Hollow plate design and construction of combustor liners

Abstract

A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh and a plurality of inner panels mounted to the inner mesh. The outer liner includes an outer mesh and a plurality of outer panels mounted to the outer mesh. Each of the plurality of inner and outer panels includes an inner wall, an outer wall, and a side wall defining a cavity to allow a flow of gas to circulate within the cavity to cool the inner wall.

Description

Technical Field

[0001] This disclosure generally relates to burner liners, and more specifically, to burner liners having a hollow plate and a skeletal mesh 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 2A According to embodiments of this disclosure Figure 1 A schematic cross-sectional view of the combustion section of a turbine engine.

[0007] Figure 2BAccording to embodiments of this disclosure Figure 1 A schematic cross-sectional view of the combustor of a turbine engine.

[0008] Figure 3 This is a schematic perspective view of a section of a burner according to an embodiment of the present disclosure.

[0009] Figure 4 This is a schematic diagram of the inner and outer lining sections of a burner according to an embodiment of the present disclosure.

[0010] Figure 5 This is a schematic diagram of one of a plurality of hot side plates installed on a skeleton mesh structure according to an embodiment of the present invention.

[0011] Figure 6A This is a schematic cross-sectional view of one of a plurality of hot side plates according to embodiments of the present disclosure, showing the arrangement of holes within the plurality of plates.

[0012] Figure 6B This is a schematic cross-sectional view of one of a plurality of hot side plates according to another embodiment of the present disclosure, showing the arrangement of a plurality of external holes within the plurality of hot side plates.

[0013] Figure 6C This is a schematic front view of one of a plurality of hot side plates according to an embodiment of the present disclosure, showing the arrangement of holes within the plurality of hot side plates.

[0014] Figure 6D This is a schematic cross-sectional view of one of a plurality of hot side plates according to embodiments of the present disclosure, showing the dimensions of the inner and outer walls, the dimensions of the side walls, and the dimensions of the cavity.

[0015] Figure 7 This is a schematic cross-sectional view of one of a plurality of hot side plates according to embodiments of the present disclosure, showing the various material layers.

[0016] Figures 8A to 8E Embodiments according to this disclosure are shown. Figure 3 and 4 Various geometric configurations of the structural elements of the skeleton mesh structure shown.

[0017] Figures 9A to 9E Various geometries of plates with multiple hot side plates according to embodiments of the present disclosure are shown.

[0018] Figure 10A and 10B This is a schematic cross-sectional view of a burner using a skeleton mesh structure along with multiple hot side plates according to an embodiment of the present disclosure. Detailed Implementation

[0019] 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.

[0020] 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.

[0021] 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.

[0022] 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.

[0023] 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.

[0024] 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 a combustion chamber. The inner and outer linings include multiple plates. The multiple plates at least cover the inner side of the skeletal mesh structure. In embodiments, the multiple plates may be made of a ceramic material, a ceramic matrix composite (CMC) material, or a metal coated with CMC or a thermal barrier coating (TBC). In embodiments, the multiple plates are exposed to a hot flame. Each of the multiple plates is hollow and includes an inner wall and an outer wall. The hollow multiple plates provide lining protection in the event of major surface damage due to hot gases. The skeletal mesh structure, together with the multiple plates, can improve durability by reducing or substantially eliminating circumferential stress, while providing a lightweight lining construction for the burner. In addition, the use of multiple plates with a skeletal mesh structure provides a modular or segmented construction that facilitates the manufacture and / or inspection, repair and replacement of individual plates.

[0025] 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. For example... 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.

[0026] 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.

[0027] In the depicted embodiment, fan section 14 includes a fan 38 with a variable pitch, the fan 38 having a plurality of fan blades 40 spaced apart and coupled to disk 42. As depicted, the fan blades 40 extend generally outward from 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 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) across power gearbox 46 via LPS 36. Power gearbox 46 includes a plurality of gears for adjusting or controlling the rotational speed of fan 38 relative to LPS 36 to a more efficient fan speed.

[0028] 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.

[0029] 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 it is directed through the HPC 24 and into the combustion section 26, where it mixes with and burns with the fuel to provide combustion gases 66.

[0030] 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.

[0031] 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.

