Combustor liner

Abstract

A burner includes a skeleton meshwork having a plurality of structural elements configured to mate together to form the skeleton meshwork, each of the plurality of structural elements including a frame and a plurality of louvers connected to the frame. The burner also includes an inner liner mounted to the skeleton meshwork to define a combustion chamber. The inner liner includes a plurality of inner panels mounted to the skeleton meshwork, each of the plurality of inner panels being mounted to a corresponding one of the plurality of structural elements.

Description

Technical Field

[0001] This disclosure generally relates to burner linings. 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 According to embodiments of this disclosure Figure 1 A schematic cross-sectional view of the combustion section of a turbine engine.

[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 of one of a plurality of inner plates of a structural element mounted to a skeleton mesh structure according to an embodiment of the present invention.

[0010] Figure 6A This is a schematic front view of one of a plurality of structural elements having a plurality of shields according to an embodiment of the present disclosure.

[0011] Figure 6B This is a schematic cross-sectional view of one of a plurality of structural elements having a plurality of shields and one of a plurality of inner plates according to an embodiment of the present disclosure.

[0012] Figure 7A and 7B This is a schematic cross-sectional view of one of a plurality of structural elements having a plurality of shields and one of a plurality of inner plates according to an embodiment of the present disclosure.

[0013] Figure 7C This is a schematic cross-sectional view of one of a plurality of structural elements having a plurality of shields and one of a plurality of inner plates according to another embodiment of the present disclosure.

[0014] Figure 8A , 8B Figures 8C and 8C show various geometries and orientations of the shielding of the frame of the structural elements relative to the skeleton mesh structure according to embodiments 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 liner durability under harsh thermal and stress environments. The burner includes a skeleton mesh structure (also referred to as a hanger or truss) on which an inner liner and an outer liner are mounted. The skeleton mesh structure serves as the overall support structure for the inner and outer liners. In embodiments, the skeleton mesh structure may be made of metal. The skeleton mesh structure, together with the inner and outer liners, defines a combustion chamber. The inner liner includes a plurality of inner plates. The plurality of inner plates at least cover the inner side of the skeleton mesh structure. In embodiments, the plurality of inner 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 plurality of inner plates are exposed to a hot flame. The skeleton mesh structure may be shaped to operate as a baffle to provide impingement cooling air on the cold side of the inner plates. The skeleton mesh structure can significantly improve durability due to the elimination or reduction of circumferential stress. The plurality of inner plates are mounted to the skeleton mesh structure with the baffle. Baffles guide cooling air to impact multiple inner plates. A set of baffles can be arranged to supply guided cooling air to a single plate or multiple plates among the multiple inner plates. The skeleton mesh structure with baffles, together with multiple inner plates, can improve durability by reducing or essentially eliminating circumferential stress, while providing a lightweight lining construction for the burner. Additionally, the use of multiple inner plates with a skeleton mesh structure with baffles provides a modular or segmented construction that facilitates manufacturing and / or inspection, maintenance, and replacement of individual plates and / or baffles.

[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, forFigure 1 In the embodiment shown, the turbine engine 10 is a high-bypass turbine engine. 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] 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.

[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 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.

[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] 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.

[0029] Figure 2According 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. Of course, other combustion sections may include any other suitable structural configurations.

[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 defining 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, allowing for 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, 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 to have 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. The plurality of inner plates 302A are mounted and cover the inner side of the skeleton mesh structure 300. The plurality of inner plates 302A are exposed to the hot flame within the combustion chamber 88. In one embodiment, the plurality of inner panels 302A are made of ceramic or of metal coated with a ceramic coating to enhance resistance to relatively high temperatures. In another embodiment, the plurality of inner panels 302A may be made of ceramic material, ceramic matrix composite (CMC) material, or CMC-coated metal.

