavity shield being disposed between the OCD section and the external bridge member, and having an external damping cavity shield dilution opening therethrough, and wherein the internal acoustic damper includes at least one internal damping cavity shield, the at least one internal damping cavity shield being disposed between the ICD section and the internal bridge member, and having an internal damping cavity shield dilution opening therethrough.

[0064] The burner liner according to any one of the preceding clauses, wherein the OCD section is defined by the outer liner and the outer bridge member passes through the OCD section and is connected to the radial outer surface of the outer liner, and wherein the ICD section is defined by the inner liner and the inner bridge member is connected to the radial inner surface of the inner liner to bridge the ICD section.

[0065] The burner bushing according to any one of the preceding clauses further includes at least one outer bridge support member connecting the OCD section and the outer bridge member within the outer acoustic damper, and at least one inner bridge support member connecting the ICD section and the inner bridge member within the inner acoustic damper.

[0066] The burner bushing according to any one of the preceding clauses, wherein the outer bridge member is defined by the outer liner and the OCD section is connected to the radial inner surface of the outer liner, and wherein the inner bridge member is defined by the inner liner and the ICD section is connected to the radial outer surface of the inner liner.

[0067] The burner according to any one of the preceding clauses, wherein the external acoustic damper is a Helmholtz acoustic damper, and the internal acoustic damper is a Helmholtz acoustic damper.

[0068] The burner bushing according to any one of the preceding clauses, wherein the at least one external acoustic damper inlet supply member includes an external damper neck having an inlet orifice therethrough, the inlet orifice of the external damper neck defining its cross-sectional area, and the at least one internal acoustic damper inlet supply member includes an internal acoustic damper neck having an inlet orifice therethrough, the inlet orifice of the internal acoustic damper neck defining its cross-sectional area.

[0069] The burner according to any one of the preceding clauses, wherein the outer damper neck extends at least partially radially inward from the OCD section into the combustion chamber, and wherein the inner damper neck extends at least partially radially inward from the ICD section into the combustion chamber.

[0070] According to any one of the preceding clauses, the burner, wherein the OCD section comprises: (i) an OCD section convergence portion, the OCD section convergence portion radially inward and longitudinally downstream relative to the burner centerline from the upstream end of the OCD section to the upstream end of the OCD section transition portion into the combustion chamber; (ii) an OCD section divergence portion, the OCD section divergence portion extending radially outward and longitudinally downstream relative to the burner centerline from the downstream end of the OCD section transition portion to the downstream end of the OCD section; and (iii) the OCD section transition portion connecting the downstream end of the OCD section convergence portion and the OCD section. The upstream end of the diverging portion and the ICD section include: (i) an ICD section converging portion, which converges radially outward and longitudinally downstream relative to the burner centerline from the upstream end of the ICD section to the upstream end of the ICD section transition portion into the combustion chamber; (ii) an ICD section diverging portion, which extends radially inward and longitudinally downstream relative to the burner centerline from the downstream end of the ICD section transition portion to the downstream end of the ICD section; and (iii) the ICD section transition portion connects the downstream end of the ICD section converging portion and the upstream end of the ICD section diverging portion.

[0071] The burner bushing according to any one of the preceding clauses, wherein the OCD section includes at least one external acoustic damper inlet supply member passing through the diverging portion of the OCD section, and the ICD section includes at least one internal acoustic damper inlet supply member passing through the diverging portion of the ICD section.

[0072] The burner bushing according to any one of the preceding clauses, wherein the at least one external dilution opening comprises a plurality of external dilution holes arranged circumferentially around the burner centerline, the plurality of external dilution holes providing a dilution flow of oxidant through it to a dilution zone of the combustion chamber, the dilution zone being at least partially defined between the OCD section and the ICD section, wherein the at least one internal dilution opening comprises a plurality of internal dilution holes arranged circumferentially around the burner centerline, the plurality of internal dilution holes providing an oxidant flow through it to the dilution zone of the combustion chamber.

[0073] The burner bushing according to any one of the preceding clauses, wherein the plurality of external dilution holes are arranged to pass through the OCD section transition portion, and the plurality of internal dilution holes are arranged to pass through the ICD section transition portion.

[0074] The burner bushing according to any one of the preceding clauses, wherein the OCD section further includes a plurality of cooling holes passing through at least one of the OCD section convergence portion and the OCD section transition portion, and the ICD section further includes a plurality of cooling holes passing through at least one of the ICD section convergence portion and the ICD section transition portion.