[0032] However, Figure 1 The turbine engine 10 depicted herein is merely an example, 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.

[0033] Figure 2A According to embodiments of this 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.

[0034] 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 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.

[0035] 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. In the embodiment shown in FIG2, an outer shroud 94 (e.g., an annular shroud) and an inner shroud 96 (e.g., an 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 to 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.

[0036] 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.

[0037] 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, providing a swirling flow 130. As 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, enabling rapid mixing of air and fuel. The swirler (also called a mixer) establishes a localized low-pressure zone that forces some combustion products to recirculate, as shown in Figure 2, generating the desired high turbulence.

[0038] Figure 2B According to embodiments of this disclosure Figure 1 A schematic transverse cross-sectional view of the combustor 80 of the turbine engine 10. The combustor 80 includes an outer liner 82 and an inner liner 84 extending about a turbine centerline 12 to define a combustion chamber 88. The outer liner 82 includes a skeleton mesh structure 300 (also referred to as a hanger or truss) and a plurality of hot side plates 302A and a plurality of cold side plates 302B. The plurality of hot side plates 302A and the plurality of cold side plates 302B are mounted to the skeleton mesh structure 300 (outer mesh structure) of the outer liner 82. The inner liner 84 includes a skeleton mesh structure 301 (inner mesh structure) and a plurality of hot side plates 312A and a plurality of cold side plates 312B. The plurality of hot side plates 312A and the plurality of cold side plates 312B are mounted to the skeleton mesh structure 301 of the inner liner 84. The skeleton mesh structure 300 serves as a support structure for the hot side plates 302A and cold side plates 302B of the outer lining 82. The skeleton mesh structure 301 serves as a support structure for the hot side plates 312A and cold side plates 312B of the inner lining 84. In an embodiment, the skeleton mesh structures 300 and 301 are made of metal.

[0039] Multiple hot side plates 302A are mounted to and cover the inner side of the skeleton mesh structure 300, and cold side plates 302B are mounted to and cover the outer side of the skeleton mesh structure 300. In this respect, the multiple hot side plates 302A and the multiple cold side plates 302B can be resized and shaped to fit together or be connected together, and have adjacent edges with no gaps between adjacent plates 302A, 302B. In other embodiments, gaps may be provided between adjacent plates 302A, 302B. Multiple hot side plates 312A are mounted to and cover the outer side of the skeleton mesh structure 301, and cold side plates 312B are mounted to and cover the inner side of the skeleton mesh structure 301. In this respect, the multiple hot side plates 312A and the multiple cold side plates 312B can be resized and shaped to fit together or be connected together, and have adjacent edges with no gaps between adjacent plates 312A, 312B. In other embodiments, gaps may be provided between adjacent plates 312A, 312B. The plurality of hot side plates 302A of the outer liner 82 and the plurality of hot side plates 312A of the inner liner 84 are exposed to the hot flame within the combustion chamber 88. In embodiments, the plurality of hot side plates 302A, 312A are made of ceramic or of metal coated with a ceramic coating or a thermal barrier coating to enhance resistance to relatively high temperatures. In embodiments, the plurality of hot side plates 302A, 312A may be made of ceramic materials, ceramic matrix composite (CMC) materials, or of metal coated with CMC or a thermal barrier coating (TBC). In embodiments, the cold side plates 302B, 312B may be made of metal or ceramic matrix composite (CMC). In embodiments, the cold side plates 302B, 312B are thinner than the plurality of hot side plates 302A, 312A. In embodiments, such as Figure 2B As shown, both the inner lining 84 and the outer lining 82 are shown having a plurality of hot side plates 302A, 312A and a plurality of cold side plates 302B, 312B. In another embodiment, the plurality of cold side plates 302B, 312B may be optional for the outer lining 82, for the inner lining 84, or for both.

