Plate hanger structure for a durable combustion chamber liner

Abstract

A burner includes a skeleton mesh structure having a plurality of structural elements configured to mate together to form the skeleton mesh structure. The burner also includes an inner liner and an outer liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner panels mounted to an inner side of the inner liner and a plurality of outer panels mounted to an outer side of the inner liner. The outer liner includes a plurality of inner panels mounted to an inner side of the outer liner and a plurality of outer panels mounted to an outer side of the outer liner.

Description

Technical Field

[0001] This disclosure generally relates to burner liners, and more specifically, to burner liners having a plate and hanger structure. Background Technology

[0002] A gas turbine engine generally comprises a fan and a core arranged in flow communication with each other, wherein the core is positioned downstream of the fan in the flow direction through the gas turbine engine. The core of the gas turbine engine generally comprises, in a serial flow sequence, a compressor section, a combustion section, a turbine section, and an exhaust section. For a multi-shaft gas turbine engine, the compressor section may include a high-pressure compressor (HPC) positioned downstream of a low-pressure compressor (LPC), and the turbine section may similarly include a low-pressure turbine (LPT) positioned downstream of a high-pressure turbine (HPT). With this configuration, the HPC is connected to the HPT via a high-pressure shaft (HPS), and the LPC is connected to the LPT via a low-pressure shaft (LPS). In operation, at least a portion of the air on the fan is supplied to the inlet of the core. This portion of air is progressively compressed by the LPC, then by the HPC, until the compressed air reaches the combustion section. Fuel mixes with the compressed air and burns 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 combustion gases flow through the turbine section drive the HPT and LPT, which in turn drive a corresponding one of the HPC and LPC via the HPS and LPS, respectively. The combustion gases are then directed through the exhaust section, for example, to the atmosphere. The LPT drives the LPS, and the LPS drives the LPC. In addition to driving the LPC, the LPS can also drive the fan via the power gearbox, allowing the fan to rotate at fewer revolutions per unit time than the LPS, for greater efficiency.

[0003] Fuel, mixed with compressed air and burned in the combustion zone, is delivered through fuel nozzles. Attached Figure Description

[0004] The foregoing and other features and advantages will become more apparent from the following description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally indicate the same, functionally similar and / or structurally similar elements.

[0005] Figure 1 This is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure.

[0006] Figure 2 This is a schematic cross-sectional view of a burner according to an embodiment of the present disclosure.

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

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

[0009] Figure 5 This is a schematic perspective view showing the interconnection details between a plurality of plates and a skeleton mesh structure in a burner according to an embodiment of the present disclosure.

[0010] Figures 6A to 6E The following illustrations show embodiments according to the present disclosure. Figure 3 , 4 Various geometric configurations of the structural elements of the skeleton mesh structure shown in Figure 5.

[0011] Figures 7A to 7E Various geometries of plates in a plurality of inner plates and a plurality of outer plates according to embodiments of the present disclosure are shown.

[0012] Figure 8A This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates and a plurality of outer plates and a skeleton mesh structure according to embodiments of the present disclosure.

[0013] Figure 8B This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates and a plurality of outer plates and a skeleton mesh structure according to another embodiment of the present disclosure.

[0014] Figure 8C This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates and a plurality of outer plates and a skeleton mesh structure 300 according to yet another embodiment of the present disclosure. Detailed Implementation

[0015] Additional features, advantages, and embodiments of this disclosure are set forth or become apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that both the foregoing overview and the following detailed description are exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0016] Various embodiments of this disclosure are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0017] In the following description and claims, numerous “optional” or “optionally” elements may be referenced, meaning that the event or situation described below may or may not occur, and the description includes instances where the event occurs as well as instances where the event does not occur.

[0018] The approximate language used herein throughout the specification and claims can be applied to modify any quantitative expression that may be varied without causing a change in its essential function. Therefore, values ​​modified by one or more terms such as “approximately,” “about,” and “substantially” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Scope limitations may be combined and / or interchanged herein and throughout the specification and claims. Unless the context or language otherwise indicates, these scopes are identified and include all subscopes contained herein.

[0019] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine or combustor. Furthermore, 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.

