Combustor with dilution hole structure

Abstract

A combustor includes a skeleton structure. The combustor further includes at least one liner operably coupled to the skeleton structure to at least partially define a combustion chamber, and a plurality of first plates mounted to a first side of the at least one liner and a plurality of second plates mounted to a second side of the at least one liner. The combustor also includes at least one dilution hole structure disposed with a portion of the skeleton structure and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to combustors, and in particular, to combustors having a dilution hole structure with a plurality of dilution holes. BACKGROUND

[0002] A gas turbine engine generally includes a fan and a core arranged in flow communication with one another, with the core disposed downstream of the fan in a flow direction through the gas turbine engine. The core of the gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. For a multi-spool gas turbine engine, the compressor section can include a high pressure compressor (HPC) disposed downstream of a low pressure compressor (LPC), and the turbine section can similarly include a low pressure turbine (LPT) disposed downstream of a high pressure turbine (HPT). With this configuration, the HPC is coupled with the HPT via a high pressure spool (HPS), and the LPC is coupled with the LPT via a low pressure spool (LPS). In operation, at least a portion of air on the fan is provided to an inlet of the core. This portion of air is progressively compressed by the LPC and then 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 combustion gases are directed from the combustion section through the HPT and then through the LPT. The flow of combustion gases through the turbine section drives the HPT and the LPT, which in turn each drive a respective one of the HPC and the LPC via the HPS and the LPS. The combustion gases are then directed through the exhaust section, e.g., to the atmosphere. The LPT drives the LPS, which drives the LPC. In addition to driving the LPC, the LPS can also drive the fan through a power gear box, which allows the fan to rotate at fewer revolutions per unit time than the rotational speed of the LPS for greater efficiency.

[0003] The fuel that is mixed with the compressed air and combusted within the combustion section is delivered through a fuel nozzle. BRIEF DESCRIPTION OF DRAWINGS

[0004] The foregoing and other features and advantages will be more readily understood from the following description, taken in conjunction with the various example embodiments illustrated in the drawings, in which like reference numerals generally indicate identical, functionally similar, and / or structurally similar elements.

[0005] Figure 1 is a schematic cross-sectional view of a turbine engine in accordance with an embodiment of the present disclosure.

[0006] Figure 2 is a schematic cross-sectional view of a turbine engine in accordance with an embodiment of the present disclosure. Figure 1 is a schematic cross-sectional view of a combustion section of a turbine engine in accordance with an embodiment of the present disclosure.

[0007] Figure 3is a schematic perspective view of a section of a burner according to an embodiment of the present disclosure.

[0008] Figure 4 is a schematic perspective view of a section of an inner liner and an outer liner of a burner according to an embodiment of the present disclosure.

[0009] Figure 5A is a schematic top view of one or more beams of a skeletal mesh according to an embodiment of the present disclosure, showing a plurality of dilution holes.

[0010] Figure 5B is a schematic perspective view of one or more beams of a skeletal mesh according to an embodiment of the present disclosure, showing a plurality of dilution holes and a plurality of cooling holes.

[0011] Figure 6 is a schematic perspective view of a section of an inner liner and an outer liner of a burner according to another embodiment of the present disclosure.

[0012] Figure 7 is a perspective view of one or more dilution hole plates mounted to a skeletal mesh according to an embodiment of the present disclosure, showing a plurality of dilution holes and a peripheral or edge cooling channel.

[0013] Figure 8A and 8B are cross-sectional views of one or more dilution hole plates mounted to a skeletal mesh according to various embodiments of the present disclosure.

[0014] Figures 9A to 9E are cross-sectional views of one or more dilution hole plates mounted to a skeletal mesh according to various embodiments of the present disclosure, showing various configurations of one or more dilution holes.

[0015] Figures 10A to 10E show various geometric configurations of structural elements of a skeletal mesh shown in Figures Figure 3 , 4 and 6 according to various embodiments of the present disclosure.

[0016] Figures 11A to 11E show various geometric configurations of plates in a plurality of inner plates and a plurality of outer plates according to various embodiments of the present disclosure.

[0017] Figure 12A and 12B is a schematic cross-sectional view of a burner using a skeletal mesh along with a plurality of inner plates according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0018] Additional features, advantages, and embodiments of the present disclosure are set forth in the detailed description, the appended claims, and the accompanying drawings. Moreover, both the foregoing summary and the following detailed description are exemplary and intended to provide further explanation of the disclosure, as claimed.

[0019] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is merely for illustrative purposes. Those skilled in the relevant art will recognize that other components and configurations can be used without departing from the spirit and scope of the present disclosure.

[0020] In the following description and claims, reference can be made to a number of "optional" or "optionally" elements, meaning that the subsequently described event or circumstance can or can not occur, and that the description includes instances where the event occurs and instances where the event does not occur.