[0040] Figure 3 This is a schematic perspective view of the outer liner 82 of a burner 80 according to an embodiment of the present disclosure. Figure 3 For clarity, only the outer lining 82 is shown in this figure, and the inner lining 84 is omitted. The outer lining 82 is shown as having a generally cylindrical construction. The inner lining 84 is similar to the outer lining 82 in many respects. However, the radius of curvature of the inner lining 84 is smaller than that of the outer lining 82. Figure 3As shown, the outer liner 82 includes a skeleton mesh structure 300 (outer mesh structure) on which a plurality of hot side plates 302A and a plurality of cold side plates 302B are mounted. The plurality of hot side plates 302A and the plurality of cold side plates 302B are mounted to the skeleton mesh structure 300 of the outer liner 82. The skeleton mesh structure 300 serves as a support structure for the hot side plates 302A and cold side plates 302B of the outer liner 82. In an embodiment, the skeleton mesh structure 300 is made of metal. The plurality of hot side plates 302A are mounted to and cover the inner side of the skeleton mesh structure 300, and the cold side plates 302B are mounted to and cover the outer side of the skeleton mesh structure 300. In this respect, as... Figure 3 As shown, multiple hot side plates 302A and multiple cold side plates 302B can be resized and shaped to fit together and have adjacent edges, with no gap between adjacent plates 302A and 302B. In other embodiments, a gap may be provided between adjacent plates 302A and 302B.

[0041] The skeleton mesh structure 300, together with the multiple hot side plates 302A and multiple cold side plates 302B, can improve durability due to the reduction or elimination of circumferential stress, while providing a lightweight lining construction for the burner 80. Similarly, the skeleton mesh structure 301, together with the multiple hot side plates 312A and multiple cold side plates 312B, 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 hot side plates 302A, 312A or the multiple cold side plates 302B, 312B are damaged, only the damaged one or more plates are replaced, rather than the entire inner lining 84 or the entire outer lining 82. Moreover, this construction itself is relatively easy to inspect and maintain. All these benefits result in overall cost savings. The multiple hot side plates 302A and multiple cold side plates 302B of the outer lining 82 can also be referred to as multiple outer plates. The multiple hot side plates 312A and multiple cold side plates 312B of the inner lining 84 can also be referred to as multiple inner plates.

[0042] Figure 4 This is a schematic diagram of a section of the outer liner 82 of a burner 80 according to an embodiment of the present disclosure. Although references are made herein... Figure 4 The section of the outer liner 82 of the burner 80 (with multiple hot side plates 302A) is described, but the following description also applies to the inner liner 84 of the burner 80 (with multiple hot side plates 312A). Figure 4As shown, multiple hot side plates 302A are mounted to the skeleton mesh structure 300. The multiple hot side plates 302A include multiple external holes 302C. The multiple external holes 302C are distributed along the surface of the multiple hot side plates 302A to allow air to enter the combustion chamber 88.

[0043] Figure 5 This is a schematic diagram of one of a plurality of hot side plates 302A mounted to a skeleton mesh structure 300 according to an embodiment of the present invention. Figure 5 As shown, each of the plurality of hot side plates 302A is hollow and includes an inner wall 303A, an outer wall 303B, and a side wall 303C defining a cavity 302D. The plurality of hollow hot side plates 302A with cavities 302D provide lining protection in the event of damage to the main surface due to hot gases. The skeleton mesh structure 300 may include a plurality of structural elements 306, which are matched together to form... Figure 3 and 4 The skeleton mesh structure 300 is shown. Each of the plurality of hot side plates 302A is mounted to a plurality of structural elements 306 of the skeleton mesh structure 300. In an embodiment, a plurality of external holes 302C in the plurality of hot side plates 302A penetrate the outer wall 303B of the plurality of hot side plates 302A. In an embodiment, the plurality of external holes 302C communicate with a cavity 302D to allow airflow from the outer wall 303B to enter the cavity 302D through the plurality of external holes 302C, and to allow airflow to impact the inner wall 303A and to allow airflow to circulate within the cavity 302D to cool the inner wall 303A facing the combustion chamber 88. Figure 2A and 2B (as shown in the image).

[0044] In this embodiment, the skeleton mesh structure 300, together with the plurality of hot side plates 302A, can improve durability by reducing or substantially eliminating circumferential stress, while providing a lightweight lining construction for the burner 80. Additionally, the use of the plurality of hot side plates 302A with the skeleton mesh structure 300 provides a modular or segmented construction that facilitates the manufacture and / or inspection, repair, and replacement of the individual plates 302A.

