Thermoacoustic dampers in combustor linings

Abstract

A hollow plate of a combustor liner defining a combustion chamber includes an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of side walls coupled to the inner and outer walls to define a chamber, and a partition wall coupled to the plurality of side walls and dividing the chamber into a first sub-chamber and a second sub-chamber. The one or more outer openings communicate with the first sub-chamber and with the second sub-chamber via a plurality of tubes. The plurality of inner openings communicate with the second sub-chamber and with the first sub-chamber via one or more bypass tubes. The first sub-chamber, the second sub-chamber, or both are frequency tuned to reduce combustion dynamic frequencies.

Description

Technical Field

[0001] The present disclosure relates generally to combustor liners and, in particular, to thermoacoustic dampers in hollow panels of combustor liners. Background Art

[0002] A gas turbine engine generally comprises a fan and a core arranged in flow communication with each other, wherein the core is disposed downstream of the fan in a direction of flow through the gas turbine engine. The core of a gas turbine engine generally comprises, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] The foregoing and other features and advantages will become more particularly apparent from the following 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.

[0004] Figure 1 is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure.

[0005] Figure 2A According to an embodiment of the present disclosure Figure 1 Schematic longitudinal cross-sectional view of the combustion section of a turbine engine.

[0006] Figure 2B According to an embodiment of the present disclosure Figure 1 Schematic transverse cross-sectional view of a combustor of a turbine engine.

[0007] Figure 3 is a schematic perspective view of an outer liner of a combustor according to an embodiment of the present disclosure.

[0008] Figure 4 is a schematic diagram of sections of an inner liner and an outer liner of a combustor according to an embodiment of the present disclosure.

[0009] Figure 5 is a schematic diagram of one of a plurality of panels mounted to a skeleton network structure according to an embodiment of the present disclosure.

[0010] Figure 6 According to the embodiment of the present disclosure Figure 5 Schematic cross-sectional view of one of the plurality of plates at cross-sectional line 6 - 6 shown in FIG, showing the arrangement of the first and second sub-cavities.

[0011] Figure 7 is a top view of one of the plurality of plates showing a plurality of external holes and a plurality of external openings according to an embodiment of the present disclosure.

[0012] Figure 8 is an alternative schematic cross-sectional view of one of the plurality of plates showing the arrangement of the first sub-cavity and the second sub-cavity according to another embodiment of the present disclosure.

[0013] Figure 9 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0014] Figure 10 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0015] Figure 11 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0016] Figure 12 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0017] Figure 13 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0018] Figure 14A is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure.

[0019] Figure 14B and 14C Shown is a top view of one of a plurality of panels according to an embodiment of the present disclosure.

[0020] Figure 15 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0021] Figure 16 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity.

[0022] Figure 17 is a schematic cross-sectional view of one of the plurality of plates according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity and the second sub-cavity. DETAILED DESCRIPTION

[0023] Additional features, advantages, and embodiments of the present disclosure are set forth or become apparent from consideration of the following detailed description, drawings, and claims. In addition, it should be understood that both the foregoing summary 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.

[0024] 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.

[0025] In the following description and claims, there may be reference to a number of "optional" or "optionally" elements, meaning 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.

[0026] Approximate language used herein throughout the specification and claims can be applied to modify any quantitative expression that allows variation without causing a change in the basic function associated therewith. Therefore, the values ​​modified by one or more terms such as "about," "approximately," and "substantially" are not limited to the precise values ​​specified. In at least some cases, approximate language can correspond to the precision of the instrument used to measure the value. Here and throughout the specification and claims, range limitations can be combined and / or interchanged. Unless the context or language indicates otherwise, these ranges are identified and include all subranges contained therein.

[0027] As used herein, the terms "axial" and "axially" refer to directions and orientations that extend substantially parallel to the centerline of a turbine engine or combustor. Additionally, the terms "radial" and "radially" refer to directions and orientations that extend substantially perpendicular to the centerline of a turbine engine or fuel-air mixer assembly. Furthermore, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations that extend arcuately about the centerline of a turbine engine or fuel-air mixer assembly.

[0028] For a multi-spool gas turbine engine, the compressor section may include a high-pressure compressor (HPC) downstream of a low-pressure compressor (LPC), and the turbine section may similarly include a low-pressure turbine (LPT) downstream of a high-pressure turbine (HPT). With this configuration, the HPC is coupled to the HPT via a high-pressure spool (HPS), and the LPC is coupled to the LPT via a low-pressure spool (LPS). In operation, at least a portion of the air from the fan is provided to the inlet of the core. This air is gradually compressed by the LPC and then by the HPC until the compressed air reaches the combustion section. Fuel is mixed with the compressed air and combusted within the combustion section to produce combustion gases. The fuel, mixed with the compressed air and combusted within the combustion section, is delivered to the combustion section via fuel nozzles. From the combustion section, the combustion gases are directed through the HPT and then through the LPT. The combustion gas flow through the turbine section drives the HPT and LPT, which in turn drive a corresponding one of the HPC and LPC via the HPS and LPS. The combustion gases are then directed through an exhaust section, for example, to the atmosphere. The LPT drives the LPS, which drives the LPC. In addition to driving the LPC, the LPS can also drive a fan through a power gearbox, which allows the fan to rotate at fewer revolutions per unit time than the LPS for greater efficiency.

[0029] As will be described in further detail in the following paragraphs, the combustor has improved liner durability in harsh thermal and stress environments. The combustor includes a skeleton network structure (also known as a hanger or truss) on which an inner liner and an outer liner are mounted. The skeleton network structure as a whole serves as a support structure for the inner liner and the outer liner. In an embodiment, the skeleton network structure can be made of metal. The skeleton network structure, together with the inner liner and the outer liner, defines a combustion chamber. The inner liner and the outer liner include a plurality of plates. The plurality of plates cover at least the inner side of the skeleton network structure. In an embodiment, the plurality of plates can be made of ceramic material, ceramic matrix composite (CMC) material, or metal coated with CMC or thermal barrier coating (TBC). In an embodiment, the plurality of plates are exposed to hot flames. Each of the plurality of plates is hollow and includes an inner wall and an outer wall. The hollow plurality of plates provides liner protection in the event of primary surface damage caused by hot gases. The skeleton network structure, together with the plurality of plates, can improve durability by reducing or substantially eliminating hoop stress while providing a lightweight liner construction for the combustor. In addition, the use of multiple plates together with the skeleton mesh structure provides a modular or segmented construction that facilitates the manufacture and / or inspection, repair and replacement of each plate. In addition, the space inside each hollow plate can be subdivided into two or more cavities to form, for example, a double-layer cavity to damp combustion dynamic pressure oscillations. Various structures can be used to tune the hollow plate cavity to effectively damp a wide range of frequencies. In addition, at least one of the two or more cavities within the space inside each hollow plate is used as a damper. For example, two cavities within a plate can be tuned to act as dampers simultaneously and to reduce a wide range of combustion dynamic frequencies. Each of the multiple plates can be provided with an acoustic damping feature. Alternatively, one or more selected plates among the multiple plates can be provided with an acoustic damping feature. Any combination can be targeted at a certain range of frequencies.