[0075] According to any one of the preceding clauses, the length of the outer damper neck and the cross-sectional area of ​​the outer damper neck are configured to suppress the acoustic characteristics of the burner in the range of 200 Hz to 800 Hz or in the range of 800 Hz to 1600 Hz based on the volume of the outer acoustic damper, and the length of the inner damper neck and the cross-sectional area are configured to suppress the acoustic characteristics of the burner in the range of 200 Hz to 800 Hz or in the range of 800 Hz to 1600 Hz based on the volume of the inner acoustic damper.

[0076] The burner according to any one of the preceding clauses, wherein the outer bridge member extends circumferentially about the burner centerline such that the outer acoustic damper includes an annular outer acoustic damper extending circumferentially about the burner centerline, and the inner bridge member extends circumferentially about the burner centerline such that the inner acoustic damper includes an annular inner acoustic damper extending circumferentially about the burner centerline.

[0077] The burner according to any one of the preceding claims, wherein the burner includes a plurality of external acoustic dampers arranged circumferentially around the burner centerline, and a plurality of internal acoustic dampers arranged circumferentially around the burner centerline, each of the plurality of external acoustic dampers including a plurality of external acoustic damper sidewalls connecting the external bridge component and the OCD section to define the external acoustic damper therein, and each of the plurality of internal acoustic dampers including a plurality of internal acoustic damper sidewalls connecting the internal bridge component and the ICD section to define the internal acoustic damper therein.

[0078] A method of operating a combustion section of a gas turbine, the combustion section comprising (i) a combustor bushing, the combustor bushing comprising (a) an outer liner, (b) an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween, (c) an outer convergent-divergent (OCD) section extending into the combustion chamber and including at least one outer dilution opening through the OCD section, the OCD section further including an outer acoustic damper inlet supply member extending through a downstream portion of the OCD section, and (d) an inner convergent-divergent (ICD) section extending into the combustion chamber and including at least one inner dilution opening through the ICD section. The ICD section further includes an internal acoustic damper inlet supply member extending through the downstream portion of the ICD section; (e) an outer bridge member defining a bridge across the OCD section to define an external acoustic damper cavity therebetween; the outer bridge member includes at least one outer bridge opening therethrough; the outer bridge member and the OCD section define an external acoustic damper; and (f) an inner bridge member defining a bridge across the ICD section to define an internal acoustic damper cavity therebetween; the inner bridge member includes at least one inner bridge opening therethrough; the inner bridge member and the ICD section define an internal acoustic damper; and (ii) a housing surrounding the burner bushing, oxidized. The method includes (iii) defining an oxidant flow channel between the burner bushing and the housing, and (iv) a fuel-air mixer assembly connected to the upstream end of the burner bushing, the method comprising: dispersing a fuel-air mixture flow from the fuel-air mixer assembly into a primary combustion zone of the combustion chamber; igniting the fuel-air mixture flow in the primary combustion zone of the combustion chamber to generate combustion gases in the primary combustion zone; allowing an oxidant to flow from the oxidant flow channel through at least one external dilution opening of the OCD section into a dilution zone of the combustion chamber disposed between the OCD section and the ICD section, and allowing the oxidant to flow from the oxidant flow channel through at least one external dilution opening of the ICD section into a dilution zone of the combustion chamber. At least one internal dilution opening enters the dilution zone of the combustion chamber; in the dilution zone of the combustion chamber, the oxidant flow through the at least one external dilution opening and the oxidant flow through the at least one internal dilution opening are mixed with the combustion gas of the primary combustion zone to produce diluted combustion gas; and a portion of the acoustic oscillation wave propagates through at least one external acoustic damper inlet supply member into the external acoustic damper cavity of the external acoustic damper to suppress the acoustic characteristics of the burner, and a portion of the acoustic oscillation wave propagates through at least one internal acoustic damper inlet supply member into the internal acoustic damper cavity of the internal acoustic damper to suppress the acoustic characteristics of the burner.

[0079] According to the method described in the preceding paragraph, the external acoustic damper suppresses the acoustic characteristics of the burner at a first frequency, and the internal acoustic damper suppresses the acoustic characteristics of the burner at a second frequency.