[0020] As will be described in further detail in the following paragraphs, the burner exhibits improved lining durability under harsh thermal and stress environments. The burner includes a skeletal mesh structure (also referred to as a hanger or truss) on which an inner and outer lining are mounted. The skeletal mesh structure serves as the overall support structure for the inner and outer linings. In embodiments, the skeletal mesh structure may be made of metal. The skeletal mesh structure, together with the inner and outer linings, defines the combustion chamber. The inner and outer linings include multiple plates, each comprising multiple inner plates and multiple outer plates. The inner plates cover the inner side of the skeletal mesh structure, and the outer plates cover the outer side of the skeletal mesh structure. In embodiments, the inner plates may be made of ceramic materials, ceramic matrix composite (CMC) materials, or metals coated with CMC or thermal barrier coating (TBC). The skeletal mesh structure, together with the inner and outer plates, can improve durability due to the reduction or elimination of circumferential stress, while providing a lightweight lining construction for the burner. Furthermore, this lining construction provides the added benefit of modularity or segmentation, thus facilitating relatively easy maintenance.

[0021] Figure 1 This is a schematic cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure. More specifically, for Figure 1 In the embodiment shown, the turbine engine 10 is a high-bypass turbine engine 10. As... Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to a reference longitudinal centerline 12) and a radial direction R, the radial direction R being 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 the airflow direction 58.

[0022] The depicted core turbine engine 16 generally includes a casing 18, which is essentially tubular and defines an annular inlet 20. The casing 18 encloses, in a series flow relationship, a compressor section including a turbocharger 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 shaft (HPS) 34 drives the HPT 28 to the HPC 24. A low-pressure shaft (LPS) 36 drives the LPT 30 to the LPC 22. The compressor section, combustion section 26, turbine section, and exhaust nozzle section 32 together define a core airflow path 37.

[0023] for Figure 1 In the embodiment depicted, fan section 14 includes a fan 38 with a variable pitch, the fan 38 having a plurality of spaced-apart fan blades 40 coupled to a disk 42. As depicted, the fan blades 40 extend generally outward from the disk 42 along a radial direction R. Since the fan blades 40 are operatively coupled to suitable actuating members 44, which are configured to uniformly and collectively change the pitch of the fan blades 40, each fan blade 40 is capable of rotating relative to the disk 42 about a pitch axis P. The fan blades 40, disk 42, and actuating members 44 are capable of rotating together about a longitudinal centerline 12 (longitudinal axis) via a power gearbox 46 through a LPS 36. The power gearbox 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 fan speed.

[0024] The disc 42 is covered by a rotatable front hub 48, which has an aerodynamic profile to facilitate airflow through multiple fan blades 40. Additionally, the fan section 14 includes an annular fan housing or nacelle 50 that circumferentially surrounds at least a portion of the fan 38 and / or the core turbine engine 16. The nacelle 50 may be configured to be supported relative to the core turbine engine 16 by multiple circumferentially spaced outlet guide vanes 52. Furthermore, a downstream section 54 of the nacelle 50 may extend over the outer portion of the core turbine engine 16 to define a bypass airflow passage 56 therebetween.

[0025] During operation of the turbine engine 10, a certain amount of airflow 58 enters the turbine engine 10 in the airflow direction 58 through the associated inlet 60 of the nacelle 50 and / or fan section 14. As the certain amount of air passes through the fan blades 40, a first portion of the air, as indicated by arrow 62, is directed or directed into the bypass airflow passage 56, and a second portion of the air, as indicated by arrow 64, is directed or directed into the core airflow path 37, or more specifically, into the 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 commonly referred to as the bypass ratio. The pressure of the second portion of air, as indicated by arrow 64, then increases as the air is directed through the HPC 24 and into the combustion section 26, where it mixes with fuel and burns to provide combustion gases 66.

[0026] Combustion gas 66 is directed through HPT 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted at HPT 28 via a continuous stage of HPT stator blades 68 connected to housing 18 and HPT rotor blades 70 connected to HPS 34, thereby causing HPS 34 to rotate and thus supporting the operation of HPC 24. Combustion gas 66 is then directed through LPT 30, where a second portion of the thermal and kinetic energy is extracted at LPT 30 via a continuous stage of LPT stator blades 72 connected to housing 18 and LPT rotor blades 74 connected to LPS 36, thereby causing LPS 36 to rotate and thus supporting the operation of LPC 22 and / or the rotation of fan 38.