[0021] The terms "coupled," "fixed," "attached to," and the like, mean either a direct coupling, fixation, or attachment, as well as an indirect coupling, fixation, or attachment via one or more intermediary components or features, unless specifically stated to the contrary.

[0022] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0023] As used herein, the terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0024] The terms "forward" and "aft" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust.

[0025] The terms "upstream" and "downstream" refer to the relative direction with respect to the flow in a path. For example, for a fluid flow, "upstream" refers to the direction from which the fluid flows and "downstream" refers to the direction to which the fluid flows. The term "fluid" can be a gas or a liquid. The term "fluid communication" means that a fluid is able to establish a connection between designated areas.

[0026] Approximating language can be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as "about" and "substantially," can not to be limited to the precise value specified. In at least some instances, an approximation can correspond to the precision of an instrument for measuring the value. For example, an approximation can be within 1%, 2%, 4%, 5%, 10%, 15%, or 20% of a single value, a range of values, and / or an end point of a range of values. Ranges can be combined and / or interchanged. Unless otherwise specified, these ranges are identified and include all sub-ranges therein. Here and throughout the specification and claims, ranges are used as endpoints only when otherwise explicitly

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

[0028] As will be described in further detail in the following paragraphs, the combustor has improved liner durability under harsh thermal and stress environments. The combustor includes a skeletal mesh (also referred to as a hanger or truss) to which an inner liner and an outer liner are coupled. The skeletal mesh functions as a support structure for the inner liner and the outer liner as a whole. In embodiments, the skeletal mesh can be made of metal. The skeletal mesh, together with the inner liner and the outer liner, defines a combustion chamber. The inner liner and the outer liner include a plurality of inner panels. The plurality of inner panels covers at least an inner side of the skeletal mesh. In embodiments, the plurality of inner panels can be made of a ceramic material, a ceramic matrix composite (CMC) material, or a metal coated with a CMC or a thermal barrier coating (TBC). In embodiments, the plurality of inner panels are exposed to hot flames. The connection interface of the plurality of inner panels to the skeletal mesh can be configured to be thermally expansion resistant. Further, the plurality of inner panels coupled to the interface of the skeletal mesh can be configured to improve performance by reducing or substantially eliminating air leakage, such that the interface does not affect NOx emissions. xAerodynamics of hot field and film cooling. Dilution holes can be provided on the crossbeams of the skeleton mesh or on separate dilution hole plates attached to the skeleton mesh. The holes can have various patterns and shapes. The parametric relationship of the dilution holes, cooling holes, and plate area is defined using ratios. Dilution hole plate connection fasteners include but are not limited to bolts, pins, clips, etc. Other attachment methods include using brazing, welding, adhesives, spring clips, piston seals, W-seals, and gang channel slides, etc. W-seals are W-shaped seals that can be provided to limit air leakage. This construction provides increased time on wing (TOW) and fuel burn benefits due to weight reduction, in addition to significantly increasing the durability of the combustor. This further provides a lightweight design of greater than twenty percent weight reduction, overall manufacturing cost savings, and relatively easier maintenance and repair.

[0029] Figure 1 is a schematic cross-sectional view of a turbine engine 10 according to embodiments of the present disclosure. More specifically, for the embodiment shown, Figure 1 Turbine engine 10 is a high-bypass turbine engine. As Figure 1 shown, turbine engine 10 defines an axial direction A (extending parallel to a longitudinal centerline 12 for reference) and a radial direction R, generally perpendicular to the axial direction A. Turbine engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream from fan section 14. The term "downstream" is used herein with reference to the direction of air flow 58.

[0030] Core turbine engine 16, as depicted, generally includes an outer casing 18 that is substantially tubular and defines an annular inlet 20. Outer casing 18 encases, in serial flow relationship, a compressor section including a booster 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 injection exhaust nozzle section 32. A high pressure shaft (HPS) 34 drivingly connects HPT 28 to HPC 24. A low pressure shaft (LPS) 36 drivingly connects LPT 30 to LPC 22. The compressor section, combustion section 26, turbine section, and injection exhaust nozzle section 32 together define a core air flowpath 37.

[0031] For the depicted embodiment, the fan section 14 includes a fan 38 having a variable pitch, the fan 38 having a plurality of fan blades 40 coupled to a disk 42 in a spaced apart manner. As depicted, the fan blades 40 extend outwardly from the disk 42 generally along a radial direction R. As the fan blades 40 are operably coupled to a suitable actuation member 44, the actuation member 44 is configured to uniformly collectively change the pitch of the fan blades 40, each fan blade 40 is therefore able to rotate about a pitch axis P relative to the disk 42. The fan blades 40, the disk 42, and the actuation member 44 are able to rotate together about the longitudinal centerline 12 (longitudinal axis) by the LPS 36 across a power gear box 46. The power gear box 46 includes a plurality of gears for adjusting or controlling the rotational speed of the fan 38 relative to the LPS 36 to a more efficient rotational fan speed.