[0080] According to any one of the preceding clauses, the first frequency ranges from 200 Hz to 800 Hz, and the second frequency ranges from 800 Hz to 1600 Hz, or the first frequency ranges from 800 Hz to 1600 Hz, and the second frequency ranges from 200 Hz to 800 Hz.

[0081] While the foregoing description is directed to some exemplary embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection 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 bushing for a gas turbine burner, characterized in that, The burner bushing includes: Outer lining; and The liner, the outer liner, and the inner liner define a combustion chamber therebetween. Wherein, at least one of the outer liner or the inner liner includes: (a) A convergence-divergence (CD) section, said convergence-divergence (CD) section extending circumferentially around the burner centerline axis and into the combustion chamber and including at least one dilution opening through said convergence-divergence section, said convergence-divergence section further including at least one acoustic damper inlet supply member extending through a downstream portion of said convergence-divergence section, and (b) A bridge member defining a bridge extending across the convergence-divergence section, the bridge member including at least one bridge opening therethrough, the bridge member and the convergence-divergence section defining an acoustic damper cavity therebetween, wherein the at least one bridge opening provides airflow through it to the acoustic damper cavity, the at least one dilution opening provides dilution airflow from the acoustic damper cavity into the combustion chamber, and the at least one acoustic damper inlet supply member provides inlet flow of acoustic oscillation waves from the combustion chamber into the acoustic damper cavity.

2. The burner bushing according to claim 1, characterized in that, in, Both the outer liner and the inner liner include the convergent-divergent section and the bridging member. The convergence-divergence section of the liner includes an external convergence-divergence (OCD) section, and the at least one acoustic damper inlet supply member of the liner includes at least one external acoustic damper inlet supply member. The upstream portion of the external convergence-divergence section extends radially inward and downstream relative to the burner centerline in the longitudinal direction, and the downstream portion of the external convergence-divergence section extends radially outward and downstream relative to the burner centerline in the longitudinal direction. The convergence-divergence section of the liner includes an inner convergence-divergence (ICD) section, and the at least one acoustic damper inlet supply member of the liner includes at least one inner acoustic damper inlet supply member. The upstream portion of the inner convergence-divergence section extends radially outward and downstream relative to the burner centerline along the longitudinal direction, and the downstream portion of the inner convergence-divergence section extends radially inward and downstream relative to the burner centerline along the longitudinal direction. The bridge member of the outer liner includes an outer bridge member that extends at least partially in the longitudinal direction and defines a bridge across the outer convergent-divergent section, the outer bridge member including at least one outer bridge opening therethrough, and the outer bridge member and the outer convergent-divergent section defining an outer acoustic damper. and The lining's bridge member includes an inner bridge member that extends at least partially in the longitudinal direction and defines a bridge across the inner convergent-divergent section. The inner bridge member includes at least one inner bridge opening through which it passes. The inner bridge member and the inner convergent-divergent section define an inner acoustic damper.

3. The burner bushing according to claim 2, characterized in that, in, The outer bridge member extends circumferentially around the burner centerline, such that the outer acoustic damper includes an annular outer acoustic damper extending circumferentially around the burner centerline, and the inner bridge member extends circumferentially around the burner centerline, such that the inner acoustic damper includes an annular inner acoustic damper extending circumferentially around the burner centerline.

4. The burner bushing according to claim 2, characterized in that, in, The burner includes a plurality of external acoustic dampers arranged circumferentially around the burner's centerline, and a plurality of internal acoustic dampers arranged circumferentially around the burner's centerline. Each of the plurality of external acoustic dampers includes a plurality of external damper sidewalls connecting the external bridge member and the external convergent-divergent section to define the external acoustic damper therein, and Each of the plurality of internal acoustic dampers includes a plurality of internal damper sidewalls connecting the internal bridge member and the internal convergent-divergent section to define the internal acoustic damper therein.

5. The burner bushing according to claim 2, characterized in that, in, The external acoustic damper includes at least one external damping cavity shield, which is disposed between the external convergence-divergence section and the external bridge member, and has a dilution opening through which the external damping cavity shield passes. The internal acoustic damper includes at least one internal damping cavity shield, which is disposed between the inner convergence-divergence section and the inner bridge member, and has a dilution opening through which the internal damping cavity shield passes.