[0027] Subsequently, combustion gases 66 are directed through the injection exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it is directed through the bypass airflow passage 56 before being exhausted from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. HPT 28, LPT 30, and the injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gases 66 through the core turbine engine 16.

[0028] As an example only Figure 1 The present invention depicts a turbine engine 10, and in other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. In other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may be incorporated into, for example, turboshaft engines, turboprop engines, turbine core engines, turbojet engines, etc.

[0029] Figure 2 According to embodiments of this disclosure Figure 1 A 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.

[0030] 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 the combustor. Furthermore, diffuser 90 can 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.

[0031] 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 configuration.

[0032] The burner 80 is also provided with an igniter 114. The igniter 114 is configured to ignite the fuel / air mixture supplied to the combustion chamber 88 of the burner 80. The igniter 114 is attached to the housing 100 of the burner 80 in a substantially fixed manner. Furthermore, the igniter 114 extends generally along the axial direction A2, defining a distal end 116 positioned close to an opening in the burner assembly of the combustion chamber 88. The distal end 116 is positioned close to the opening 118 of the combustion chamber 88 within the outer liner 82 of the burner 80.

[0033] In this embodiment, the dome 86 of the burner 80, together with the outer liner 82, the inner liner 84, and the fuel / air mixer 92, forms a combustion chamber 88 and defines a swirling flow 130. When air enters the combustion chamber 88, it flows through the fuel / air mixer assembly 92. The dome 86 and the fuel / air mixer assembly 92 function to generate turbulence in the airflow to rapidly mix the air with the fuel. The swirler (also called a mixer) creates a localized low-pressure zone that forces some combustion products to recirculate, such as... Figure 2 As shown, this generates the desired high turbulence.

[0034] Figure 3 This is a schematic perspective view of a section of a burner 80 according to an embodiment of the present disclosure. The burner 80 is shown as having a cylindrical configuration. The burner 80 includes a skeleton mesh structure 300 (also referred to as a hanger or truss) on which an inner liner 84 and an outer liner 82 are mounted. The skeleton mesh structure 300 serves as a support structure for the inner liner 84 and the outer liner 82. In an embodiment, the skeleton mesh structure 300 is made of metal. The skeleton mesh structure 300, together with the inner liner 84 and the outer liner 82, defines a combustion chamber 88. The inner liner 84 and the outer liner 82 include a plurality of plates 302. The plurality of plates 302 include a plurality of inner plates 302A ( Figure 3 (Not shown in the diagram) and multiple outer panels 302B. Multiple inner panels 302A are mounted and cover the inner side of the skeleton mesh structure 300, and outer panels 302B are mounted and cover the outer side of the skeleton mesh structure 300. The multiple inner panels 302A are exposed to the hot flame within the combustion chamber 88. In an embodiment, the multiple 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 an embodiment, the multiple inner panels 302A may be made of ceramic material, ceramic matrix composite (CMC) material, or of metal coated with CMC or TBC. In an embodiment, the outer panels 302B may be made of metal or ceramic matrix composite (CMC) and are used to regulate or guide the cooling airflow between the multiple outer panels 302B and the multiple inner panels 302A to provide cooling to the multiple inner panels 302A through cooling airflow impact. In an embodiment, the outer panels 302B are thinner than the multiple inner panels 302A.

[0035] The skeletal mesh structure 300, together with multiple inner panels 302A and multiple outer panels 302B, can improve durability due to the reduction or elimination of circumferential stress, while providing a lightweight lining construction for the burner 80. For example, this construction provides at least a 20% weight reduction compared to conventional burners. Furthermore, this construction offers the added benefit of modularity or segmentation, thus facilitating maintenance. In practice, if one or more of the multiple inner panels 302A or multiple outer panels 302B are damaged, only the damaged one or more panels are replaced, rather than the entire inner lining 84 or the entire outer lining 82. Moreover, this construction itself makes it relatively easy to inspect and maintain. All these benefits result in overall cost savings.