[0045] Figure 6A This is a schematic cross-sectional view of one of a plurality of hot side plates 302A according to an embodiment of the present disclosure, showing the arrangement of a plurality of external holes 302C within the plurality of hot side plates 302A. Figure 6AAs shown, a plurality of hot side plates 302A have an inner wall 303A, an outer wall 303B, and a side wall 303C defining a cavity 302D. A plurality of external holes 302C are provided in the outer wall 303B of the plurality of hot side plates 302A. In addition to the plurality of external holes 302C, in an embodiment, a plurality of internal holes 302E are provided in the inner wall 303A of the plurality of hot side plates 302A. In an embodiment, the plurality of external holes 302C in the outer wall 303B of the plurality of hot side plates 302A are orthogonal holes relative to the outer wall 303B. In an embodiment, the plurality of internal holes 302E in the inner wall 303A of the plurality of hot side plates 302A are oblique holes relative to the inner wall 303A of the plurality of hot side plates 302A and communicate with the cavity 302D. The oblique holes, also called porous structures, are used to form a cooling air film on the surface of the inner wall 303A facing the hot gases inside the combustion chamber. In this embodiment, a plurality of outer holes 302C have an area Ah1, and a plurality of inner holes 302E have an area Ah2. In addition to the plurality of outer holes 302C and the plurality of inner holes 302E, the plurality of hot side plates 302A may also include a plurality of side holes 302L disposed in the sidewall 303C and communicating with the cavity 302D. The plurality of outer holes 302C, the plurality of inner holes 302E, and the plurality of side holes 302L allow airflow to pass through them, entering and exiting the cavity 302D, to cool the plurality of hot side plates 302.

[0046] Figure 6B This is a schematic cross-sectional view of one of a plurality of plates 602A according to an embodiment of the present disclosure, showing the arrangement of a plurality of external holes 602C within the plurality of plates 602A. Figure 6B As shown, a plurality of plates 602A have an inner wall 603A, an outer wall 603B, and a side wall 603C defining a cavity 602D. A plurality of external holes 602C are provided in the outer wall 603B of the plurality of plates 602A. In addition to the plurality of external holes 602C, in an embodiment, a plurality of internal holes 602E are provided in the inner wall 603A of the plurality of plates 602A. In an embodiment, as Figure 6BAs shown, multiple plates 602A include multiple fins or turbulence generators 602F. The multiple fins or turbulence generators 602F are disposed within a cavity 602D of the multiple plates 602A. The multiple fins or turbulence generators 602F are used to generate turbulence in the airflow within the cavity 602D. In an embodiment, multiple external holes 602C in the outer wall 603B of the multiple plates 602A are orthogonal holes relative to the outer wall 603B. In an embodiment, multiple internal holes 602E in the inner wall 603A of the multiple plates 602A are oblique holes relative to the inner wall 603A of the multiple plates 602A and communicate with the cavity 602D. The oblique holes, also called porous structures, are used to form a cooling air film on the surface of the inner wall 603A facing the hot gases inside the combustion chamber. In an embodiment, the multiple external holes 602C have an area Ah1, and the multiple internal holes 602E have an area Ah2. In addition to multiple outer holes 602C and multiple inner holes 602E, the multiple hot side plates 302A may also include multiple side holes 602L disposed in the sidewall 603C and communicating with the cavity 602D. The multiple outer holes 602C, multiple inner holes 602E and multiple side holes 602L allow airflow to pass through them, entering and exiting the cavity 602D, to cool the multiple plates 602A.

[0047] Figure 6C This is a schematic top view of one of a plurality of hot side plates 302A according to an embodiment of the present disclosure, showing the arrangement of a plurality of external holes 302C within the plurality of hot side plates 302A. In the embodiment, as Figure 6C As shown, multiple hot side plates 302A have a rectangular shape, with a length L and a height H defining an area L×H. Multiple external holes 302C are distributed on the outer wall 303B of the multiple hot side plates 302A.

