Combustion chamber mesh structure

Abstract

A burner includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, a plurality of hot side plates mounted to the hot side of the inner mesh structure, and a plurality of cold side plates mounted to the cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot side plates mounted to the hot side of the outer mesh structure, and a plurality of cold side plates mounted to the cold side of the outer mesh structure. The burner further includes a plurality of clips configured to connect the plurality of hot side plates and the plurality of cold side plates to a plurality of structural elements of the inner and outer mesh structures.

Description

Technical Field

[0001] This disclosure generally relates to burner liners, and more specifically, to clips for attaching burner liners to the skeletal mesh structure of a burner. 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 longitudinal 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 the outer lining of a burner according to an embodiment of the present disclosure.

[0009] 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.

[0010] Figure 5A One of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to an embodiment of the present disclosure is a hot side plate. Figure 4 A schematic cross-sectional view at section line 5A-5A shown.

[0011] Figure 5B This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0012] Figure 6A This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0013] Figure 6B This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0014] Figure 6C This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0015] Figure 7A This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0016] Figure 7B This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0017] Figure 8A This is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0018] Figure 8BThis is a schematic cross-sectional view of one of a plurality of hot side plates of a structural element mounted to a skeleton mesh structure according to yet another embodiment of the present disclosure.

[0019] Figure 9A This is a schematic perspective view of one of a plurality of hot side plates and one of a plurality of cold side plates of a structural element mounted to a skeleton mesh structure according to another embodiment of the present disclosure.

[0020] Figure 9B This is a schematic cross-sectional view of one of a plurality of hot side plates and one of a plurality of cold side plates of a structural element mounted to a skeleton mesh structure according to an embodiment of the present disclosure.

[0021] Figure 9C This is a schematic cross-sectional view of one of a plurality of hot side plates or one of a plurality of cold side plates mounted to a structural element according to various embodiments of the present disclosure, showing various tapered or stepped configurations of the interface.

[0022] Figure 9D This is a schematic diagram of one of a plurality of hot side plates or one of a plurality of cold side plates mounted to a structural element according to various embodiments of the present disclosure, showing a polygonal (e.g., square) configuration of the interface. Detailed Implementation

[0023] 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.

[0024] 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.

[0025] 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.

[0026] 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.

[0027] 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.

[0028] 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 and outer liners include multiple hot side plates. The multiple hot side plates at least cover the hot sides of the skeleton mesh structure. In embodiments, the multiple hot side 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 hot side plates are exposed to a hot flame. The connection interfaces between the multiple hot side plates and the skeleton mesh structure can be configured to be resistant to thermal expansion. Furthermore, the multiple hot side plates connected to the interfaces of the skeleton mesh structure can be configured to improve performance by minimizing or substantially eliminating air leakage, so that the interfaces do not affect NO. x / Aerodynamics of the thermal field and film cooling. The interface between multiple hot side plates and the skeleton mesh structure can be an inverted "S" shaped interface, a conical interface, a stepped interface with axial bolts on the hanger without clamps, a variable clamp with axial bolts for stress relief and to accommodate thermal growth, etc. The skeleton mesh structure, together with multiple hot side plates, can improve durability by reducing or essentially eliminating circumferential stress, while providing a lightweight lining construction for the burner (achieving a weight reduction of more than 20 percent). In addition, the use of multiple hot side plates with a skeleton mesh structure having baffles provides a modular or segmented construction that facilitates the manufacture and / or inspection, maintenance, and replacement of individual plates and / or baffles.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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 air 62, as indicated by the arrow, is directed or directed into the bypass airflow passage 56, and a second portion of air 64, as indicated by the arrow, 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 62 and the second portion of air 64 is commonly referred to as the bypass ratio. The pressure of the second portion of air 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.

[0034] 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.

[0035] 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.

[0036] However, Figure 1 The turbine engine 10 depicted is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. In yet 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.

[0037] Figure 2A According to embodiments of this disclosure Figure 1 A schematic cross-sectional view of the combustion section 26 of the turbine engine 10. The combustion section 26 generally includes a combustor 80 that generates combustion gases discharged into the turbine section, or more specifically, into the HPT 28. The combustor 80 includes an outer liner 82, an inner liner 84, and a dome 86. The outer liner 82, inner liner 84, and dome 86 together define a combustion chamber 88 extending around the turbine centerline 12. Additionally, a diffuser 90 is positioned upstream of the combustion chamber 88. The diffuser 90 has an outer diffuser wall 90A and an inner diffuser wall 90B. The inner diffuser wall 90B is closer to the longitudinal centerline 12. The diffuser 90 receives 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.