[0036] Figure 4 This is a schematic perspective view of sections of the inner liner 84 and outer liner 82 of a burner 80 according to an embodiment of the present disclosure. Figure 4 As shown, multiple plates 302, including multiple inner plates 302A and multiple outer plates 302B, are mounted to the skeleton mesh structure 300. The multiple inner plates 302A and multiple outer plates 302B include multiple holes 302C. Figure 4 As shown, multiple inner panels 302A and multiple outer panels 302B are mounted on opposite sides of the skeleton mesh structure 300. Multiple holes 302C are distributed along the surfaces of the multiple inner panels 302A and multiple outer panels 302B to allow air to enter the combustion chamber 88 and / or allow air to pass through the gap G between the multiple inner panels 302A and multiple outer panels 302B. Figure 5 (As shown in the diagram) Inner loop.

[0037] Figure 5 This is a schematic perspective view showing the interconnection details between a plurality of plates 302 and a skeleton mesh structure 300 according to embodiments of the present disclosure. Figure 5 As shown, multiple inner plates 302A and multiple outer plates 302B are mounted on opposite sides of the skeleton mesh structure 300, and the inner plates 302A and multiple outer plates 302B are radially spaced apart from each other by gaps G. Furthermore, each pair of continuous plates of the inner plates 302A and multiple outer plates 302B is also laterally separated by a distance D. The skeleton mesh structure 300 includes a separator feature 304 to maintain the distance between each pair of continuous plates of the inner plates 302A and multiple outer plates 302B.

[0038] Figures 6A to 6E The following illustrations show embodiments according to the present disclosure. Figure 3 , 4 Various geometric configurations of the structural elements of the skeleton mesh structure 300 shown in Figure 5. The skeleton mesh structure 300 may include meshes that are matched together to form Figure 3 , 4 And the multiple structural elements 306 of the skeleton mesh structure 300 shown in Figure 5. Figures 6A to 6EAs shown, each of the multiple structural elements 306 can have any desired geometry, including any polygonal shape, such as a square or rectangular shape, a rhombus shape, a triangle shape, a pentagonal shape, a hexagonal shape, or a more complex shape. Each structural element 306 can have multiple sides defining a hollow surface.

[0039] Figures 7A to 7E Various geometries of the plates in a plurality of inner plates 302A and a plurality of outer plates 302B according to embodiments of the present disclosure are shown. In embodiments, such as Figures 7A to 7E As shown, each of the plurality of inner panels 302A and the plurality of outer panels 302B can also have the same as Figures 6A to 6E The corresponding shapes of each of the multiple structural elements 306 shown are matched geometric shapes. Each of the multiple inner plates 302A and multiple outer plates 302B is essentially a filled shape. The filled shape is provided with multiple holes 302C. The filled shape of each or more inner plates 302A and multiple outer plates 302B is ( Figures 7A to 7E (As shown) can be installed into the corresponding hollow shape of multiple structural elements 306 ( Figures 6A to 6E (As shown in the diagram). In an embodiment, the plurality of inner plates 302A and / or the plurality of outer plates 302B may have fine curvature to follow or conform to the curvature of the skeleton mesh structure 300.

[0040] Multiple inner panels 302A and multiple outer panels 302B can be installed to multiple structural elements 306 of the skeleton mesh structure 300 using various fastening techniques, similar to covering truss structures such as bridges, buildings, aircraft fuselages, rocket structures, etc.

[0041] Figure 8A This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates 302A and a plurality of outer plates 302B and the skeleton mesh structure 300 according to an embodiment of the present disclosure. Figure 8A As shown, multiple inner plates 302A are connected to multiple structural elements 306 of the skeleton mesh structure 300. Burner 80 ( Figure 2 and Figure 3 (As shown) further includes a plurality of radial spacers 308 positioned above a plurality of inner plates 302A and surrounding a plurality of structural elements 306. A plurality of outer plates 302B are disposed on the plurality of radial spacers 308. A plurality of connector clips 310 (e.g., clamps) are used to attach the plurality of outer plates 302B to the plurality of structural elements 306. Figure 8A As shown, the multiple outer panels 302B are thinner than the multiple inner panels 302A. In an embodiment, as... Figure 8A As shown, the multiple inner panels 302A and the multiple outer panels 302B have different thicknesses. For example, the multiple inner panels 302A are thicker than the multiple outer panels 302B.