6. The burner bushing according to claim 2, characterized in that, in, The outer convergence-divergence section is defined by the outer liner, and the outer bridging member is connected to the radially outer surface of the outer liner to bridge the outer convergence-divergence section. The inner convergent-divergent section is defined by the liner, and the inner bridging member is connected to the radial inner surface of the liner to bridge the inner convergent-divergent section.

7. The burner bushing according to claim 6, characterized in that, It further includes at least one outer bridge support member connecting the outer convergence-divergence section and the outer bridge member within the outer acoustic damper, and at least one inner bridge support member connecting the inner convergence-divergence section and the inner bridge member within the inner acoustic damper.

8. The burner bushing according to claim 2, characterized in that, in, The outer bridge component is defined by the outer liner, and the outer convergent-divergent section is connected to the radially inner surface of the outer liner. The inner bridge member is defined by the liner, and the inner convergent-divergent section is connected to the radial outer surface of the liner.

9. The burner bushing according to claim 2, characterized in that, in, The external acoustic damper is a Helmholtz acoustic damper, and the internal acoustic damper is a Helmholtz acoustic damper.

10. The burner bushing according to claim 2, characterized in that, in, The at least one external acoustic damper inlet supply member includes an external damper neck having an inlet orifice therethrough, the inlet orifice of the external damper neck defining its cross-sectional area, and The at least one internal acoustic damper inlet supply member includes an internal damper neck having an inlet orifice therethrough, the inlet orifice of the internal damper neck defining its cross-sectional area.

11. The burner bushing according to claim 10, characterized in that, in, The outer damper neck extends at least partially radially inward from the outer convergent-divergent section into the combustion chamber, and wherein the inner damper neck extends at least partially radially inward from the inner convergent-divergent section into the combustion chamber.

12. The burner bushing according to claim 2, characterized in that, in, The external convergence-divergence section includes: (i) a convergent portion of the outer convergence-divergence section, which, relative to the burner centerline, converges radially inward and longitudinally downstream from the upstream end of the outer convergence-divergence section to the upstream end of the transition portion of the outer convergence-divergence section into the combustion chamber; (ii) a divergent portion of the outer convergence-divergence section, which, relative to the burner centerline, extends radially outward and longitudinally downstream from the downstream end of the transition portion of the outer convergence-divergence section to the downstream end of the outer convergence-divergence section; and (iii) the transition portion of the outer convergence-divergence section connects the downstream end of the convergent portion of the outer convergence-divergence section and the upstream end of the divergent portion of the outer convergence-divergence section. The convergent-divergent section includes: (i) a convergent portion of the inner convergence-divergence section, which, relative to the burner centerline, converges radially outward and longitudinally downstream from the upstream end of the inner convergence-divergence section transition portion into the combustion chamber; (ii) a divergent portion of the inner convergence-divergence section, which, relative to the burner centerline, extends radially inward and longitudinally downstream from the downstream end of the inner convergence-divergence section transition portion; and (iii) the inner convergence-divergence section transition portion connects the downstream end of the inner convergence-divergence section convergent portion and the upstream end of the inner convergence-divergence section divergent portion.

13. The burner bushing according to claim 12, characterized in that, in, The external convergence-divergence section includes at least one external acoustic damper inlet supply member passing through the divergence portion of the external convergence-divergence section, and The inner convergence-divergence section includes at least one internal acoustic damper inlet supply member passing through the divergence portion of the inner convergence-divergence section.

14. The burner bushing according to claim 13, characterized in that, in, The at least one external dilution opening includes a plurality of external dilution holes arranged circumferentially around the burner centerline, the plurality of external dilution holes providing a dilution flow of oxidant through which to a dilution zone of the combustion chamber, the dilution zone being at least partially defined between the external convergence-divergence section and the internal convergence-divergence section. The at least one internal dilution opening includes a plurality of internal dilution holes arranged circumferentially around the centerline of the burner, the plurality of internal dilution holes providing an oxidant flow through which to the dilution zone of the combustion chamber.

15. The burner bushing according to claim 14, characterized in that, in, The plurality of external dilution orifices are arranged to pass through the transition portion of the external convergence-divergence section, and the plurality of internal dilution orifices are arranged to pass through the transition portion of the internal convergence-divergence section.