[0035] The skeletal mesh structure 300, together with the multiple inner plates 302A, improves 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. As a result, the total lifespan of the burner 80 is improved to more than 20,000 cycles. Furthermore, this construction offers the added benefit of modularity or segmentation, thus facilitating maintenance. In practice, if one or more of the multiple inner plates 302A fail, only the damaged one or more plates are replaced, rather than the entire lining 84. Moreover, this construction itself is 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, are mounted to the skeleton mesh structure 300. The multiple inner plates 302A include multiple holes 302C. Figure 4 As shown, multiple inner panels 302A are mounted on a skeleton mesh structure 300. Multiple holes 302C are distributed along the surfaces of the multiple inner panels 302A. The skeleton mesh structure 300 includes multiple baffles 400 configured to allow air to pass through gaps G between the baffles to impact the multiple inner panels 302A. The air impacting the multiple inner panels 302A can further enter through the multiple holes 302C in the multiple inner panels 302A to further cool the multiple inner panels 302A.

[0037] Figure 5 This is a schematic perspective view of one of a plurality of inner plates 302A of structural elements 306 mounted to a skeleton mesh structure 300 according to an embodiment of the present invention. Figure 5 As shown, the skeleton mesh structure 300 may include multiple structural elements 306, which are meshed together to form a structure. Figure 3 and 4 The skeleton mesh structure 300 is shown. Each of the plurality of inner panels 302A is mounted to a corresponding structural element among the plurality of structural elements 306 of the skeleton mesh structure 300. Figure 5As shown, each of the multiple structural elements 306 of the skeleton mesh structure 300 has a frame 306A and multiple baffles 400 connected to the frame 306A of each of the multiple structural elements 306 of the skeleton mesh structure 300. The multiple baffles 400 are spaced apart by gaps G to define multiple openings, thereby allowing air to pass through them. In an embodiment, the multiple baffles 400 may be integral with the frame 306A. However, the multiple baffles 400 may also be fastened to the frame 306A using fasteners or welded to the frame 306A. In an embodiment, the skeleton mesh structure 300 with baffles 400, together with multiple inner plates 302A, can improve durability by significantly reducing or eliminating circumferential stress, while providing a lightweight lining construction for the burner 80. In addition, the use of multiple inner plates 302A with the skeleton mesh structure 300 provides a modular or segmented construction that facilitates manufacturing and / or inspection, maintenance, and replacement of the individual inner plates 302A.

[0038] Figure 6A This is a schematic diagram of one of a plurality of structural elements 306 having a plurality of shields 400 according to an embodiment of the present disclosure. Figure 6A As shown, each of the plurality of structural elements 306 of the skeleton mesh structure 300 has a frame 306A, and a plurality of baffles 400 are connected or coupled to the frame 306A of each of the plurality of structural elements 306 of the skeleton mesh structure 300. The plurality of baffles 400 are spaced apart by gaps G to define a plurality of openings 402, thereby allowing air to pass through them.

[0039] Figure 6B This is a schematic cross-sectional view of one of a plurality of structural elements 306 having a plurality of shields 400 and one of a plurality of inner plates 302A according to an embodiment of the present disclosure. Figure 6B In the diagram, multiple baffles are schematically shown as curved measuring lines. The curved measuring lines representing the multiple baffles 400 have multiple openings 402 defined by gaps G between the respective multiple baffles 400. Each of the multiple inner plates 302A includes multiple holes 302C. In an embodiment, the multiple holes 302C are inclined relative to the surface 302S of each of the multiple inner plates 302A. Airflow, indicated by arrow 600, enters through the multiple openings 402, and a portion of the airflow exiting the multiple openings propagates along the surface 302S of each of the multiple inner plates 302A, while another portion of the airflow exiting the multiple openings enters through the multiple holes 302C. The angle and size of the multiple holes 302C in the multiple inner plates 302A relative to the surface 302S of each of the multiple inner plates 302A can be selected to control the amount of airflow entering the multiple holes 302C relative to the amount of airflow that will propagate along the surface 302S of each of the multiple inner plates 302A.