[0038] In an embodiment, diffuser 90 can be used to slow down high-speed, highly compressed air from a compressor (not shown) to a speed optimal for 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.

[0039] Fuel nozzles (not shown) supply fuel to the fuel / air mixer 92 based on the desired performance of the burner 80 under various engine operating conditions. Figure 2AIn the illustrated embodiment, the outer shroud 94 (e.g., annular shroud) and the inner shroud 96 (e.g., annular shroud) are located upstream of the combustion chamber 88 to direct airflow into the fuel / air mixer 92. The outer shroud 94 and the inner shroud 96 may also direct a portion of the airflow from the diffuser 90 into an outer passage 98 defined between the outer liner 82 and the outer shell 100, and an inner passage 102 defined between the inner liner 84 and the inner shell 104. Additionally, the inner support cone 106 is further shown connected to the nozzle support 108 using a plurality of bolts 110 and nuts 112. However, other combustion sections may include any other suitable structural configuration.

[0040] 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.

[0041] 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 92. The dome 86 and the fuel / air mixer 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, as shown in Figure 2, generating the desired high turbulence.

[0042] Figure 2B According to embodiments of this disclosure Figure 1A 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 an outer 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 outer mesh structure 300 (outer mesh structure) of the outer liner 82. The inner liner 84 includes an inner 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 inner mesh structure 301 of the inner liner 84. The outer 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 inner 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 this embodiment, both the outer mesh structure 300 and the inner mesh structure 301 are made of metal.

[0043] Multiple hot side plates 302A are mounted to and cover the hot side of the outer mesh structure 300, and cold side plates 302B are mounted to and cover the cold side of the outer 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 hot side of the inner mesh structure 301, and cold side plates 312B are mounted to and cover the cold side of the inner 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 2BAs shown, both the inner liner 84 and the outer liner 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 liner 82, for the inner liner 84, or for both. The hot side of the inner mesh structure 301 faces and / or is adjacent to the combustion chamber 88, and the cold side of the inner mesh structure 301 faces and / or is adjacent to the inner channel 102 surrounding the liner, as shown. Figure 2A As shown. The hot side of the outer mesh structure 300 faces and / or is adjacent to the combustion chamber 88, and the cold side of the outer mesh structure 300 faces and / or is adjacent to the outer channel 98 surrounding the liner, as shown. Figure 2A As shown.

[0044] 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 3 As shown, the outer liner 82 includes an outer 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 outer mesh structure 300 of the outer liner 82. The outer 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 outer mesh structure 300 is made of metal. The plurality of hot side plates 302A are mounted to and cover the hot side of the outer mesh structure 300, and the cold side plates 302B are mounted to and cover the cold side of the outer 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.

[0045] The outer 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 inner 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.

[0046] 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 hot side plates 302A and multiple cold side plates 302B are mounted to the outer mesh structure 300. The multiple hot side plates 302A and multiple cold side plates 302B include multiple holes 302C. Figure 4 As shown, multiple hot side plates 302A and multiple cold side plates 302B are mounted on opposite sides of the outer mesh structure 300. Multiple holes 302C are distributed along the surfaces of the multiple hot side plates 302A and multiple cold side plates 302B to allow air to enter the combustion chamber 88 and / or to allow air to circulate within the gaps between the multiple hot side plates 302A and multiple cold side plates 302B. Although in this document relative to... Figure 4 The outer lining 82 has been discussed, but the same description can also be applied to the inner lining 84.

[0047] Figure 5A One of the plurality of hot side plates 302A of the structural element 306 installed in the external mesh structure 300 according to an embodiment of the present disclosure is a hot side plate. Figure 4 A schematic cross-sectional view at cross-sectional line 5A-5A shown. (See diagram.) Figure 5A As shown, the outer mesh structure 300 may include multiple structural elements 306, which are connected together to form a structure. Figure 3 and 4The diagram shows an outer mesh structure 300. Multiple clips 402 are provided to connect multiple hot side plates 302A and multiple cold side plates 302B to multiple structural elements 306. The multiple hot side plates 302A are connected to the multiple clips 402, and the multiple clips 402 are in turn connected to the multiple structural elements 306. The multiple clips 402 have a first end 402A (inner clamping structure) directly connected to the hot side plates 302A. The first end 402A of the multiple clips 402 is connected to the multiple hot side plates 302A. The second end 402B (inner clamping structure) of the multiple clips 402 is connected to the multiple structural elements 306 using multiple fasteners 404. The multiple cold side plates 302B are mounted or connected to the multiple clips 402. Multiple retaining members 409 (e.g., L-shaped clips) are used to push against multiple cold side plates 302B and clamp the multiple cold side plates 302B between the multiple clips 402 and the multiple retaining members 409 to retain the multiple cold side plates 302B. Fasteners 404 are used to connect the multiple retaining members 409 to the multiple clips 402 and structural element 306. Figure 5A As shown, the plurality of structural elements 306 may include a plurality of grooves 306A. A plurality of resilient sealing members 306B (e.g., C-shaped springs) may be disposed between the plurality of structural elements 306 and the plurality of clips 402.