[0032] The disk 42 is covered by a rotatable front hub 48 having an aerodynamic profile to facilitate airflow 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 can be configured to be supported relative to the core turbine engine 16 by a plurality of circumferentially spaced apart outlet guide vanes 52. Moreover, a downstream section 54 of the nacelle 50 can extend over an outer portion of the core turbine engine 16 so as to define a bypass airflow passage 56 therebetween.

[0033] During operation of the turbine engine 10, an amount of air flow 58 enters the turbine engine 10 through an associated inlet 60 of the nacelle 50 and / or fan section 14 in an air flow direction 58. As the amount of air passes through the fan blades 40, a first portion of air 62 as indicated by the arrows is directed or channeled into the bypass airflow passage 56 and a second portion of air 64 as indicated by the arrows is directed or channeled into the core air flowpath 37, or more specifically, into the LPC 22. The ratio between the first portion of air 62 as indicated by the arrows and the second portion of air 64 as indicated by the arrows is generally referred to as a bypass ratio. The pressure of the second portion of air 64 as indicated by the arrows is then increased as it is channeled through the HPC 24 and into the combustion section 26, where it is mixed with fuel and combusted to provide combustion gases 66.

[0034] Combustion gases 66 are directed through the HPT 28, a first portion of thermal and / or kinetic energy from the combustion gases 66 being extracted at the HPT 28 via successive stages of HPT stator vanes 68 coupled to the outer casing 18 and HPT rotor blades 70 coupled to the HPS 34, thereby causing the HPS 34 to rotate, supporting operation of the HPC 24. The combustion gases 66 are then directed through the LPT 30, a second portion of thermal and kinetic energy being extracted from the combustion gases 66 at the LPT 30 via successive stages of LPT stator vanes 72 coupled to the outer casing 18 and LPT rotor blades 74 coupled to the LPS 36, thereby causing the LPS 36 to rotate, supporting operation of the LPC 22 and / or rotation of the fan 38.

[0035] Subsequently, the combustion gases 66 are directed through the ejection exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. At the same time, the pressure of the first portion of air 62 is substantially 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, the LPT 30, and the ejection 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.

[0036] However, Figure 1 The turbine engine 10 depicted is merely an example. In other example embodiments, the turbine engine 10 can have any other suitable configuration. In still other example embodiments, aspects of the present disclosure can be incorporated into any other suitable gas turbine engine. For example, in other example embodiments, aspects of the present disclosure can be incorporated into, for example, a turboshaft engine, a turboprop engine, a turbocore engine, a turbojet engine, etc.

[0037] Figure 2 is in accordance with an embodiment of the present disclosure Figure 1A schematic 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 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, inner liner 84, and dome 86 together define a combustion chamber 88. 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 airflow from the compressor section and supplies compressed airflow to the combustor 80. In an embodiment, the diffuser 90 supplies compressed airflow to a single circumferentially spaced fuel / air mixer 92. In one embodiment, the dome 86 of the burner 80 is configured as a single annular dome, and a circumferentially arranged fuel / air mixer 92 is disposed within an opening formed in the dome 86 (air supply dome or burner dome). However, in other embodiments, multiple annular domes may also be used. Other types of burners may also be used.

[0038] In an embodiment, diffuser 90 can be used to slow down high-speed, highly compressed air from a compressor (not shown) to a speed optimal for combustor 80. Furthermore, diffuser 90 can also be configured to limit flow deformation as much as possible by avoiding flow effects such as boundary layer separation. Similar to most other gas turbine engine components, diffuser 90 is generally designed to be as lightweight as possible to reduce the overall engine weight.

[0039] Fuel nozzles (not shown) supply fuel to the fuel / air mixer 92 based on the desired performance of the burner 80 under various engine operating conditions. Figure 2 In the illustrated embodiment, the outer shroud 94 (e.g., annular shroud) and the inner shroud 96 (e.g., annular shroud) are located upstream of the combustion chamber 88 to direct airflow into the fuel / air mixer 92. The outer shroud 94 and the inner shroud 96 may also direct a portion of the airflow 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. Additionally, the inner support cone 106 is further shown 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.

[0040] The combustor 80 also has an igniter 114. The igniter 114 is disposed to ignite a fuel / air mixture supplied to the combustion chamber 88 of the combustor 80. The igniter 114 is attached to the outer shell 100 of the combustor 80 in a substantially fixed manner. In addition, the igniter 114 extends generally along the axial direction A2, defining a distal end 116 positioned proximate to an opening in the combustor member to the combustion chamber 88. The distal end 116 is positioned proximate to an opening 118 in the outer liner 82 of the combustor 80 to the combustion chamber 88.