16. The burner bushing according to claim 15, characterized in that, in, The outer convergence-divergence section further includes a plurality of cooling holes passing through at least one of the convergence portion or the transition portion of the outer convergence-divergence section, and the inner convergence-divergence section further includes a plurality of cooling holes passing through at least one of the convergence portion or the transition portion of the inner convergence-divergence section.

17. The burner bushing according to claim 11, characterized in that, in, The length of the outer damper neck and the cross-sectional area of ​​the outer damper neck are configured to suppress the acoustic characteristics of the burner in the range of 200 Hz to 800 Hz or in the range of 800 Hz to 1600 Hz, based on the volume of the outer acoustic damper, and the length of the inner damper neck and the cross-sectional area are configured to suppress the acoustic characteristics of the burner in the range of 200 Hz to 800 Hz or in the range of 800 Hz to 1600 Hz, based on the volume of the inner acoustic damper.

18. A method of operating a combustion section of a gas turbine, the combustion section comprising (i) a combustor bushing, the combustor bushing comprising (a) an outer liner, (b) an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween, (c) an outer convergent-divergent (OCD) section, the outer convergent-divergent (OCD) section extending circumferentially about a combustor centerline axis and extending into the combustion chamber and including at least one outer dilution opening through the outer convergent-divergent section, the outer convergent-divergent section further including an outer acoustic damper inlet supply member extending through a downstream portion of the outer convergent-divergent section, and (d) an inner convergent-divergent (ICD) section, the inner convergent-divergent (ICD) section extending circumferentially about a combustor centerline axis and extending into the combustion chamber and including at least one inner dilution opening through the inner convergent-divergent section, the inner convergent-divergent section further ... The device comprises, (e) an internal acoustic damper inlet supply member extending through the downstream portion of the inner convergence-divergence section; (f) an outer bridge member defining a bridge across the outer convergence-divergence section to define an external acoustic damper cavity therebetween; the outer bridge member including at least one outer bridge opening therethrough; the outer bridge member and the outer convergence-divergence section defining an external acoustic damper; and (ii) an inner bridge member defining a bridge across the inner convergence-divergence section to define an internal acoustic damper cavity therebetween; the inner bridge member including at least one inner bridge opening therethrough; the inner bridge member and the inner convergence-divergence section defining an internal acoustic damper; (iii) a housing surrounding the burner bushing, an oxidizer flow passage defined between the burner bushing and the housing; and (iii) a fuel-air mixer assembly connected at the upstream end of the burner bushing, characterized in that... The method includes: This disperses the fuel-air mixture flow from the fuel-air mixer assembly into the primary combustion zone of the combustion chamber; Ignite the fuel-air mixture stream in the primary combustion zone of the combustion chamber to generate combustion gases in the primary combustion zone; (1) The oxidant flows from the oxidant flow channel through the at least one outer bridge opening into the outer acoustic damper cavity, and from the outer acoustic damper cavity through at least one outer dilution opening of the outer convergence-divergence section into the dilution zone of the combustion chamber disposed between the outer convergence-divergence section and the inner convergence-divergence section; and (2) The oxidant flows from the oxidant flow channel through the at least one inner bridge opening into the inner acoustic damper cavity, and from the inner acoustic damper cavity through at least one inner dilution opening of the inner convergence-divergence section into the dilution zone of the combustion chamber; In the dilution zone of the combustion chamber, the oxidant flow passing through the at least one external dilution opening and the oxidant flow passing through the at least one internal dilution opening are mixed with the combustion gas in the primary combustion zone to produce diluted combustion gas; and A portion of the acoustic oscillation wave is propagated through the at least one external acoustic damper inlet supply member into the external acoustic damper cavity of the external acoustic damper to suppress the acoustic characteristics of the burner, and a portion of the acoustic oscillation wave is propagated through the at least one internal acoustic damper inlet supply member into the internal acoustic damper cavity of the internal acoustic damper to suppress the acoustic characteristics of the burner.

19. The method according to claim 18, characterized in that, in, The external acoustic damper suppresses the acoustic characteristics of the burner at a first frequency, and the internal acoustic damper suppresses the acoustic characteristics of the burner at a second frequency.

20. The method according to claim 19, characterized in that, in, The first frequency ranges from 200 Hz to 800 Hz, and the second frequency ranges from 800 Hz to 1600 Hz, or the first frequency ranges from 800 Hz to 1600 Hz, and the second frequency ranges from 200 Hz to 800 Hz.

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