[0042] Figure 8B This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates 302A and a plurality of outer plates 302B and the skeleton mesh structure 300 according to another embodiment of the present disclosure. Figure 8B As shown, multiple inner plates 302A are connected to multiple structural elements 306 of the skeleton mesh structure 300. Multiple links 314 are connected to the multiple inner plates 302A. Multiple outer plates 302B are connected to the multiple links 314 and the multiple structural elements 306 of the skeleton mesh structure 300. Multiple fasteners 318 are used to connect the multiple outer plates 302B to the multiple links 314. Multiple elastic elements 320 (e.g., springs) may be disposed between the multiple fasteners 318 and the multiple links 314 to push the multiple outer plates 302B against the multiple links 314. In an embodiment, as Figure 8B As shown, cooling air passages 307 are provided within each of the plurality of structural elements 306. For example, Figure 8A and 8B The configurations shown provide an interlocking system for multiple inner panels 302A (e.g., sliding plates) and multiple outer panels 302B (e.g., sliding plates). Additionally, these configurations provide the use of C-clamps to attach the multiple inner panels 302A and multiple outer panels 302B to multiple structural elements 306 of the skeleton mesh structure 300, instead of using bolts. A material layer 302M may be provided for coating the multiple inner panels 302A.

[0043] Figure 8C This is a schematic cross-sectional view showing the interconnection between a plurality of inner plates 302A and a plurality of outer plates 302B and the skeleton mesh structure 300 according to yet another embodiment of the present disclosure. Figure 8C As shown, multiple inner plates 302A are connected to multiple structural elements 306 of the skeleton mesh structure 300. Multiple outer plates 302B are connected to multiple inner plates 302A. Multiple fasteners 322 are used to connect the multiple inner plates 302A to the multiple structural elements 306. Multiple spacer elastic members 324 (e.g., springs) may be disposed between the multiple inner plates 302A and the multiple outer plates 302B. In an embodiment, as... Figure 8C As shown, a spacer 327 is disposed between two portions of a plurality of inner plates 302A for connecting the two portions using a plurality of fasteners 322.

[0044] The skeletal mesh structure, together with the inner and outer plates, can improve durability due to reduced or eliminated circumferential stress, while providing a lightweight lining for the burner. Furthermore, this lining construction offers the added benefit of modularity or segmentation, making it relatively easy to repair or replace.

[0045] As can be understood from the above discussion, a burner includes a skeletal mesh structure having a plurality of structural elements configured to fit together to form the skeletal mesh structure. The burner also includes an inner liner and an outer liner mounted to the skeletal mesh structure to define a combustion chamber. The inner liner includes a plurality of inner plates mounted to the inner side of the inner liner and a plurality of outer plates mounted to the outer side of the inner liner. The outer liner includes a plurality of inner plates mounted to the inner side of the outer liner and a plurality of outer plates mounted to the outer side of the outer liner.

[0046] The burner according to any one of the foregoing clauses, wherein the plurality of inner plates and the plurality of outer plates are radially spaced apart from each other by gaps.

[0047] In any of the preceding clauses, each pair of continuous plates in the plurality of inner plates and each pair of continuous plates in the plurality of outer plates are separated using a separator.

[0048] The burner according to any one of the foregoing clauses, wherein the plurality of structural elements have a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

[0049] The burner according to any one of the foregoing clauses, wherein the plurality of inner plates and the plurality of outer plates have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

[0050] The burner according to any one of the foregoing clauses further includes radial spacers disposed around the plurality of structural elements. The plurality of inner plates are connected to the plurality of structural elements. The radial spacers are disposed on the plurality of inner plates. The plurality of outer plates are disposed on the radial spacers. The plurality of outer plates are coupled to the plurality of structural elements using a plurality of clips.

[0051] The burner according to any one of the foregoing clauses further includes a plurality of connecting rods. The plurality of inner plates and the plurality of outer plates are connected to the plurality of structural elements. The plurality of connecting rods are connected to the plurality of inner plates. The plurality of outer plates are connected to the plurality of connecting rods using a plurality of fasteners.

[0052] The burner according to any one of the foregoing clauses, wherein each of the plurality of structural elements has a cooling air passage.

[0053] In the burner according to any one of the foregoing clauses, the plurality of inner plates are connected to the plurality of structural elements using a plurality of fasteners. The plurality of outer plates are coupled to the plurality of inner plates. The plurality of outer plates are spaced apart from the plurality of inner plates using a plurality of spacers.