[0048] Figure 6D This is a schematic cross-sectional view of one of the multiple hot side plates 302A according to an embodiment of the present disclosure, showing the dimensions of the inner wall 303A and outer wall 303B, the dimensions of the side wall 303C, and the dimensions of the cavity 302D. In the embodiment, the dimensions (thickness) of the inner wall 303A and outer wall 303B are “To”, the dimensions (thickness) of the side wall 303C are “w”, and the dimensions (width) of the cavity 302D are “Ti”. The total cross-sectional area A1 (including the cavity 302D) can be calculated using equation (1).

[0049] A1=L×(2To+Ti) (1)

[0050] The area A2 of cavity 302D can be calculated using equation (2).

[0051] A2=(L-2×w)×Ti (2)

[0052] The ratio of A2 / A1 is in the range of 0.2 to 0.98. The area of ​​the external cooling hole is Ah1, and the area of ​​the internal cooling hole is Ah2. The ratio of Ah1 / Ah2 is in the range of 1 to 2. The coefficient of performance (CEF) is given by equation (3). ΔP is in the range of 1.5% to 3.5%. ΔP is the air pressure drop across one of the multiple hot side plates 302A.

[0053] CEF=ΔP×A2 / A1×Ah1 / Ah2 (3)

[0054] The cooling efficiency coefficient ranges from 0.3% to 7%.

[0055] Figure 7 This is a schematic cross-sectional view of one of a plurality of hot side plates 302A according to an embodiment of the present disclosure, showing the various material layers. Figure 7 As shown, in this embodiment, the plurality of hot side plates 302A may be made of metal 312M. The metal 312M may be coated with a ceramic material or a ceramic matrix composite (CMC) material 312C or a thermal barrier coating (TBC).

[0056] Figures 8A to 8E Embodiments according to this disclosure are shown. Figure 3 and 4 The skeleton mesh structure 300 shown includes various geometric configurations of its structural elements. The skeleton mesh structure 300 may include elements that match or connect together to form... Figure 3 and 4 The skeleton mesh structure 300 shown has multiple structural elements 306. For example... Figures 8A to 8E As 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.

[0057] Figures 9A to 9E Various geometries of plates of multiple hot side plates 302A according to embodiments of the present disclosure are shown. In embodiments, such as Figures 9A to 9E As shown, each of the multiple hot side plates 302A can also have the same characteristics as... Figures 8A to 8E The corresponding shape of each of the multiple structural elements 306 shown matches the geometry. Each of the multiple hot side plates 302A is substantially a filled or solid shape. The filled shape is provided with multiple external holes 302C. The solid shape of each of the multiple hot side plates 302A ( Figures 9A to 9E (As shown) can be installed into the corresponding hollow shape of multiple structural elements 306 ( Figures 8A to 8E(As shown in the diagram). The term "hollow" is used herein to mean that multiple structural elements occupy less than 20% of the total area, or that the empty or hollow portion exceeds 80% of the total area. Multiple hot side panels 302A can be mounted 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.

[0058] Figure 10A and 10B This is a schematic cross-sectional view of a burner 80 using a skeleton mesh structure 300 along with a plurality of hot side plates 302A according to an embodiment of the present disclosure. Figure 10A In the burner 80, the inner liner 84 and the outer liner 82 are composed of a front section and a rear section of the respective liner. The front section may be a hanger type with multiple hot side plates 302A (hollow plates), and the rear section may be a solid liner from the prior art with an annular gap between the two sections. Figure 10B It is shown that both the inner lining 84 and the outer lining 82 are made of hangers and hollow panels.

[0059] As can be understood from the above discussion, a burner includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure and a plurality of inner plates mounted to the inner mesh structure. The outer liner includes an outer mesh structure and a plurality of outer plates mounted to the outer mesh structure. Each of the plurality of inner and outer plates includes an inner wall, an outer wall, and a sidewall defining a cavity to allow airflow to circulate within the cavity, thereby cooling the inner wall.

[0060] According to the above terms, the burner's outer wall includes a plurality of external holes that communicate with the cavity of each of the plurality of inner and outer plates.

[0061] According to any one of the foregoing clauses, the burner's inner wall includes a plurality of inner holes communicating with the cavity of each of the plurality of inner plates and outer plates.