[0030] Figure 1 is a schematic cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure. More specifically, Figure 1 In the embodiment shown, the turbine engine 10 is a high bypass turbine engine. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to a longitudinal centerline 12 for reference) and a radial direction R, which is generally perpendicular to the axial direction A. The turbine engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream of the fan section 14. The term "downstream" is used herein with reference to an air flow direction 58.

[0031] The depicted core turbine engine 16 generally includes a casing 18 that is substantially tubular and defines an annular inlet 20. The casing 18 encloses, in serial flow relationship, a compressor section including a supercharger or low-pressure compressor (LPC) 22 and a high-pressure compressor (HPC) 24, a combustion section 26, a turbine section including a high-pressure turbine (HPT) 28 and a low-pressure turbine (LPT) 30, and an exhaust nozzle section 32. A high-pressure spool (HPS) 34 drivingly connects the HPT 28 to the HPC 24. A low-pressure spool (LPS) 36 drivingly connects the LPT 30 to the LPC 22. The compressor section, combustion section 26, turbine section, and exhaust nozzle section 32 together define a core air flow path 37.

[0032] For the depicted embodiment, fan section 14 includes a variable pitch fan 38 having a plurality of fan blades 40 coupled to a disk 42 in a spaced-apart manner. As depicted, fan blades 40 extend generally outwardly from disk 42 along a radial direction R. Because fan blades 40 are operably coupled to suitable actuation members 44 that are configured to collectively change the pitch of fan blades 40 in unison, each fan blade 40 is rotatable relative to disk 42 about a pitch axis P. Fan blades 40, disk 42, and actuation members 44 are rotatable together about longitudinal centerline 12 (longitudinal axis) via LPS 36 across a power gearbox 46. Power gearbox 46 includes a plurality of gears for regulating or controlling the rotational speed of fan 38 relative to LPS 36 to a more efficient rotational fan speed.

[0033] The disk 42 is covered by a rotatable forward hub 48 having an aerodynamic profile to facilitate air flow through the plurality of fan blades 40. Additionally, the fan section 14 includes an annular fan case or nacelle 50 that circumferentially surrounds the fan 38 and / or at least a portion of the core turbine engine 16. The nacelle 50 may be configured to be supported relative to the core turbine engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Furthermore, a downstream section 54 of the nacelle 50 may extend over an outer portion of the core turbine engine 16 to define a bypass air flow passage 56 therebetween.

[0034] During operation of turbine engine 10, a volume of airflow 58 enters turbine engine 10 in an airflow direction 58 through nacelle 50 and / or associated inlet 60 of fan section 14. As the volume of air passes through fan blades 40, a first portion of the air, indicated by arrow 62, is directed or channeled into bypass air flow passage 56, and a second portion of the air, indicated by arrow 64, is directed or channeled into core air flow path 37, or more specifically, into LPC 22. The ratio between the first portion of air, indicated by arrow 62, and the second portion of air, indicated by arrow 64, is generally referred to as the bypass ratio. The pressure of the second portion of air, indicated by arrow 64, then increases as it is directed through HPC 24 and into combustion section 26, where it mixes with fuel and combusts to provide combustion gases 66.

[0035] Combustion gases 66 are directed through HPT 28, where a portion of thermal and / or kinetic energy from combustion gases 66 is extracted via successive stages of HPT stator vanes 68 coupled to casing 18 and HPT rotor blades 70 coupled to HPS 34, thereby causing HPS 34 to rotate, thereby supporting operation of HPC 24. Combustion gases 66 are then directed through LPT 30, where a second portion of thermal and kinetic energy is extracted from combustion gases 66 via successive stages of LPT stator vanes 72 coupled to casing 18 and LPT rotor blades 74 coupled to LPS 36, thereby causing LPS 36 to rotate, thereby supporting operation of LPC 22 and / or rotation of fan 38.

[0036] The combustion gases 66 are then directed through the exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 is significantly increased as it is directed through the bypass air flow passage 56 before being discharged from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. The HPT 28, LPT 30, and exhaust nozzle section 32 at least partially define a hot gas path 78 for directing the combustion gases 66 through the core turbine engine 16.

[0037] However, Figure 1 The turbine engine 10 depicted in FIG. 1 is merely an example, and in other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. In still other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of the present disclosure may be incorporated into, for example, a turboshaft engine, a turboprop engine, a turbocore engine, a turbojet engine, and the like.

[0038] Figure 2AAccording to an embodiment of the present disclosure Figure 1 FIG1 is a schematic longitudinal cross-sectional view of the combustion section 26 of the turbine engine 10. The combustion section 26 generally includes a combustor 80 that generates combustion gases that are discharged into the turbine section, or more specifically, into the HPT 28. The combustor 80 includes an outer liner 82, an inner liner 84, and a dome 86. The outer liner 82, the inner liner 84, and the dome 86 together define a combustion chamber 88 that extends about the longitudinal centerline 12. Additionally, a diffuser 90 is positioned upstream of the combustion chamber 88. The diffuser 90 has an outer diffuser wall 90A and an inner diffuser wall 90B. The inner diffuser wall 90B is closer to the longitudinal centerline 12. The diffuser 90 receives the air flow from the compressor section and provides a compressed air flow to the combustor 80. In an embodiment, the diffuser 90 provides the compressed air flow to a single circumferential row of fuel / air mixers 92. In an embodiment, the dome 86 of the combustor 80 is configured as a single annular dome, and the circumferential row of fuel / air mixers 92 is disposed within an opening formed in the dome 86 (the air supply dome or the combustor dome). However, in other embodiments, multiple annular domes may be used.

[0039] In an embodiment, the diffuser 90 can be used to slow down high-speed, highly compressed air from a compressor (not shown) to an optimal speed for the combustor 80. Furthermore, the diffuser 90 can be configured to minimize flow distortion by avoiding flow effects such as boundary layer separation. Like most other gas turbine engine components, the diffuser 90 is generally designed to be as light as possible to reduce the overall engine weight.