[0040] Figure 7A and 7B This is a schematic cross-sectional view of one of a plurality of structural elements 306 having a plurality of shields 400 and one of a plurality of inner plates 302A according to an embodiment of the present disclosure. Figure 7A and 7B Several parameters that affect the cooling effect on the airflow represented by arrow 600 are further shown. Figure 7A As shown). Figure 7B As shown, distance L1 is the distance between the bottoms of two consecutive shields in the plurality of shields 400. Distance L2 is the distance between the tops of two consecutive shields in the plurality of shields 400. Height H is the apparent height of the plurality of shields 400. Angle θ1 is the angle of hole 302C relative to surface 302S of the plurality of inner plates 302A. Angle θ2 is the angle of shield 400 relative to surface 302S of the plurality of inner plates 302A. Parameter S defines the spacing between the plurality of shields 400 and surface 302S of the plurality of inner plates 302A, and parameter T defines the thickness of the plurality of inner plates 302A.

[0041] Figure 7C This is a schematic cross-sectional view of one of a plurality of structural elements 306 having a plurality of shields 400 and one of a plurality of inner plates 302A according to another embodiment of the present disclosure. Figure 7C Another configuration of multiple baffles 400 is shown. For example... Figure 7C As shown, the baffle is formed as a unit in which a corner opening 402 is provided.

[0042] Table 1 shows the various parameters defined above and how they affect the cooling effect of airflow on the multiple inner panels 302A. For example, the ratio between L1 and L2 provides the greatest cooling effect between 0.1 and 1.1. However, lower values ​​in the range of 0.1 to 1.1 perform better. For example, the cooling effect is greater when L1 (the distance between the bottoms of two consecutive baffles in the multiple baffles 400) is less than L2 (the distance between the tops of two consecutive baffles in the multiple baffles 400). Similarly, the ratio between θ1 and θ2 provides the greatest cooling effect between 1 and 4.5. However, higher values ​​in the range of 1 to 4.5 perform better. For example, the cooling effect is greater when θ2 (the angle of baffle 400 relative to surface 302S) is greater than θ1 (the angle of hole 302C relative to surface 302S). Additionally, the ratio between S and T provides the greatest cooling effect between 0.1 and 2. DP / P is the percentage of air pressure drop across the liner.

[0043] Table 1

[0044] Min Max Comment L1 / L2 0.1 1.1 Lower value better θ1 / θ2 1 4.5 Higher value better S / T 0.1 2 Lower value better H / T 1 4 Higher value better DP / P, % 1 4 Higher value better Cooling effect parameter 1 3 Higher value better

[0045] The cooling effect (CE) parameter can be represented by the following equation (1). A cooling effect parameter between one and three is optimal. However, higher values ​​of the cooling effect parameter perform better and provide better cooling effect.

[0046] Cooling effect parameter = (L1 / L2) / (θ1 / θ2)×(S / T) / (DP / P) / (H / T)(1)

[0047] Figure 8A , 8B Figures 8C and 8C show various geometries and orientations of the frame 306A of the shield 400 relative to the structural element 306 of the skeleton mesh structure 300 according to embodiments of the present disclosure. Figure 8A The orientation of two adjacent baffles among a plurality of baffles 400 forming a “V” shape in a first direction according to an embodiment of the present disclosure is shown. Figure 8B The orientation of two adjacent baffles among a plurality of baffles 400 forming a “V” shape in a second direction opposite to the first direction is shown according to another embodiment of the present disclosure. Figure 8C The diagram shows the wave shape of two adjacent baffles among a plurality of baffles 400 according to yet another embodiment of the present disclosure. The adjacent baffles can also be oriented in relation to... Figure 8C In the opposite direction shown.

[0048] 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. Each of the plurality of structural elements has a frame and a plurality of baffles connected to the frame. The burner also includes a liner mounted to the skeletal mesh structure to define a combustion chamber. The liner has a plurality of inner plates mounted to the skeletal mesh structure, each of the inner plates being mounted to a corresponding structural element among the plurality of structural elements.

[0049] According to the burner described in the above clauses, the plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them.

[0050] According to any one of the foregoing clauses, the plurality of baffles are integral with the frame of each of the plurality of structural elements of the skeleton mesh structure.

[0051] According to any one of the foregoing clauses, each of the plurality of inner plates has a plurality of holes.