[0062] The burner according to any one of the foregoing clauses, wherein the outer wall includes a plurality of external holes communicating with a cavity of each of the plurality of inner plates and outer plates, and the inner wall includes a plurality of internal holes communicating with a cavity of each of the plurality of inner plates and outer plates. The plurality of internal holes in the inner walls of the plurality of inner plates and outer plates are oblique holes relative to the inner walls of the plurality of inner plates and outer plates, and the plurality of external holes in the outer walls of the plurality of inner plates and outer plates are orthogonal holes relative to the outer walls of the plurality of inner plates and outer plates.

[0063] The burner according to any one of the foregoing clauses, the sidewall includes a plurality of side holes communicating with the cavity of each of the plurality of inner and outer plates.

[0064] According to any one of the foregoing clauses, each of the plurality of inner plates and outer plates includes a plurality of fins or turbulence generators disposed within the cavity of each of the plurality of inner plates and outer plates.

[0065] According to any one of the foregoing clauses, the inner mesh structure and the outer mesh structure include a plurality of structural elements connected together and having a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

[0066] According to any one of the foregoing clauses, the plurality of inner and outer plates have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

[0067] According to any one of the foregoing clauses, the plurality of inner and outer plates of the burner further comprise metal coated with a ceramic coating.

[0068] The burner according to any one of the foregoing clauses, wherein at least one of the plurality of inner and outer plates comprises one or more metal layers and one or more ceramic coatings deposited on the opposing surfaces of the one or more metal layers.

[0069] Another aspect of this disclosure is to provide a turbine engine including a combustor. The combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure and a plurality of inner plates mounted to the inner mesh structure. The outer liner includes an outer mesh structure and a plurality of outer plates mounted to the outer mesh structure. Each of the plurality of inner and outer plates includes an inner wall, an outer wall, and a sidewall defining a cavity to allow airflow to circulate within the cavity, thereby cooling the inner wall.

[0070] According to the above clauses, the outer wall of the turbine engine includes a plurality of external holes that communicate with a cavity in each of the plurality of inner plates and outer plates.

[0071] The turbine engine according to any one of the foregoing clauses, the inner wall includes a plurality of inner holes communicating with a cavity in each of the inner plate and the outer plate.

[0072] According to any one of the foregoing clauses, the turbine engine's outer wall includes a plurality of external holes communicating with a cavity of each of the plurality of inner and outer plates, and the inner wall includes a plurality of internal holes communicating with a cavity of each of the inner and outer plates. The plurality of internal holes in the inner walls of the plurality of inner and outer plates are oblique holes relative to the inner walls of the plurality of inner and outer plates, and the plurality of external holes in the outer walls of the plurality of inner and outer plates are orthogonal holes relative to the outer walls of the plurality of inner and outer plates.

[0073] The turbine engine according to any one of the foregoing clauses, the sidewall includes a plurality of side holes communicating with a cavity in each of the plurality of inner and outer plates.

[0074] The turbine engine according to any one of the foregoing clauses, each of the plurality of inner plates and outer plates includes a plurality of fins or turbulence generators disposed within the cavity of each of the plurality of plates.

[0075] According to any one of the foregoing clauses, the inner mesh structure and the outer mesh structure comprise a plurality of structural elements connected together and having a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

[0076] According to any one of the foregoing clauses, the plurality of inner and outer plates of the turbine engine have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

[0077] The turbine engine according to any one of the foregoing clauses, wherein the plurality of inner and outer plates further comprises metal coated with a ceramic coating.

[0078] The turbine engine according to any one of the foregoing clauses, wherein at least one of the plurality of inner plates and outer plates comprises one or more metal layers and one or more ceramic coatings deposited on the opposing surfaces of the one or more metal layers.

[0079] While the foregoing description is directed to preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that, include: An inner liner and an outer liner, wherein the inner liner and the outer liner define a combustion chamber therebetween. The lining includes an inner mesh structure and a plurality of first hot side plates and a plurality of first cold side plates mounted to the inner mesh structure. The outer lining includes an outer mesh structure and multiple second hot side plates and multiple second cold side plates mounted to the outer mesh structure. Each of the plurality of first hot side plates and the plurality of second hot side plates includes an inner wall, an outer wall, and a side wall defining a cavity to allow airflow to circulate within the cavity, thereby cooling the inner wall.