[0040] Fuel nozzles (not shown) provide fuel to the fuel / air mixer 92 depending on the desired performance of the combustor 80 under various engine operating conditions. Figure 2A In the illustrated embodiment, an outer shroud 94 (e.g., an annular shroud) and an inner shroud 96 (e.g., an annular shroud) are positioned upstream of the combustion chamber 88 to direct air flow into the fuel / air mixer 92. The outer shroud 94 and the inner shroud 96 can also direct a portion of the air flow from the diffuser 90 into an outer passage 98 defined between the outer liner 82 and the outer shell 100, and an inner passage 102 defined between the inner liner 84 and the inner shell 104. In addition, the inner support cone 106 is further shown as being connected to the nozzle support 108 using a plurality of bolts 110 and nuts 112. However, other combustion sections may include any other suitable structural configurations.

[0041] The combustor 80 also includes an igniter 114. The igniter 114 is configured to ignite a fuel / air mixture supplied to the combustion chamber 88 of the combustor 80. The igniter 114 is attached to the outer casing 100 of the combustor 80 in a substantially fixed manner. Additionally, the igniter 114 extends generally along the axial direction A2 and defines a distal end 116 that is positioned proximate an opening in a combustor member 120 of the combustion chamber 88. The distal end 116 is positioned proximate an opening 118 within the outer liner 82 of the combustor 80 to the combustion chamber 88.

[0042] In an embodiment, the dome 86 of the combustor 80, together with the outer liner 82, the inner liner 84, and the fuel / air mixers 92, provides a swirling flow 130 in the combustion chamber 88. As air enters the combustion chamber 88, it flows through the fuel / air mixers 92. The dome 86 and the fuel / air mixers 92 function to generate turbulence in the air flow, allowing the air to mix rapidly with the fuel. Each fuel / air mixer 92 (also known as a swirler) creates a localized low-pressure region that forces some of the combustion products to recirculate, as shown in FIG2 , producing the desired high turbulence.

[0043] Figure 2B According to an embodiment of the present disclosure Figure 1 FIG2 is a schematic transverse cross-sectional view of a combustor 80 of a turbine engine 10. The combustor 80 includes an outer liner 82 and an inner liner 84 extending about the turbine centerline 12 to define a combustion chamber 88. The outer liner 82 includes a skeletal lattice structure 300 (also known as a pylon or truss) and a plurality of hot side panels 302A and, optionally, a plurality of cold side panels 302B. The plurality of hot side panels 302A and the plurality of cold side panels 302B are mounted to the skeletal lattice structure 300 (outer lattice structure) of the outer liner 82. The inner liner 84 includes a skeletal lattice structure 301 (inner lattice structure) and a plurality of hot side panels 312A and, optionally, a plurality of cold side panels 312B. The plurality of hot side panels 312A and the plurality of cold side panels 312B are mounted to the skeletal lattice structure 301 of the inner liner 84. Skeleton mesh structure 300 serves as a support structure for hot side panels 302A and cold side panels 302B of outer liner 82. Skeleton mesh structure 301 serves as a support structure for hot side panels 312A and cold side panels 312B of inner liner 84. In an embodiment, skeleton mesh structures 300 and 301 are made of metal. Outer liner 82 is shown as having a generally cylindrical configuration. Inner liner 84 is similar to outer liner 82 in many respects. However, inner liner 84 has a smaller radius of curvature than outer liner 82.

[0044] A plurality of hot side panels 302A are mounted to and cover the inner side of the skeletal network structure 300, and a cold side panel 302B is mounted to and covers the outer side of the skeletal network structure 300. In this regard, the plurality of hot side panels 302A can be sized and shaped to mesh or connect together edge to edge and have abutting edges with no gaps between adjacent panels 302A. Similarly, the plurality of cold side panels 302B can be sized and shaped to mesh or connect together edge to edge and have abutting edges with no gaps between adjacent panels 302B. In other embodiments, gaps can be provided between adjacent panels 302A, 302B. A plurality of hot side panels 312A are mounted to and cover the outer side of the skeletal network structure 301, and a cold side panel 312B is mounted to and covers the inner side of the skeletal network structure 301. In this regard, the plurality of hot side panels 312A can be sized and shaped to mate or connect together edge to edge and have abutting edges without gaps between adjacent panels 312A. Similarly, the plurality of cold side panels 312B can be sized and shaped to mate or connect together edge to edge and have abutting edges without gaps between adjacent panels 312B. In other embodiments, gaps can be provided between adjacent panels 312A, 312B. The plurality of hot side panels 302A of the outer liner 82 and the plurality of hot side panels 312A of the inner liner 84 are exposed to the hot flames within the combustion chamber 88. In embodiments, the plurality of hot side panels 302A, 312A are made of ceramic or metal coated with a ceramic coating or thermal barrier coating to enhance resistance to relatively high temperatures. In embodiments, the plurality of hot side panels 302A, 312A can be made of a ceramic material, a ceramic matrix composite (CMC) material, or a metal coated with a CMC or thermal barrier coating (TBC). In an embodiment, the cold side plates 302B, 312B may be made of metal or ceramic matrix composite (CMC). In an embodiment, the cold side plates 302B, 312B are thinner than the plurality of hot side plates 302A, 312A. In an embodiment, as Figure 2B As shown, both the inner liner 84 and the outer liner 82 are shown as having a plurality of hot side panels 302A, 312A and a plurality of cold side panels 302B, 312B. In another embodiment, the plurality of cold side panels 302B, 312B may be optional for the outer liner 82, for the inner liner 84, or for both.

[0045] Figure 3 is a schematic perspective view of the outer liner 82 of the combustor 80 according to an embodiment of the present disclosure. Figure 3 In the figure, for the purpose of clarity, only the outer lining 82 is shown, and the inner lining 84 (FIG. 2) is omitted. Figure 3As shown, the outer liner 82 includes a skeleton mesh structure 300 (outer mesh structure), on which a plurality of hot side panels 302A and a plurality of cold side panels 302B are mounted. The plurality of hot side panels 302A and the plurality of cold side panels 302B are mounted to the skeleton mesh structure 300 of the outer liner 82. The skeleton mesh structure 300 serves as a support structure for the hot side panels 302A and the cold side panels 302B of the outer liner 82. In an embodiment, the skeleton mesh structure 300 is made of metal. The plurality of hot side panels 302A are mounted to and cover the inner side of the skeleton mesh structure 300, and the cold side panels 302B are mounted to and cover the outer side of the skeleton mesh structure 300. In this regard, as Figure 3 As shown, the plurality of hot side plates 302A and the plurality of cold side plates 302B can be sized and shaped to fit together and have abutting edges with no gaps between adjacent plates 302A and 302B. In other embodiments, gaps can be provided between adjacent plates 302A and 302B.