[0041] In embodiments, the dome 86 of the combustor 80, together with the outer liner 82, the inner liner 84, and the fuel / air mixer 92, forms the combustion chamber and defines the swirling flow 130. As air enters the combustion chamber 88, the air flows through the fuel / air mixer 92. The dome 86 and the fuel / air mixer 92 function to generate turbulence in the air stream to rapidly mix the air with the fuel, resulting in a fuel-air mixture. The swirler (also referred to as a mixer) creates a localized low pressure area that forces some of the combustion products to recirculate, as shown, creating the high turbulence required. Figure 2

[0042] Figure 3 is a schematic perspective view of a section of the combustor 80 according to embodiments of the present disclosure. The combustor 80 is shown as having a cylindrical configuration. The combustor 80 includes a skeletal lattice 300 (also referred to as a truss or a trellis) on which the inner liner 84 and the outer liner 82 are mounted. The skeletal lattice 300 functions as a support structure for the inner liner 84 and the outer liner 82 as a whole. In embodiments, the skeletal lattice 300 is made of metal. The skeletal lattice 300, together with the inner liner 84 and the outer liner 82, defines the combustion chamber 88. The inner liner 84 and the outer liner 82 include a plurality of panels 302. The plurality of panels 302 includes a plurality of inner panels 302A, and, optionally, a plurality of outer panels 302B. The plurality of inner panels 302A are mounted to and cover the inner side of the skeletal lattice 300, and the outer panels 302B are mounted to and cover the outer side of the skeletal lattice 300. The plurality of inner panels 302A are exposed to the hot flame within the combustion chamber 88. In embodiments, the plurality of inner panels 302A are made of ceramic, or of metal coated with a ceramic coating or a thermal barrier coating (TBC) to enhance resistance to relatively high temperatures. In embodiments, the plurality of inner panels 302A can be made of a ceramic material, a ceramic matrix composite (CMC) material, or metal coated with a CMC or a TBC. In embodiments, the outer panels 302B can be made of metal or a ceramic matrix composite (CMC). In embodiments, the outer panels 302B are thinner than the plurality of inner panels 302A.

[0043] ​The skeletal mesh 300, along with the plurality of inner panels 302A and the plurality of outer panels 302B, can improve durability due to a reduction or elimination of hoop stress, while providing a lightweight lining configuration for the combustor 80. For example, the present configuration provides at least a twenty percent weight reduction compared to conventional combustors. Moreover, the present configuration provides additional benefits of being modular or segmented, and thus, relatively easy to repair or maintain. In fact, if one or more of the plurality of inner panels 302A or the plurality of outer panels 302B are damaged, only the damaged one or more panels are replaced, rather than the entire inner liner 84 or the entire outer liner 82. Moreover, the present configuration lends itself to being relatively easy to inspect and repair. All of these benefits result in overall cost savings.

[0044] Figure 4 is a schematic perspective view of a section of the inner liner 84 and the outer liner 82 of the combustor 80 according to embodiments of the present disclosure. As shown, a plurality of panels 302, including the plurality of inner panels 302A and the plurality of outer panels 302B, are mounted to the skeletal mesh 300. The plurality of inner panels 302A include a plurality of holes 302C. The plurality of outer panels 302B include a plurality of holes 302D. As shown, the plurality of inner panels 302A are mounted on one side of the skeletal mesh 300. The plurality of holes 302C are distributed along the surface of the plurality of inner panels 302A. The plurality of holes 302D are distributed along the surface of the plurality of outer panels 302B. Figure 4 Figure 4

[0045] In the skeletal mesh 300, a plurality of dilution holes 400 are provided, which are configured to allow air to pass therethrough into the combustion chamber 88 for further mixing with the fuel-air mixture. The skeletal mesh 300 includes one or more crossbeams 300A, a plurality of longitudinal rods 300B, and a plurality of transverse rods 300C. The plurality of transverse rods 300C and the one or more crossbeams 300A are substantially perpendicular to the plurality of longitudinal rods 300B. The plurality of inner panels 302A and the plurality of outer panels 302B are operably coupled or mounted to the plurality of longitudinal rods 300B and the plurality of transverse rods 300C. The plurality of dilution holes 400 can be provided on the one or more crossbeams 300A of the skeletal mesh 300. The one or more crossbeams 300A having the plurality of dilution holes 400 are generally referred to as dilution hole structures. Additionally, air impinging on the plurality of inner panels 302A can further pass through the plurality of holes 302C in the plurality of inner panels 302A for further cooling of the plurality of inner panels 302A. In this exemplary illustration, the plurality of dilution holes 400 are within the skeletal mesh itself.