[0052] According to any one of the foregoing clauses, the plurality of holes are inclined relative to the surface of each of the plurality of inner plates.

[0053] According to any one of the foregoing clauses, in the burner, the plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them, and each of the plurality of inner plates has a plurality of holes, the plurality of holes being oriented such that a portion of the airflow exiting through the plurality of openings enters through the plurality of holes, and another portion of the airflow exiting the plurality of openings propagates along the surface of each of the plurality of inner plates.

[0054] According to any one of the foregoing clauses, the angle of the plurality of orifices relative to the surface is selected to control the gas flow rate entering the plurality of orifices relative to another gas flow rate propagating along the surface.

[0055] According to any one of the foregoing clauses, when the distance L1 between the bottoms of two consecutive baffles in the plurality of baffles is less than the distance L2 between the tops of two consecutive baffles in the plurality of baffles, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between L1 and L2 provides the maximum cooling effect between 0.1 and 1.1.

[0056] According to any one of the foregoing clauses, when the angle θ1 of the hole in each of the plurality of inner plates relative to the surface of each of the plurality of inner plates is greater than the angle θ2 of the baffle relative to the surface, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between θ1 and θ2 provides the maximum cooling effect between 1 and 4.5.

[0057] According to any one of the above clauses, when the distance S between the plurality of baffles and the surface is less than the thickness T of the plurality of inner plates, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between S and T provides the maximum cooling effect between 0.1 and 2.

[0058] Another aspect of this disclosure is to provide a turbine engine including a combustor. The combustor includes a skeletal mesh structure having a plurality of structural elements configured to mate together to form the skeletal mesh structure. Each of the plurality of structural elements includes a frame and a plurality of baffles connected to the frame. The combustor further includes a liner mounted to the skeletal mesh structure to define a combustion chamber. The liner has a plurality of inner plates mounted to the skeletal mesh structure, each of the inner plates being mounted to a corresponding structural element among the plurality of structural elements.

[0059] According to the turbine engine described in the above clauses, the plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them.

[0060] According to any one of the foregoing clauses, in the turbine engine, the plurality of shields are integral with the frame of each of the plurality of structural elements of the skeleton mesh structure.

[0061] The turbine engine according to any one of the foregoing clauses, each of the plurality of inner plates has a plurality of holes.

[0062] The turbine engine according to any one of the foregoing clauses, wherein the plurality of holes are inclined relative to the surface of each of the plurality of inner plates.

[0063] According to any one of the preceding clauses, in the turbine engine, the plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them, and each of the plurality of inner plates includes a plurality of holes, the plurality of holes being oriented such that a portion of the airflow exiting through the plurality of openings enters through the plurality of holes, and another portion of the airflow exiting the plurality of openings propagates along the surface of each of the plurality of inner plates.

[0064] According to any one of the foregoing clauses, the turbine engine selects the angle of the plurality of orifices relative to the surface to control the airflow entering the plurality of orifices relative to another airflow propagating along the surface.

[0065] According to any one of the foregoing clauses, when the distance L1 between the bottoms of two consecutive baffles in the plurality of baffles is less than the distance L2 between the tops of two consecutive baffles in the plurality of baffles, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between L1 and L2 provides the maximum cooling effect between 0.1 and 1.1.

[0066] According to any one of the foregoing clauses, when the angle θ1 of the hole in each of the plurality of inner plates relative to the surface of each of the plurality of inner plates is greater than the angle θ2 of the baffle relative to the surface, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between θ1 and θ2 provides the maximum cooling effect between 1 and 4.5.

[0067] According to any one of the foregoing clauses, when the distance S between the plurality of baffles and the surface is less than the thickness T of the plurality of inner plates, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between S and T provides the maximum cooling effect between 0.1 and 2.