[0046] The skeleton lattice structure 300, together with the plurality of hot side panels 302A and the optional plurality of cold side panels 302B, can improve durability by reducing or eliminating hoop stresses, while providing a lightweight liner construction for the combustor 80. Similarly, the skeleton lattice structure 301, together with the plurality of hot side panels 312A and the optional plurality of cold side panels 312B ( FIG. 2 ), can improve durability by reducing or eliminating hoop stresses, while providing a lightweight liner construction for the combustor 80. For example, this construction provides a weight reduction of at least 20 percent compared to conventional combustors. Furthermore, this construction offers the added benefit of being modular or segmented, making it relatively easy to repair. In fact, if one or more of the plurality of hot side panels 302A, 312A or the plurality of cold side panels 302B, 312B become damaged, only the damaged one or more panels need to be replaced, rather than the entire inner liner 84 or the entire outer liner 82. Furthermore, this construction lends itself to relatively easy inspection and repair. All of these benefits result in overall cost savings.

[0047] Figure 4 FIG is a schematic diagram of a section of the inner liner 84 of the combustor 80 according to an embodiment of the present disclosure. Figure 4 As shown, a plurality of hot side panels 312A are mounted to the skeleton network structure 301. The plurality of hot side panels 312A include a plurality of external holes 400. The plurality of external holes 400 are distributed along the surface of the plurality of hot side panels 312A to allow air to enter the combustion chamber 88.

[0048] Figure 5 FIG is a schematic diagram of one of the plurality of hot side plates 312A mounted to the skeleton mesh structure 301 according to an embodiment of the present disclosure. Figure 5As shown, each of the plurality of hot side panels 312A is hollow and includes an inner wall 303A, an outer wall 303B, and a side wall 303C that define a cavity 302C. The hot side panel 312A may be referred to as a "hollow panel." The side wall 303C is coupled to the inner wall 303A (hot side wall) and the outer wall 303B (cold side wall). For example, the side wall 303C, the inner wall 303A (hot side wall), and the outer wall 303B (cold side wall) may be integrally formed. The plurality of hot side panels 312A that are hollow within the cavity 302C may provide lining protection in the event of primary surface damage due to hot gases. The skeleton mesh structure 301 may include a plurality of structural elements 306 that are connected or matched together to form Figure 4 The skeleton mesh structure 301 is shown. In an embodiment, each of the plurality of hot side panels 312A is mounted to the plurality of structural elements 306 of the skeleton mesh structure 301. In another embodiment, each of the plurality of hot side panels 312A is mounted between the plurality of structural elements 306 of the skeleton mesh structure 301. In an embodiment, the plurality of external holes 400 in the plurality of hot side panels 312A penetrate the outer wall 303B of the plurality of hot side panels 312A. In an embodiment, the plurality of external holes 400 are in communication with the cavity 302C to allow airflow from the outer wall 303B to enter the cavity 302C through the plurality of external holes 400 and allow airflow to impinge on the inner wall 303A and to circulate within the cavity 302C to cool the area facing the combustion chamber 88 ( Figure 2A and 2B 302C is divided into at least a first sub-chamber 500A and a second sub-chamber 500B using a partition wall 500C. The partition wall 500C is connected to the side wall 303C. In addition to the external holes 400, the plurality of hot side plates 312A are also provided with a plurality of external openings 600. In an embodiment, the plurality of external openings 600 are provided in the outer wall 303B. The plurality of external openings 600 are in communication with the first sub-chamber 500A to allow airflow to traverse the outer wall 303B and enter the first sub-chamber 500A through the plurality of external openings 600. In addition, as will be described in the following paragraphs, the plurality of external holes 400 are in communication with the second sub-chamber 500B to allow airflow to traverse the outer wall 303B and enter the second sub-chamber 500B through the plurality of external holes 400. The airflow passing through the plurality of external holes 400 impinges on the inner wall 303A and provides airflow circulation inside the second sub-chamber 500B to cool the inner wall 303A facing the combustion chamber 88. In an embodiment, the first sub-cavity 500A serves as a thermoacoustic resonator cavity, and the plurality of outer openings 600 serve as inlets to the thermoacoustic resonator cavity and for providing film cooling of the inner wall 303A.

[0049] Figure 6 According to the embodiment of the present disclosure Figure 5A schematic cross-sectional view of one of the plurality of hot side plates 312A at cross-sectional line 6-6 is shown, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 6 As shown, the plurality of hot side plates 312A include an inner wall 303A, an outer wall 303B, and a side wall 303C defining a cavity 302C. A plurality of outer holes 400 are provided in the outer wall 303B of the plurality of hot side plates 312A. In addition to the plurality of outer holes 400, a plurality of inner openings 402 are provided in the inner wall 303A of the plurality of plates 312A. In an embodiment, as shown in FIG. Figure 6 As shown, the plurality of outer holes 400 in the outer wall 303B of the plurality of hot side plates 312A are orthogonal holes relative to the outer wall 303B. In an embodiment, the plurality of inner openings 402 in the inner wall 303A of the plurality of hot side plates 312A are oblique holes relative to the inner wall 303A of the plurality of hot side plates 312A and communicate with the cavity 302C. Figure 6 As shown, chamber 302C is divided into at least a first sub-chamber 500A and a second sub-chamber 500B using a partition wall 500C. Partition wall 500C is connected to side wall 303C. In addition to external holes 400 and internal openings 402, hot side plate 312A is also provided with a plurality of external openings 600. In an embodiment, the plurality of external openings 600 are provided in outer wall 303B. The plurality of external openings 600 communicate with first sub-chamber 500A, allowing airflow to traverse outer wall 303B and enter first sub-chamber 500A through the plurality of external openings 600.

[0050] The plurality of outer holes 400 communicate with the second sub-cavity 500B through the plurality of tubes 400A to bypass the first sub-cavity 500A, while the plurality of inner openings 402 communicate directly with the second sub-cavity 500B. The airflow traversing the outer wall 303B passes through the plurality of outer holes 400 and enters the second sub-cavity 500B through the plurality of tubes 400A, allowing it to impinge on the inner wall 303A and provide airflow circulation inside the second sub-cavity 500B, thereby cooling the inner wall 303A facing the combustion chamber 88. The plurality of inner openings 402 (e.g., Figure 6 The plurality of hot side plates 312A (shown as inclined) are used to form a cooling air film on the surface of the inner wall 303A facing the hot gases inside the combustion chamber 88. In addition to the plurality of external holes 400, the plurality of internal openings 402, and the plurality of external openings 600, the plurality of hot side plates 312A may also include a plurality of side holes 403 disposed in the side wall 303C and communicating with the second sub-cavity 500B. The plurality of external holes 400, the plurality of internal openings 402, and the plurality of side holes 403 allow air to flow therethrough, entering and exiting the second sub-cavity 500B, thereby cooling the inner wall 303A of the plurality of hot side plates 312A facing the hot gases inside the combustion chamber 88. Because the inner wall 303A faces the hot gases inside the combustion chamber 88, the inner wall 303A may be provided with a thermal barrier coating (TBC) 303D.