[0046] Figure 5A is a schematic top view of the one or more crossbeams 300A of the skeletal mesh 300 according to embodiments of the present disclosure, showing the plurality of dilution holes 400. Figure 5B ​​is a schematic perspective view of one or more beams 300A of the skeletal mesh 300 according to another embodiment of the disclosure, showing a plurality of dilution holes 400 and a plurality of cooling holes 401. Although the dilution holes 400 and the cooling holes 401 are shown as cylindrical and having a circular cross-section, the dilution holes 400 and the cooling holes 401 can also have an elliptical cross-section or a polygonal cross-section (e.g., rectangular, hexagonal, etc.). The total area Al of the plurality of beams 300A in the burner 80 is π x Dl x L, where L is the length of the beams 300A and Dl is the diameter of the inner liner 84 of the burner 80 at the dilution hole location (shown in Figure 2 and Figure 3 ). The total area A2 of the plurality of beams 300A in the burner 80 is π x D2 x L, where L is the length of the beams 300A and D2 is the diameter of the outer liner 82 of the burner 80 at the dilution hole location (shown in Figure 2 and Figure 3 ). When the inner liner 84 is close to the outer liner 82 and both are located at a distance from the central axis of the burner 80 that is greater than the distance separating the inner liner 84 and the outer liner 82, the diameter Dl of the inner liner 84 is substantially equal to the diameter D2 of the outer liner 82. The total dilution area of all the dilution holes 400 is equal to N x π x d 2 / 4, where N is the number of dilution holes and d is the diameter of the dilution holes 400. The area A3 is equal to the sum of the total dilution area (total area of the dilution holes 400 equal to N x π x d 2 / 4) and the total area of the cooling holes 401. The ratio of the area A3 to the area Al ranges between 0.1 and 0.95. Similarly, the ratio of the area A3 to the area A2 ranges between 0.1 and 0.95 (the area Al is substantially equal to the area A2).

[0047] Figure 6 is a schematic perspective view of a section of the inner liner 84 and the outer liner 82 of the burner 80 according to another embodiment of the disclosure. As Figure 6 shown, a plurality of plates 302 comprising a plurality of inner plates 302A and a plurality of outer plates 302B are mounted to the skeletal mesh 300. The plurality of inner plates 302A comprise a plurality of holes 302C. The plurality of outer plates 302B comprise a plurality of holes 302D. As Figure 6As shown, multiple inner plates 302A are mounted on one side of the skeleton mesh structure 300. Multiple holes 302C are distributed along the surfaces of the multiple inner plates 302A. Multiple holes 302D are distributed along the surfaces of the multiple outer plates 302B. The skeleton mesh structure 300 has multiple longitudinal rods 300B and multiple transverse rods 300C. The multiple transverse rods 300C are substantially perpendicular to the multiple longitudinal rods 300B. Additionally, the burner 80 includes one or more dilution orifice plates 600 mounted to the skeleton mesh structure 300. One or more dilution orifice plates 600 are mounted on the longitudinal rods 300B and the multiple transverse rods 300C of the skeleton mesh structure 300. In this exemplary illustration, multiple dilution holes 602 are within the dilution orifice plates 600, which are then mounted or otherwise coupled to the skeleton mesh structure 300. Various mounting configurations can be used to mount the dilution orifice plates 600 on the longitudinal rods 300B and the multiple transverse rods 300C of the skeleton mesh structure 300. These various structures will be described in detail in the following paragraphs.

[0048] One or more dilution orifice plates 600 include a plurality of dilution orifices 602, the plurality of dilution orifices 602 being configured to allow air to pass through them and enter combustion chamber 88. Figure 3 As shown in the diagram, it is used for further mixing with the fuel-air mixture. One or more dilution orifice plates 600 having a plurality of dilution orifices 602 are generally referred to as dilution orifice structures. Additionally, in embodiments, one or more dilution orifice plates 600 may also have... Figure 5B The cooling hole 401 shown is similar to multiple cooling holes ( Figure 6 (Not shown in the image).

[0049] Figure 7 This is a perspective view of one or more dilution perforated plates 600 mounted to a skeleton mesh structure 300 according to an embodiment of the present disclosure, showing a plurality of dilution holes 602 and peripheral cooling grooves 604. Figure 7 As shown, in addition to the dilution hole 602, an outer peripheral cooling groove 604 may also be provided in one or more dilution hole plates 600. The outer peripheral cooling groove 604 is provided at the outer periphery of one or more dilution hole plates 600, at the interface between one or more dilution hole plates 600 and one of the transverse rods 300C and / or one of the longitudinal rods 300B. Although in Figure 7 Two dilution holes 602 are depicted, but any number of dilution holes can be provided. A peripheral cooling groove 604 can be used to cool one or more dilution hole plates 600. Therefore, these peripheral cooling grooves 604 are often referred to as cooling peripheral cooling grooves.