[0054] According to any one of the foregoing clauses, the plurality of inner plates further include a ceramic coating deposited on the inner side of the plurality of inner plates.

[0055] The burner according to any one of the foregoing clauses, wherein the plurality of inner plates and the plurality of outer plates have different thicknesses.

[0056] According to any one of the foregoing clauses, the plurality of inner plates and the plurality of outer plates are bent to conform to the curvature of the skeleton mesh structure.

[0057] Another aspect of this disclosure provides a turbine engine including a combustor. The combustor includes a skeletal mesh structure comprising a plurality of structural elements configured to mate together to form the skeletal mesh structure. The combustor also includes an inner liner and an outer liner mounted to the skeletal mesh structure to define a combustion chamber. The inner liner includes a plurality of inner plates mounted to the inner side of the inner liner and a plurality of outer plates mounted to the outer side of the inner liner. The outer liner includes a plurality of inner plates mounted to the inner side of the outer liner and a plurality of outer plates mounted to the outer side of the outer liner.

[0058] The turbine engine according to any one of the foregoing clauses, wherein the plurality of inner plates and the plurality of outer plates are radially spaced apart from each other by a gap.

[0059] In the turbine engine according to any one of the foregoing clauses, each pair of continuous plates in the plurality of inner plates and each pair of continuous plates in the plurality of outer plates are separated using a separator.

[0060] The turbine engine according to any one of the foregoing clauses, wherein the plurality of structural elements have a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

[0061] The turbine engine according to any one of the foregoing clauses, wherein the plurality of inner plates and the plurality of outer plates have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

[0062] The turbine engine according to any one of the foregoing clauses further includes radial spacers disposed around the plurality of structural elements. The plurality of inner plates are connected to the plurality of structural elements. The radial spacers are disposed on the plurality of inner plates. The plurality of outer plates are disposed on the radial spacers. The plurality of outer plates are coupled to the plurality of structural elements using a plurality of clips.

[0063] The turbine engine according to any one of the foregoing clauses further includes a plurality of connecting rods. The plurality of inner plates and the plurality of outer plates are connected to the plurality of structural elements. The plurality of connecting rods are connected to the plurality of inner plates. The plurality of outer plates are connected to the plurality of connecting rods using a plurality of fasteners.

[0064] While the foregoing description pertains to certain embodiments of this disclosure, it should be noted that other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, features described in connection with one embodiment of this disclosure can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that, include: A skeleton mesh structure comprising multiple structural elements configured to be matched together to form the skeleton mesh structure; and Inner and outer liners, the inner and outer liners being mounted to the skeleton mesh structure to define the combustion chamber, The lining includes a plurality of first inner plates mounted to a first inner side of the skeleton mesh structure and a plurality of first outer plates mounted to a first outer side of the skeleton mesh structure. The outer lining includes a plurality of second inner plates mounted to the second inner side of the skeleton mesh structure and a plurality of second outer plates mounted to the outer side of the skeleton mesh structure.

2. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining are radially spaced apart from each other by a gap, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining are radially spaced apart from each other by a gap.

3. The burner according to claim 1, characterized in that, Wherein (i) a pair of continuous plates of the plurality of first inner plates in the lining and a pair of continuous plates of the plurality of first outer plates in the lining are separated by a separator, and / or (ii) a pair of continuous plates of the plurality of second inner plates in the outer lining and a pair of continuous plates of the plurality of second outer plates in the outer lining are separated by a separator.

4. 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.

5. The burner according to claim 4, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

6. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining have a filled polygonal shape and include a plurality of holes, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining have a filled polygonal shape and include a plurality of holes.

7. The burner according to claim 1, characterized in that, The liner further includes radial spacers disposed around the plurality of structural elements, (i) the plurality of first inner plates of the liner being connected to the plurality of structural elements, the radial spacers being disposed on the plurality of first inner plates, the plurality of first outer plates of the liner being disposed on the radial spacers, and the plurality of first outer plates being coupled to the plurality of structural elements using a plurality of clips, and / or (ii) the plurality of second inner plates of the outer liner being connected to the plurality of structural elements, the radial spacers being disposed on the plurality of second inner plates, the plurality of second outer plates of the outer liner being disposed on the radial spacers, and the plurality of second outer plates being coupled to the plurality of structural elements using a plurality of clips.