[0051] In an embodiment, the inner wall 303A in the plurality of hot side plates 312A may further include one or more inner holes 404 connected to one or more bypass tubes 404A (resonator necks). The one or more inner holes 404 connect the first sub-cavity 500A to the combustion chamber 88. The one or more bypass tubes 404A also connect the one or more inner holes 404 to the first sub-cavity 500A while bypassing the second sub-cavity 500B. The airflow in the first sub-cavity 500A passes through the plurality of tubes 404A and enters the combustion chamber 88 without communicating with the second sub-cavity 500B. In an embodiment, as Figure 6 As shown, one or more bypass tubes 404A are angled relative to inner wall 303A of the plurality of hot side plates 312A facing the hot gases inside combustion chamber 88. One or more bypass tubes 404A may be used to tune the second subcavity 500B (resonator subcavity).

[0052] In an embodiment, the first sub-cavity 500A functions as a resonator cavity, and the plurality of external openings 600 are used to pressurize the thermoacoustic resonator cavity. In an embodiment, the first sub-cavity 500A can function as a thermoacoustic resonator cavity and be used to damp combustion dynamic oscillations. In an embodiment, the second sub-cavity 500B can function as a thermoacoustic resonator cavity and be used to damp combustion dynamic oscillations. In an embodiment, the thickness of the outer wall 303B can be approximately 0.05 inches. In an embodiment, the thickness of the inner wall 303A is approximately 0.06 inches. In an embodiment, the thickness of the thermal barrier coating is approximately 0.02 inches. In an embodiment, the thickness of the partition wall 500C is approximately 0.03 inches. In an embodiment, the width of the first sub-cavity 500A is approximately 0.04 inches. In an embodiment, the width of the second cavity is approximately 0.04 inches. The dimensions may vary + / - 20% about the average values ​​specified above.

[0053] Figure 7 is a top view of one of the plurality of hot side plates 312A, showing a plurality of external holes 400 and a plurality of external openings 600, according to an embodiment of the present disclosure. In an embodiment, the plurality of external holes 400 and the plurality of external openings 600 may be evenly distributed within the plurality of hot side plates 312A. In another embodiment, the plurality of external holes 400 and the plurality of external openings 600 may be unevenly distributed within the plurality of hot side plates 312A.

[0054] Figure 8 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 8 The embodiment shown is similar in many respects to Figure 7 Therefore, similar features will not be referenced. Figure 8However, in this embodiment, the one or more bypass tubes 404A (resonator necks) are substantially perpendicular relative to the inner walls 303A of the plurality of hot side panels 312A that face the hot gases inside the combustion chamber 88 .

[0055] Figure 9 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 9 The embodiment shown is similar in many respects to Figure 8 Therefore, similar features will not be discussed with respect to Figure 9 404A) and the one or more openings 402. The one or more second inner openings 802 connect the second sub-cavity 500B to the combustion chamber 88. In addition to the one or more inner openings 402, the airflow within the second sub-cavity 500B can also exit through the one or more second inner openings 802. In an embodiment, the one or more second inner openings 802, similar to the one or more bypass ducts 404A, can also be used to tune the second sub-cavity 500B. In an embodiment, the one or more second inner openings 802 and the one or more bypass ducts 404A can be positioned substantially perpendicular to the inner wall 303A of the plurality of hot side plates 312A facing the hot gases inside the combustion chamber 88.

[0056] Figure 10 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 10 The embodiment shown is similar in many respects to Figure 9 Therefore, similar features will not be discussed with respect to Figure 10 Detailed description is provided below. However, in this embodiment, the one or more second inner openings 802 and the one or more bypass tubes 404A may be arranged at an angle relative to the inner wall 303A of the plurality of hot side plates 312A facing the hot gases inside the combustion chamber 88. The one or more second inner openings 802 connect the second sub-cavity 500B to the combustion chamber 88. In addition to passing through the plurality of inner openings 402, the airflow within the second sub-cavity 500B may also exit through the one or more second inner openings 802. In embodiments, the one or more second inner openings 802, similar to the one or more bypass tubes 404A, may also be used to tune the second sub-cavity 500B.

[0057] Figure 11is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 11 The embodiment shown is similar in many respects to Figure 9 Therefore, similar features will not be discussed with respect to Figure 11 In this embodiment, cavity 302C also uses the same Figure 9 The partition wall 500C is similar to the partition wall 1100, which is divided into at least a first sub-cavity 500A and a second sub-cavity 500B. However, the partition wall 1100 is wavy or corrugated, while the partition wall 500C is straight. Similar to the partition wall 500C, the partition wall 1100 is also connected to the side wall 303C of the plurality of hot side plates 312A. The waviness of the partition wall 1100 can further be used to tune the first sub-cavity 500A (resonator cavity) and / or the second sub-cavity 500B (resonator cavity). By controlling the impingement distance of the flow emitted from the one or more inner holes 404 through the one or more bypass tubes 404A, the waviness of the partition wall 1100 can also be used to optimize the impingement cooling efficiency for cooling the inner wall 303A (hot side wall).

[0058] Figure 12 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 12 The embodiment shown is similar in many respects to Figure 11 Therefore, similar features will not be discussed with respect to Figure 11 In this embodiment, the cavity 302C is also divided into at least a first sub-cavity 500A and a second sub-cavity 500B using a partition wall 1100. Figure 12 As shown, the partition wall 1100 is also wavy or corrugated. In addition, instead of the straight outer wall 303B ( Figure 11 ), the outer wall 1200 is wavy or corrugated. The waviness of the outer wall 1200 can be further used to tune the first sub-cavity 500A (resonator cavity). In addition, the waviness of the partition wall 1100 can be further used to tune the first sub-cavity 500A (resonator cavity) and / or the second sub-cavity 500B (resonator cavity).