[0050] Figure 8A and 8B This is a cross-sectional view of one or more dilution perforated plates 600 mounted to a skeleton mesh structure 300 according to various embodiments of the present disclosure.Figure 8A As shown, for example, one or more dilution orifice plates 600 are coupled to a plurality of longitudinal rods 300B of the skeleton mesh structure 300. In an embodiment, one or more dilution orifice plates 600 may be provided with a plurality of coupling grooves 600C, and the plurality of longitudinal rods 300B of the skeleton mesh structure 300 may be inserted into the plurality of coupling grooves 600C. Figure 8B As shown, for example, one or more dilution orifice plates 600 are coupled to a plurality of longitudinal bars 300B of the skeleton mesh structure 300. However, alternatively or additionally, one or more dilution orifice plates 600 may also be coupled or mounted to a plurality of transverse bars 300C of the skeleton mesh structure 300. In embodiments, as Figure 8B As shown, multiple inner plates 302A can be mounted to multiple longitudinal rods 300B of the skeleton mesh structure 300, and vice versa. One or more dilution orifice plates 600 can be mounted to multiple longitudinal rods 300B of the skeleton mesh structure 300. One or more dilution orifice plates 600 may have one or more dilution holes 602. One or more dilution orifice plates 600 can be mounted to the skeleton mesh structure 300 using various types of connection methods, including but not limited to bolts, pins, clips, brazing, additives, pistons, W seals, etc. In an embodiment, the dilution orifice plates 600 can be coupled to multiple longitudinal rods 300B and / or coupled to transverse rods 300C using any of the various connection methods, including but not limited to bolts, pins, clips, brazing, welding, additives, spring clips, pistons, W seals, etc. In an embodiment, the dilution orifice plates 600 can slide in a circumferential coupling groove, wherein the coupling groove can be arranged around the outer periphery of the dilution orifice plates 600 in the form of a bracket (e.g., a C-shaped bracket).

[0051] Figures 9A to 9E This is a cross-sectional view of one or more dilution orifice plates 600 mounted to a skeleton mesh structure 300 according to various embodiments of the present disclosure, showing various configurations of one or more dilution orifices 602. Figure 9A One or more dilution orifices 602 with a backward tilt are shown. Figure 9B One or more dilution orifices 602 are shown tilted forward. Figure 9C Multiple dilution orifices 602, tilted forward and backward, are shown. Figure 9D One or more dilution holes 602 are shown, which are vertically expanding. Figure 9E One or more dilution orifices 602 are shown, which are vertical and tapered. Any of the above configurations can be used in combination with any of the other above configurations.

[0052] Figures 10A to Figure 10E Various embodiments according to this disclosure are shown. Figure 3 , 4various geometrical configurations of the structural elements of the skeletal reticulated structure 300 shown in Figures 6. The skeletal reticulated structure 300 can comprise a plurality of structural elements 306 connected together to form the skeletal reticulated structure 300. As Figures 10A to 10E shown, each of the plurality of structural elements 306 can have any desired geometrical shape, including any polygonal shape, such as a square shape or a rectangular shape, a diamond shape, a triangular shape, a pentagonal shape, a hexagonal shape, or a more complex shape, etc. Each structural element 306 can have a plurality of sides defining a hollow face.

[0053] Figures 11A to 11E various geometrical configurations of the plates in the plurality of inner plates 302A and the plurality of outer plates 302B are shown in accordance with various embodiments of the present disclosure. As Figures 9A to Figure 9E shown, each of the plurality of inner plates 302A and the plurality of outer plates 302B can also have a geometrical shape matching the corresponding shape of each of the plurality of structural elements 306 shown in Figure Figures 10A to 10E The plurality of inner plates 302A and the plurality of outer plates 302B can be installed to the plurality of structural elements 306 of the skeletal reticulated structure 300 using various fastening techniques, similar to covering truss structures of, for example, bridges, buildings, aircraft fuselages, rocket structures, etc. Figures 11A to 11E The plurality of inner plates 302A and the plurality of outer plates 302B can be installed to the plurality of structural elements 306 of the skeletal reticulated structure 300 using various fastening techniques, similar to covering truss structures of, for example, bridges, buildings, aircraft fuselages, rocket structures, etc. Figures 10A to 10E

[0054] Figure 12A and 12B is a schematic cross-sectional view of a combustor 80 according to embodiments of the present disclosure using the skeletal reticulated structure 300 along with the plurality of inner plates 302A. In Figure 12A the inner liner 84 and the outer liner 82 of the combustor 80 are made of a front section and a back section of the respective liner. The front section can be of the hanger type with the plurality of inner plates 302A and the plurality of outer plates 302B (hollow plates), and the back section can be from the prior art of solid liners with an annular gap between the two sections. Figure 12B is shown where the inner liner 84 and the outer liner 82 are both made of a hanger and hollow plate arrangement.