8. The burner according to claim 1, characterized in that, Further comprising a plurality of links, (i) the plurality of first inner plates and the plurality of first outer plates of the liner being connected to the plurality of structural elements, the plurality of links being connected to the plurality of first inner plates, and the plurality of first outer plates being connected to the plurality of links using a plurality of fasteners, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer liner being connected to the plurality of structural elements, the plurality of links being connected to the plurality of second inner plates, and the plurality of second outer plates being connected to the plurality of links using a plurality of fasteners.

9. The burner according to claim 1, characterized in that, Each of the plurality of structural elements has a cooling air passage.

10. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner panels of the liner are connected to the plurality of structural elements using a plurality of fasteners, the plurality of first outer panels of the liner are connected to the plurality of first inner panels, and the plurality of first outer panels are spaced apart from the plurality of first inner panels using a plurality of spacers, and / or (ii) the plurality of second inner panels of the outer liner are connected to the plurality of structural elements using a plurality of fasteners, the plurality of second outer panels of the outer liner are connected to the plurality of second inner panels, and the plurality of second outer panels are spaced apart from the plurality of second inner panels using a plurality of spacers.

11. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner panels of the lining further include a ceramic coating or thermal barrier coating deposited on the inner side of the plurality of first inner panels, and / or (ii) the plurality of first inner panels of the outer lining further include a ceramic coating or thermal barrier coating deposited on the inner side of the plurality of second inner panels.

12. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining have different thicknesses, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining have different thicknesses.

13. The burner according to claim 1, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining are bent to conform to the curvature of the skeleton mesh structure, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining are bent to conform to the curvature of the skeleton mesh structure.

14. A turbine engine, characterized in that, include: A burner, the burner comprising: (a) A skeleton mesh structure comprising a plurality of structural elements configured to be matched together to form the skeleton mesh structure; and (b) An inner liner and an outer liner, the inner liner and the outer liner being mounted to the skeleton mesh structure to define a combustion chamber, the inner liner comprising a plurality of first inner plates mounted to a first inner side of the skeleton mesh structure and a plurality of first outer plates mounted to a first outer side of the skeleton mesh structure, and the outer liner comprising a plurality of second inner plates mounted to a second inner side of the skeleton mesh structure and a plurality of second outer plates mounted to a second outer side of the skeleton mesh structure.

15. The turbine engine according to claim 14, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining are radially spaced apart from each other by a gap, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining are radially spaced apart from each other by a gap.

16. The turbine engine according to claim 14, characterized in that, Wherein (i) a pair of continuous plates of the plurality of first inner plates and a pair of continuous plates of the plurality of first outer plates in the lining are separated by a separator, and / or (ii) a pair of continuous plates of the plurality of second inner plates and a pair of continuous plates of the plurality of second outer plates in the outer lining are separated by a separator.

17. The turbine engine according to claim 14, 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.

18. The turbine engine according to claim 17, characterized in that, Wherein (i) the plurality of first inner plates and the plurality of first outer plates of the lining have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer lining have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

19. The turbine engine according to claim 14, characterized in that, The liner further includes radial spacers disposed around the plurality of structural elements, (i) the plurality of first inner plates of the liner being connected to the plurality of structural elements, the radial spacers being disposed on the plurality of first inner plates, the plurality of first outer plates of the liner being disposed on the radial spacers, and the plurality of first outer plates being coupled to the plurality of structural elements using a plurality of clips, and / or (ii) the plurality of second inner plates of the outer liner being connected to the plurality of structural elements, the radial spacers being disposed on the plurality of second inner plates, the plurality of second outer plates of the outer liner being disposed on the radial spacers, and the plurality of second outer plates being coupled to the plurality of structural elements using a plurality of clips.

20. The turbine engine according to claim 14, characterized in that, Further comprising a plurality of links, (i) the plurality of first inner plates and the plurality of first outer plates of the liner being connected to the plurality of structural elements, the plurality of links being connected to the plurality of first inner plates, and the plurality of first outer plates being connected to the plurality of links using a plurality of fasteners, and / or (ii) the plurality of second inner plates and the plurality of second outer plates of the outer liner being connected to the plurality of structural elements, the plurality of links being connected to the plurality of second inner plates, and the plurality of second outer plates being connected to the plurality of links using a plurality of fasteners.

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