[0059] Figure 13 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 13 The embodiment shown is similar in many respects to Figure 6 Therefore, similar features will not be discussed with respect to Figure 13In this embodiment, the cavity 302C is also divided into at least a first sub-cavity 500A and a second sub-cavity 500B using a partition wall 500C. Figure 13 As shown, a portion 1301 of the partition wall 500C is common to both the first sub-chamber 500A and the second sub-chamber 500B. However, another portion 1302 of the partition wall 500C is only a wall in the second sub-chamber 500B, not in the first sub-chamber 500A. The length of the first sub-chamber 500A is less than the length of the second sub-chamber 500B. Similarly, the length of the outer wall 303B is less than the length of the inner wall 303A. In an embodiment, a plurality of holes 1304 are provided in the portion 1302 of the partition wall 500C. The plurality of holes 1304 are provided to allow airflow from outside the plurality of hot side plates 312A to enter the second sub-chamber 500B of the plurality of hot side plates 312A. In addition, similar to Figure 6 In the embodiment shown, a plurality of external holes 400 are provided in the outer wall 303B and communicate with the second sub-cavity 500B via a plurality of tubes 400A. Figure 6 In the embodiment shown, a plurality of external openings 600 are also provided in the outer wall 303B and are in direct communication with the first sub-cavity 500A. By providing the first sub-cavity 500A on top of the second sub-cavity 500B, as shown in FIG. Figure 13 As shown, the volume of the first sub-cavity 500A may be selected to tune the resonance of the first sub-cavity 500A to dampen thermoacoustic combustion dynamic frequencies within the combustion chamber 88 .

[0060] Figure 14A FIG. 1 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure. Figure 14A As shown, the plurality of hot side plates 312A include a first sub-cavity 1402 and a second sub-cavity 1404. The first sub-cavity 1402 and the second sub-cavity may be similar to the first sub-cavity 500A and the second sub-cavity 500B, respectively. Figure 14A As shown, for example, the first subcavity 1402 can have a trapezoidal cross-sectional shape. However, other shapes can also be used.

[0061] Figure 14B and 14C A top view of one of the plurality of hot side plates 312A is shown according to an embodiment of the present disclosure. Figure 14B A rectangular shaped (eg, with rounded corners) footprint of a first sub-cavity 1402 and a rectangular footprint of a second sub-cavity 1404 are shown. Figure 14C An elliptical or more circular footprint is shown for the first subcavity 1402 and a rectangular footprint is shown for the second subcavity 1404. Although specific footprints for the first subcavity 1402 and the second subcavity 1404 are shown, other footprint shapes may be used.

[0062] Figure 15 FIG. 1 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 15 As shown, a plurality of hot side plates 312A are coupled to the skeleton network structure 301 using a plurality of fasteners 1500. A plurality of openings 311 are provided within the skeleton network structure 301 to accommodate the plurality of hot side plates 312A. The plurality of hot side plates 312A include an inner wall 303A, an outer wall 303B, and a side wall 303C defining a cavity 302C. For example, Figure 15 As shown, the outer wall 303B is inserted into the opening 311 of the skeleton network structure 301. The opening 311 can be adjusted in size to fit the outer wall 303B. Figure 15 In the embodiment shown, the plurality of hot side plates 312A include a plurality of structural walls (eg, three structural walls) 1501. Figure 15 As shown, the outermost structural wall 1509 of the structural walls 1501 is used to couple the plurality of hot side plates 312A to the skeletal network structure 301. The plurality of side walls 303C are located between the plurality of structural walls 1501.

[0063] A plurality of outer holes 400 are provided in the outer wall 303B of the plurality of hot side plates 312A. In addition to the plurality of outer holes 400, a plurality of inner openings 402 are provided in the inner wall 303A of the plurality of plates 302. In an embodiment, the plurality of outer holes 400 in the outer wall 303B of the plurality of hot side plates 312A are orthogonal holes with respect to the outer wall 303B. In an embodiment, the plurality of inner openings 402 in the inner wall 303A of the plurality of hot side plates 312A are oblique holes with respect to the inner wall 303A of the plurality of hot side plates 312A, and are in communication with the cavity 302C. The cavity 302C is divided into at least a first sub-cavity 500A and a second sub-cavity 500B using a partition wall 500C. In an embodiment, the partition wall 500C is connected to the side wall 303C. As Figure 15 As shown, a plurality of openings 1505 are provided in the skeleton mesh structure 301 to allow airflow into the side cavity 1507. The side cavity 1507 is defined by at least the skeleton mesh structure 301, the inner wall 303A, the side wall 303C, and the structural walls 1508 and 1509. The structural walls 1508 and 1509 are in contact with the skeleton mesh structure 301.

[0064] The plurality of outer holes 400 communicate with the second sub-cavity 500B through the plurality of tubes 400A to bypass the first sub-cavity 500A, while the plurality of inner openings 402 communicate directly with the second sub-cavity 500B. The airflow that traverses the outer wall 303B passes through the plurality of outer holes 400 and enters the second sub-cavity 500B through the plurality of tubes 400A, allowing it to impinge on the inner wall 303A and allow the airflow to circulate within the second sub-cavity 500B, thereby cooling the inner wall 303A facing the combustion chamber 88. The plurality of inner openings 402 (e.g., at Figure 15 88) is used to form a cooling air film on the surface of the inner wall 303A facing the hot gas inside the combustion chamber 88.

[0065] In an embodiment, the plurality of hot side plates 312A may further include one or more bypass tubes 404A (resonator necks) that connect the first sub-cavity 500A to the combustion chamber 88. The one or more bypass tubes 404A bypass the second sub-cavity 500B. The airflow in the first sub-cavity 500A passes through the plurality of tubes 404A and enters the combustion chamber 88 without communicating with the second sub-cavity 500B. In an embodiment, as Figure 15 As shown, one or more bypass tubes 404A are angled relative to the inner wall 303A of the plurality of hot side panels 312A facing the hot gases inside the combustion chamber 88. The one or more bypass tubes 404A can be used to tune the second sub-cavity 500B (resonator sub-cavity). In this embodiment, the first sub-cavity 500A and the second sub-cavity 500B (either of which can operate as an acoustic damper resonator) are disposed in the inner liner 84 ( Figure 2B ) within the incision of the skeleton network structure 301.

[0066] Figure 16 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 16 The embodiment shown is similar in many respects to Figure 15 The embodiment shown is similar. Therefore, common features will not be further described herein. Instead of openings 311 provided within the skeleton network structure 301 to accommodate the plurality of hot side plates 312A, a plurality of holes 1600 are provided within the skeleton network structure 301 to fluidically connect with a plurality of external holes 400 provided in the outer walls 303B of the plurality of hot side plates 312A, which are connected to a plurality of tubes 400A that bypass the first sub-cavity 500A. The plurality of hot side plates 312A are coupled to the skeleton network structure 301 using support members 1602 and fasteners 1604. In this embodiment, the first sub-cavity 500A and the second sub-cavity 500B are defined by the inner wall 303A, the outer wall 303B, the side wall 303C, and the partition wall 500C. The side wall 303C is disposed between the support members 1602. In this embodiment, a first sub-cavity 500A and a second sub-cavity 500B (either or both of which may operate as acoustic damper resonators) are disposed within the inner liner 84 ( Figure 2B ) within the skeleton network structure 301.