[0055] ​As can be appreciated from the foregoing discussion, a combustor includes a skeletal structure. The combustor also includes at least one liner operably coupled to the skeletal structure to at least partially define a combustion chamber, and a plurality of first panels mounted to a first side of the at least one liner and a plurality of second panels mounted to a second side of the at least one liner. The combustor further includes at least one dilution hole structure disposed with a portion of the skeletal structure and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.

[0056] The combustor according to any of the preceding clauses, the dilution hole structure including a crossbeam of the skeletal mesh structure, the crossbeam having the plurality of dilution holes.

[0057] The combustor according to any of the preceding clauses, the skeletal mesh structure including a plurality of longitudinal struts and a plurality of transverse struts, and the plurality of first panels and the plurality of second panels being mounted to the plurality of longitudinal struts and the plurality of transverse struts.

[0058] The combustor according to any of the preceding clauses, the dilution hole structure including one or more dilution hole panels having the plurality of dilution holes and a plurality of cooling holes.

[0059] The combustor according to any of the preceding clauses, the one or more dilution hole panels being mounted to the skeletal mesh structure.

[0060] The combustor according to any of the preceding clauses, the skeletal mesh structure including a plurality of longitudinal struts and a plurality of transverse struts, and the one or more dilution hole panels being mounted to the plurality of longitudinal struts and the plurality of transverse struts.

[0061] The combustor according to any of the preceding clauses, the one or more dilution hole panels including a plurality of keyed grooves, and the plurality of longitudinal struts, or the plurality of transverse struts, or both, being inserted into the plurality of keyed grooves of the one or more dilution panels.

[0062] The combustor according to any of the preceding clauses, the one or more dilution hole panels being mounted to the plurality of longitudinal struts, or the plurality of transverse struts, or both.

[0063] The combustor according to any of the preceding clauses, the one or more dilution hole panels further including a plurality of peripheral cooling slots disposed at a periphery of the one or more dilution hole panels, at an interface between the one or more dilution hole panels and the skeletal mesh structure.

[0064] The combustor of any of the preceding clauses, the plurality of dilution holes are vertical, rearwardly inclined, or forwardly inclined, or any combination thereof.

[0065] The combustor of any of the preceding clauses, the plurality of dilution holes are converging holes, or diverging holes, or both.

[0066] The combustor of any of the preceding clauses, the plurality of first and second plates include a plurality of holes to pass air therethrough to cool the plurality of first plates.

[0067] The combustor of any of the preceding clauses, the plurality of structural elements have a hollow polygonal shape with a plurality of sides defining a hollow face.

[0068] The combustor of any of the preceding clauses, the plurality of first plates, or the plurality of second plates, or both, have a filled polygonal shape matching the hollow polygonal shape of the plurality of structural elements.

[0069] Another aspect of the present disclosure provides a turbine engine comprising a combustor. The combustor includes a skeletal structure. The combustor further includes at least one liner operably coupled to the skeletal structure to at least partially define a combustion chamber, and a plurality of first plates mounted to a first side of the at least one liner and a plurality of second plates mounted to a second side of the at least one liner. The combustor further includes at least one dilution hole structure disposed with a portion of the skeletal structure and including at least one dilution hole configured to allow a fluid to pass therethrough into the combustion chamber.

[0070] The turbine engine of the preceding clause, the dilution hole structure includes a crossbeam of the skeletal lattice structure having the plurality of dilution holes.

[0071] The turbine engine of any of the preceding clauses, the skeletal lattice structure includes a plurality of longitudinal struts and a plurality of transverse struts, and the plurality of first and second plates are mounted to the plurality of longitudinal struts and the plurality of transverse struts.

[0072] The turbine engine of any of the preceding clauses, the dilution hole structure includes one or more dilution plates having the plurality of dilution holes and a plurality of cooling holes.

[0073] The turbine engine of any of the preceding clauses, the one or more dilution plates further include a plurality of peripheral cooling slots disposed at a periphery of the one or more dilution hole plates at an interface between the one or more dilution hole plates and the skeletal lattice structure.

[0074] The turbine engine of any of the preceding paragraphs, the one or more dilution plates mounted to the skeletal network.