2. The burner according to claim 1, characterized in that, The outer wall includes a plurality of external holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

3. The burner according to claim 1, characterized in that, The inner wall includes a plurality of inner holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

4. The burner according to claim 1, characterized in that, The outer wall includes a plurality of external holes, which communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates. The inner wall includes a plurality of inner holes, which communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates. The plurality of inner holes in the inner walls of the plurality of first hot side plates and the plurality of second hot side plates are oblique holes relative to the inner walls of the plurality of first hot side plates and the plurality of second hot side plates, and The plurality of external holes in the outer walls of the plurality of first hot side plates and the plurality of second hot side plates are orthogonal holes relative to the outer walls of the plurality of first hot side plates and the plurality of second hot side plates.

5. The burner according to claim 1, characterized in that, The sidewall includes a plurality of side holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

6. The burner according to claim 1, characterized in that, Each of the plurality of first hot side plates and the plurality of second hot side plates includes a plurality of fins or turbulence generators disposed within the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

7. The burner according to claim 1, characterized in that, The inner mesh structure and the outer mesh structure include multiple structural elements connected together and having a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

8. The burner according to claim 7, characterized in that, The plurality of first hot side plates and the plurality of second hot side plates have solid polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

9. The burner according to claim 1, characterized in that, The plurality of first hot side plates and the plurality of second hot side plates further comprise metal coated with ceramic or thermal barrier coatings.

10. The burner according to claim 1, characterized in that, At least one of the plurality of first hot side plates and the plurality of second hot side plates includes one or more metal layers and one or more ceramic or thermal barrier coatings deposited on the opposing surfaces of the one or more metal layers.

11. A turbine engine, characterized in that, include: A burner, the burner comprising: An inner liner and an outer liner, wherein the inner liner and the outer liner define a combustion chamber therebetween. The lining includes an inner mesh structure and a plurality of first hot side plates and a plurality of first cold side plates mounted to the inner mesh structure. The outer lining includes an outer mesh structure and multiple second hot side plates and multiple second cold side plates mounted to the outer mesh structure. Each of the plurality of first hot side plates and the plurality of second hot side plates includes an inner wall, an outer wall, and a side wall defining a cavity to allow airflow to circulate within the cavity, thereby cooling the inner wall.

12. The turbine engine according to claim 11, characterized in that, The outer wall includes a plurality of external holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

13. The turbine engine according to claim 11, characterized in that, The inner wall includes a plurality of inner holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

14. The turbine engine according to claim 11, characterized in that, The outer wall includes a plurality of external holes, which communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates. The inner wall includes a plurality of inner holes, which communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates. The plurality of inner holes in the inner walls of the plurality of first hot side plates and the plurality of second hot side plates are oblique holes relative to the inner walls of the plurality of first hot side plates and the plurality of second hot side plates, and The plurality of external holes in the outer walls of the plurality of first hot side plates and the plurality of second hot side plates are orthogonal holes relative to the outer walls of the plurality of first hot side plates and the plurality of second hot side plates.

15. The turbine engine according to claim 11, characterized in that, The sidewall includes a plurality of side holes that communicate with the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

16. The turbine engine according to claim 11, characterized in that, Each of the plurality of first hot side plates and the plurality of second hot side plates includes a plurality of fins or turbulence generators disposed within the cavity of each of the plurality of first hot side plates and the plurality of second hot side plates.

17. The turbine engine according to claim 11, characterized in that, The inner mesh structure and the outer mesh structure include multiple structural elements connected together and having a hollow polygonal shape, the hollow polygonal shape having multiple sides defining a hollow surface.

18. The turbine engine according to claim 17, characterized in that, The plurality of first hot side plates and the plurality of second hot side plates have filled polygonal shapes that match the hollow polygonal shapes of the plurality of structural elements.

19. The turbine engine according to claim 11, characterized in that, The plurality of first hot side plates and the plurality of second hot side plates further comprise metal coated with ceramic or thermal barrier coatings.

20. The turbine engine according to claim 11, characterized in that, At least one of the plurality of first hot side plates and the plurality of second hot side plates includes one or more metal layers and one or more ceramic or thermal barrier coatings deposited on the opposing surfaces of the one or more metal layers.

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