[0067] Figure 17 is a schematic cross-sectional view of one of the plurality of hot side plates 312A according to another embodiment of the present disclosure, showing the arrangement of the first sub-cavity 500A and the second sub-cavity 500B. Figure 17The embodiment shown is similar in many respects to Figure 16 The embodiment shown is similar. In this embodiment, the first sub-cavity 500A and the second sub-cavity 500B are defined by the inner wall 303A, the outer wall 303B and the side wall 303C. The side wall 303C serves as a support member and is connected to the skeleton mesh structure 301 of the inner liner 84 using a plurality of fasteners 1702. In this embodiment, the first sub-cavity 500A and the second sub-cavity 500B (either or both can operate as acoustic damper resonators) are coupled to the inner liner 84 ( Figure 2B ) of the skeleton network structure 301.

[0068] The various features described above are described with respect to one or more of the plurality of hot side plates 312A. However, alternatively or additionally, any one or more of the various features described above with respect to one or more of the plurality of hot side plates 312A may also be provided in one or more of the plurality of hot side plates 302A. One or more of the plurality of hot side plates 312A and one or more of the plurality of hot side plates 302A may generally be referred to as hollow plates.

[0069] It can be understood from the above paragraphs that the cavity within the hollow plate can be divided into two or more sub-cavities. For example, the cavity within the hollow plate can be divided into a first sub-cavity 500A and a second cavity 500B. For example, the first sub-cavity 500A and / or the second sub-cavity 500B can be used as a thermoacoustic resonator cavity. The holes, openings and / or bypass pipes provided in the hollow cavity can be used to frequency tune the first sub-cavity 500A and / or the second sub-cavity 500B to reduce combustion dynamic frequency or pressure oscillations. In an embodiment, each plate can be provided with a cavity to provide an acoustic damping arrangement. In another embodiment, a selected number of plates can be provided with cavities to provide an acoustic damping arrangement.

[0070] Further aspects are provided by the subject matter of the following clauses:

[0071] A hollow plate of a combustor liner defining a combustion chamber comprises: an inner wall having a plurality of inner openings and one or more inner holes; an outer wall having one or more outer openings and a plurality of outer holes; a plurality of side walls coupled to the inner and outer walls to define a cavity; and a divider wall coupled to the side walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The outer wall, the divider wall, and the side walls define the first sub-cavity. The inner wall, the divider wall, and the side walls define the second sub-cavity. The one or more outer openings in the outer wall communicate with the first sub-cavity. The multiple outer holes in the outer wall communicate with the second sub-cavity via a plurality of tubes, thereby bypassing the first sub-cavity. The multiple inner openings in the inner wall communicate with the second sub-cavity. The one or more inner holes in the inner wall communicate with the first sub-cavity via one or more bypass tubes, thereby bypassing the second sub-cavity. The first sub-cavity, the second sub-cavity, or both are frequency-tuned to reduce combustion dynamic frequencies.

[0072] The hollow plate according to the preceding clause, said one or more internal holes together with said one or more bypass tubes being configured to tune said first sub-cavity to damp said combustion dynamic frequencies.

[0073] The hollow panel according to any of the preceding clauses, the inner wall comprising a thermal barrier coating (TBC) to protect the inner wall from hot gases inside the combustion chamber.

[0074] A hollow panel according to any of the preceding clauses, wherein the plurality of outer holes in the outer wall are normal or inclined relative to the outer wall.

[0075] A hollow panel as in any of the preceding clauses, wherein the one or more outer openings in the outer wall are normal or inclined relative to the outer wall.

[0076] The hollow panel according to any of the preceding clauses, the plurality of inner openings in the inner wall being normal or inclined relative to the inner wall.

[0077] The hollow plate according to any of the preceding clauses, wherein the one or more bypass pipes are perpendicular or inclined relative to the inner wall.

[0078] The hollow plate according to any of the preceding clauses, the inner wall further comprising one or more second inner openings, the one or more second inner openings being arranged to frequency tune the second sub-cavity.

[0079] The hollow panel according to any of the preceding clauses, wherein the one or more second inner openings are normal or inclined relative to the inner wall.

[0080] The hollow plate according to any of the preceding clauses, wherein the plurality of side walls comprise a plurality of side holes communicating with the second sub-cavity.

[0081] A hollow panel as claimed in any preceding clause, wherein the partition walls are corrugated.

[0082] A hollow panel as claimed in any preceding clause, wherein the outer wall is corrugated.

[0083] A hollow panel according to any of the preceding clauses, wherein the first subcavity has a trapezoidal cross-sectional shape.

[0084] The hollow panel according to any of the preceding clauses, wherein the first subcavity has a rectangular footprint or an elliptical footprint.

[0085] A hollow panel as in any preceding clause having walls coupled to the skeletal network using a plurality of fasteners.

[0086] A hollow panel according to any of the preceding clauses, further comprising a plurality of side cavities, and a plurality of openings are provided in the skeleton mesh structure to allow airflow to pass into the plurality of side cavities.

[0087] A hollow panel according to any of the preceding clauses, wherein the hollow panel is housed within an opening provided within the skeletal network.

[0088] A hollow panel according to any of the preceding clauses, wherein the hollow panel is coupled to the skeletal network structure such that a plurality of pores provided within the skeletal network structure are in fluid communication with the plurality of outer pores provided in the outer wall of the hollow panel.

[0089] A hollow panel as in any of the preceding clauses, wherein the sidewalls 303C are connected to the skeletal network using a plurality of fasteners.

[0090] A combustor includes a combustor liner defining a combustion chamber. The combustor liner includes a skeletal lattice structure and a plurality of hollow plates coupled to the skeletal lattice structure. One or more of the hollow plates include an inner wall having a plurality of inner openings and one or more inner holes; an outer wall having one or more outer openings and a plurality of outer holes; a plurality of side walls coupled to the inner and outer walls to define a cavity; and a partition wall connected to the side walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The outer wall, the partition wall, and the plurality of side walls define the first sub-cavity. The inner wall, the partition wall, and the plurality of side walls define the second sub-cavity. The one or more outer openings in the outer wall communicate with the first sub-cavity. The plurality of outer holes in the outer wall communicate with the second sub-cavity via a plurality of tubes, thereby bypassing the first sub-cavity. The plurality of inner openings in the inner wall communicate with the second sub-cavity. The one or more inner holes in the inner wall communicate with the first sub-cavity via one or more bypass tubes, thereby bypassing the second sub-cavity. The first sub-cavity or the second sub-cavity or both are frequency tuned to reduce combustion dynamic frequencies generated by the combustion chamber.