[0075] While the foregoing description has been directed to the preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art from this disclosure, which are intended to fall within the scope of the present disclosure. Further, features described in conjunction with one embodiment can be used with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that, include: Skeletal mesh structure; At least one liner, said at least one liner being operatively coupled to said skeleton mesh structure to at least partially define a combustion chamber, and including a plurality of first plates mounted to a first side of said at least one liner and a plurality of second plates mounted to a second side of said at least one liner; and At least one dilution pore structure is configured as part of the skeleton mesh structure, the at least one dilution pore structure is adjacent to at least one of the plurality of first plates and at least one of the plurality of second plates, and includes at least one dilution pore configured to allow fluid to pass through it and enter the combustion chamber. Wherein, the radial thickness of the at least one dilution hole structure is greater than the radial thickness of the remaining portion of the skeleton mesh structure, the radial thickness of the at least one of the plurality of first plates, and the radial thickness of the at least one of the plurality of second plates.

2. The burner according to claim 1, characterized in that, The dilution hole structure includes a crossbeam of the skeleton mesh structure, the crossbeam having the plurality of dilution holes.

3. The burner according to claim 1, characterized in that, The skeleton mesh structure includes multiple longitudinal bars and multiple transverse bars, and the multiple first plates and the multiple second plates are mounted to the multiple longitudinal bars and the multiple transverse bars.

4. The burner according to claim 1, characterized in that, The plurality of dilution orifices are vertical, backward-sloping, or forward-sloping, or any combination thereof.

5. The burner according to claim 1, characterized in that, The plurality of dilution orifices are either tapering or expanding orifices, or both.

6. The burner according to claim 1, characterized in that, The plurality of first plates and the plurality of second plates include a plurality of cooling holes to allow air to pass through them, thereby cooling the plurality of first plates.

7. The burner according to claim 1, characterized in that, The dilution hole structure includes one or more dilution hole plates having the plurality of dilution holes and the plurality of cooling holes.

8. The burner according to claim 7, characterized in that, The one or more dilution orifice plates further include a plurality of peripheral cooling grooves disposed on the periphery of the one or more dilution orifice plates and at the interface between the one or more dilution orifice plates and the skeleton mesh structure.

9. The burner according to claim 7, characterized in that, The one or more dilution perforated plates are connected to the skeleton mesh structure.

10. The burner according to claim 9, characterized in that, The skeleton mesh structure includes a plurality of longitudinal rods and a plurality of transverse rods, and the one or more dilution orifice plates are mounted to the plurality of longitudinal rods and the plurality of transverse rods.

11. The burner according to claim 10, characterized in that, The one or more dilution plates include a plurality of coupling grooves, and the plurality of longitudinal rods, or the plurality of transverse rods, or both, are inserted into the plurality of coupling grooves of the one or more dilution plates.

12. The burner according to claim 10, characterized in that, The one or more dilution orifice plates are mounted to the plurality of longitudinal rods, or the plurality of transverse rods, or both.

13. The burner according to claim 1, characterized in that, The plurality of structural elements have a hollow polygonal shape, and the hollow polygonal shape has multiple sides defining a hollow surface.

14. The burner according to claim 13, characterized in that, The plurality of first plates, or the plurality of second plates, or both, have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

15. A turbine engine, characterized in that, include: A burner, the burner comprising: (a) Skeletal network structure; (b) At least one liner, said at least one liner operatively coupled to said skeletal mesh structure to at least partially define a combustion chamber, and comprising a plurality of first plates mounted to a first side of said at least one liner and a plurality of second plates mounted to a second side of said at least one liner; and (c) At least one dilution pore structure, said at least one dilution pore structure being configured as part of the skeleton mesh structure, the at least one dilution pore structure being adjacent to at least one of the plurality of first plates and at least one of the plurality of second plates, and including at least one dilution pore configured to allow fluid to pass through it and enter the combustion chamber. Wherein, the radial thickness of the at least one dilution hole structure is greater than the radial thickness of the remaining portion of the skeleton mesh structure, the radial thickness of the at least one of the plurality of first plates, and the radial thickness of the at least one of the plurality of second plates.

16. The turbine engine according to claim 15, characterized in that, The dilution hole structure includes a crossbeam of the skeleton mesh structure, the crossbeam having the plurality of dilution holes.

17. The turbine engine according to claim 15, characterized in that, The skeleton mesh structure includes multiple longitudinal bars and multiple transverse bars, and the multiple first plates and the multiple second plates are mounted to the multiple longitudinal bars and the multiple transverse bars.

18. The turbine engine according to claim 15, characterized in that, The dilution hole structure includes one or more dilution hole plates having the plurality of dilution holes and the plurality of cooling holes.

19. The turbine engine according to claim 18, characterized in that, The one or more dilution plates further include a plurality of peripheral cooling grooves disposed on the periphery of the one or more dilution perforated plates at the interface between the one or more dilution perforated plates and the skeleton mesh structure.

20. The turbine engine according to claim 18, characterized in that, The one or more dilution perforated plates are mounted to the skeleton mesh structure.

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