[0068] 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: A skeleton mesh structure comprising a plurality of structural elements configured to be matched together to form the skeleton mesh structure, each of the plurality of structural elements comprising a frame and a plurality of baffles connected to the frame; and A liner, the liner being mounted to the skeleton mesh structure to define a combustion chamber, the liner comprising a plurality of inner panels, the plurality of inner panels being mounted to the skeleton mesh structure, each of the plurality of inner panels being mounted to a corresponding structural element among the plurality of structural elements; The plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them, and each of the plurality of inner plates includes a plurality of holes, the plurality of holes being oriented such that a portion of the airflow exiting through the plurality of openings enters through the plurality of holes, and another portion of the airflow exiting the plurality of openings propagates along the surface of each of the plurality of inner plates.

2. The burner according to claim 1, characterized in that, The plurality of baffles are integral with the frame of each of the plurality of structural elements of the skeleton mesh structure.

3. The burner according to claim 1, characterized in that, The plurality of holes are inclined relative to the surface of each of the plurality of inner plates.

4. The burner according to claim 1, characterized in that, The angle and size of the plurality of holes relative to the surface are selected to control the airflow entering the plurality of holes relative to another airflow propagating along the surface.

5. The burner according to claim 1, characterized in that, When the distance L1 between the bottoms of two consecutive baffles in the plurality of baffles is less than the distance L2 between the tops of two consecutive baffles in the plurality of baffles, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between L1 and L2 provides the maximum cooling effect between 0.1 and 1.

1.

6. The burner according to claim 1, characterized in that, When the angle θ2 of the baffle relative to the surface of each of the plurality of inner plates is greater than the angle θ1 of the hole in each of the plurality of inner plates relative to the surface, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between θ1 and θ2 provides the maximum cooling effect between 1 and 4.

5.

7. The burner according to claim 1, characterized in that, The cooling effect of the airflow on the multiple inner plates is higher when the distance S between the multiple baffles and the surface and the thickness T of the multiple inner plates make the ratio between S and T between 0.1 and 2 provide the maximum cooling effect.

8. A turbine engine, characterized in that, include: A burner, the burner comprising: (a) A skeletal mesh structure comprising a plurality of structural elements configured to be fitted together to form the skeletal mesh structure, each of the plurality of structural elements comprising a frame and a plurality of baffles connected to the frame; and (b) A liner, said liner being mounted to the skeleton mesh structure to define a combustion chamber, said liner comprising a plurality of inner panels, said plurality of inner panels being mounted to the skeleton mesh structure, each of said plurality of inner panels being mounted to a corresponding structural element of said plurality of structural elements; The plurality of baffles are spaced apart by gaps to define a plurality of openings, thereby allowing air to pass through them, and each of the plurality of inner plates includes a plurality of holes, the plurality of holes being oriented such that a portion of the airflow exiting through the plurality of openings enters through the plurality of holes, and another portion of the airflow exiting the plurality of openings propagates along the surface of each of the plurality of inner plates.

9. The turbine engine according to claim 8, characterized in that, The plurality of baffles are integral with the frame of each of the plurality of structural elements of the skeleton mesh structure.

10. The turbine engine according to claim 8, characterized in that, The plurality of holes are inclined relative to the surface of each of the plurality of inner plates.

11. The turbine engine according to claim 8, characterized in that, The angle of the plurality of holes relative to the surface is selected to control the air flow rate entering the plurality of holes relative to another air flow rate propagating along the surface.

12. The turbine engine according to claim 8, characterized in that, When the distance L1 between the bottoms of two consecutive baffles in the plurality of baffles is less than the distance L2 between the tops of two consecutive baffles in the plurality of baffles, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between L1 and L2 provides the maximum cooling effect between 0.1 and 1.

1.

13. The turbine engine according to claim 8, characterized in that, When the angle θ2 of the baffle relative to the surface of each of the plurality of inner plates is greater than the angle θ1 of the hole in each of the plurality of inner plates relative to the surface, the cooling effect of the airflow on the plurality of inner plates is higher, so that the ratio between θ1 and θ2 provides the maximum cooling effect between 1 and 4.

5.

14. The turbine engine according to claim 8, characterized in that, The cooling effect of the airflow on the multiple inner plates is higher when the distance S between the multiple baffles and the surface and the thickness T of the multiple inner plates make the ratio between S and T between 0.1 and 2 provide the maximum cooling effect.

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