[0091] The burner according to the preceding clause, wherein the one or more internal holes together with the one or more bypass tubes are configured to tune the first sub-cavity to damp the combustion dynamic frequencies.

[0092] The combustor of any of the preceding clauses, the inner wall comprising a thermal barrier coating (TBC) to protect the inner wall from hot gases inside the combustion chamber.

[0093] A burner according to any of the preceding clauses, wherein the plurality of external holes in the outer wall are normal or inclined relative to the outer wall.

[0094] A burner according to any of the preceding clauses, wherein the one or more outer openings in the outer wall are normal or inclined relative to the outer wall.

[0095] The burner according to any of the preceding clauses, the plurality of inner openings in the inner wall being normal or inclined relative to the inner wall.

[0096] The burner according to any of the preceding clauses, wherein the one or more bypass ducts are perpendicular or inclined relative to the inner wall.

[0097] The burner according to any of the preceding clauses, the inner wall further comprising one or more second inner openings, the one or more second inner openings being arranged to frequency tune the second sub-cavity.

[0098] The burner according to any of the preceding clauses, wherein the one or more second inner openings are normal or inclined relative to the inner wall.

[0099] The burner according to any of the preceding clauses, wherein the plurality of side walls comprises a plurality of side holes communicating with the second sub-cavity.

[0100] The burner according to any of the preceding clauses, wherein the dividing wall is corrugated.

[0101] Burner according to any of the preceding clauses, wherein the outer wall is corrugated.

[0102] The burner of any of the preceding clauses, wherein the skeletal network structure comprises a plurality of openings to accommodate a plurality of hot side plates.

[0103] The burner of any of the preceding clauses, the skeletal network structure comprising a plurality of holes in fluid communication with the plurality of external holes in the outer wall.

[0104] Although the foregoing description is directed to preferred embodiments of the present disclosure, other variations 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, 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 hollow plate of a burner liner defining a combustion chamber, characterized in that The hollow plate comprises: an inner wall having a plurality of inner openings and one or more inner holes; an outer wall having one or more outer openings and a plurality of outer holes; a plurality of side walls coupled to the inner wall and the outer wall to define a cavity; and a partition wall connected to the plurality of side walls, disposed between the inner wall and the outer wall, and dividing the cavity into a first sub-cavity and a second sub-cavity, wherein the outer wall, the partition wall, and the plurality of side walls define the first sub-cavity, and the inner wall, the partition wall, and the plurality of side walls define the second sub-cavity, wherein the one or more external openings in the outer wall are in communication with the first sub-cavity, wherein the plurality of external holes in the outer wall are connected to the second sub-cavity through a plurality of tubes to bypass the first sub-cavity, wherein the plurality of inner openings in the inner wall are in communication with the second sub-cavity, wherein the one or more inner holes in the inner wall are connected to the first sub-cavity through one or more bypass pipes to bypass the second sub-cavity, and The first sub-cavity or the second sub-cavity or both are frequency tuned to reduce combustion dynamic frequencies.

2. The hollow plate according to claim 1, characterized in that The one or more inner holes and the one or more bypass tubes are configured to tune the first sub-cavity to damp the combustion dynamic frequency.

3. The hollow plate according to claim 1, characterized in that The inner wall includes a thermal barrier coating (TBC) to protect the inner wall from hot gases inside the combustion chamber.

4. The hollow plate according to claim 1, characterized in that The plurality of external holes in the outer wall are orthogonal to the outer wall.

5. The hollow plate according to claim 1, characterized in that The one or more outer openings in the outer wall are orthogonal to the outer wall.

6. The hollow plate according to claim 1, characterized in that The plurality of inner openings in the inner wall are inclined relative to the inner wall.

7. The hollow plate according to claim 1, characterized in that The one or more bypass pipes are vertical or inclined relative to the inner wall.

8. The hollow plate according to claim 1, characterized in that The plurality of side walls include a plurality of side holes communicating with the second sub-cavity.

9. The hollow plate according to claim 1, characterized in that: The inner wall further comprises one or more second inner openings, and the one or more second inner openings are configured to frequency tune the second sub-cavity.

10. The hollow plate according to claim 9, characterized in that The one or more second inner openings are perpendicular or inclined relative to the inner wall.

11. A burner, characterized in that: include: A combustor liner defining a combustion chamber, the combustor liner comprising: skeletal network structure; and A plurality of hollow panels, the plurality of hollow panels being coupled to the skeleton network structure, one or more of the plurality of hollow panels comprising: an inner wall having a plurality of inner openings and one or more inner holes; an outer wall having one or more outer openings and a plurality of outer holes; a plurality of side walls coupled to the inner wall and the outer wall to define a cavity; and a partition wall connected to the plurality of side walls, disposed between the inner wall and the outer wall, and dividing the cavity into a first sub-cavity and a second sub-cavity, wherein the outer wall, the partition wall, and the plurality of side walls define the first sub-cavity, and the inner wall, the partition wall, and the plurality of side walls define the second sub-cavity, wherein the one or more external openings in the outer wall are in communication with the first sub-cavity, wherein the plurality of external holes in the outer wall are connected to the second sub-cavity through a plurality of tubes to bypass the first sub-cavity, wherein the plurality of inner openings in the inner wall are in communication with the second sub-cavity, wherein the one or more inner holes in the inner wall are connected to the first sub-cavity through one or more bypass pipes to bypass the second sub-cavity, and Wherein the first sub-cavity or the second sub-cavity or both are frequency tuned to reduce combustion dynamic frequencies generated by the combustion chamber.

12. The burner according to claim 11, characterized in that The one or more internal holes and the one or more bypass tubes are configured to tune the first sub-cavity to damp the combustion dynamic frequencies.

13. The burner according to claim 11, characterized in that The inner wall includes a thermal barrier coating (TBC) to protect the inner wall from hot gases inside the combustion chamber.

14. The burner according to claim 11, characterized in that The plurality of external holes in the outer wall are orthogonal to the outer wall.

15. The burner according to claim 11, characterized in that The one or more outer openings in the outer wall are orthogonal to the outer wall.

16. The burner according to claim 11, characterized in that The plurality of inner openings in the inner wall are inclined relative to the inner wall.

17. The burner according to claim 11, characterized in that The one or more bypass pipes are vertical or inclined relative to the inner wall.

18. The burner according to claim 11, characterized in that The plurality of side walls include a plurality of side holes communicating with the second sub-cavity.

19. The burner according to claim 11, characterized in that The inner wall includes one or more second inner openings, and the one or more second inner openings are configured to frequency tune the second sub-cavity.

20. The burner according to claim 19, characterized in that The one or more second inner openings are perpendicular or inclined relative to the inner wall.

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