[0048] Figure 5B This is a schematic cross-sectional view of one of a plurality of hot side plates 302A of a structural element 306 mounted to an external mesh structure 300 according to another embodiment of the present disclosure. Figure 5B As shown, with Figure 5A The illustrated embodiment is similar, with multiple heated side plates 302A connected to multiple clips 402. For example... Figure 5B As shown, multiple hot side plates 302A are also connected to multiple structural elements 306. Multiple clips 402 have a first end 402A (inner clamping structure). The first end 402A of the multiple clips 402 is connected to the multiple hot side plates 302A. The second end 402B (outer clamping structure) of the multiple clips 402 is connected to multiple fasteners 404. Multiple cold side plates 302B are mounted to the multiple clips 402. Multiple retaining members 409 are used to push the multiple cold side plates 302B against the multiple clips 402 to retain the multiple cold side plates 302B. Fasteners 404 are used to connect the multiple retaining members 409 to the multiple clips 402. Multiple resilient sealing members 306B (e.g., C-shaped springs) may be disposed between the multiple structural elements 306 and the multiple clips 402. Figure 5A The illustrated embodiments and Figure 5B The main difference between the embodiments shown is that, Figure 5A In the illustrated embodiment, multiple structural elements 306 extend and are directly coupled to multiple clips 402 using multiple fasteners 404, while Figure 5BIn the illustrated embodiment, the multiple structural elements 306 are not directly connected to the multiple clips 402. Figure 5A The configuration shown is commonly referred to as "axial bolts on clips on hanger." Figure 5B The structure shown is called "hanger free axial bolts on clips".

[0049] Figure 6A This is a schematic cross-sectional view of one of a plurality of hot side plates 302A of a structural element 306 mounted to an external mesh structure 300 according to another embodiment of the present disclosure. Figure 6A As shown, multiple heated side plates 302A are connected to multiple clips 406. The multiple heated side plates 302A have an L-shaped form with C-shaped notches 362C. In this embodiment, the multiple clips 406 are L-shaped. The C-shaped notches 362C of the multiple heated side plates 302A are configured to connect with corresponding arms of the L-shaped multiple clips 406. Each pair of clips in the multiple clips 406 is further connected together using fasteners 404. A spacer sleeve 407 is provided as a spacer between each pair of clips in the multiple clips 406. The multiple heated side plates 302A are also connected to multiple structural elements 306. Multiple seals 366 (e.g., C-shaped seals) may be provided at the interface between the multiple structural elements 306 and the multiple clips 406. Figure 6A As shown, multiple cold side plates 302B are mounted on multiple hot side plates 302A. The multiple cold side plates 302B are mounted on C-shaped slots 362C of the multiple hot side plates 302A. Multiple retaining members 408 are used to push the multiple cold side plates 302B against the multiple hot side plates 302A to retain the multiple cold side plates 302B. Multiple fasteners 404 are used to connect the multiple retaining members 408 to multiple clips 406. Each retaining member of the multiple retaining members 408 is clamped between each of the multiple fasteners 404 and each of the multiple clips 406.

[0050] Figure 6B This is a schematic cross-sectional view of one of the multiple hot side plates 302A of the structural element 306 mounted to the external mesh structure 300 according to another embodiment of the present disclosure. Figure 6B The embodiments shown are similar in many respects to Figure 6A The illustrated embodiments are similar. For example... Figure 6BAs shown, multiple heated side plates 302A are connected to multiple clips 406. The multiple heated side plates 302A have an L-shaped form with C-shaped slots 362C. In an embodiment, the multiple clips 406 are L-shaped. The C-shaped slots 362C of the multiple heated side plates 302A are configured to connect with corresponding arms of the L-shaped multiple clips 406. Each pair of clips in the multiple clips 406 is further connected together using fasteners 404. A spacer sleeve 407 is provided as a spacer between each pair of clips in the multiple clips 406. The multiple heated side plates 302A are also connected to multiple structural elements 306. In an embodiment, as... Figure 6B As shown, multiple structural elements 306 have pointed shapes that fit into corresponding cavities formed by a pair of hot side plates 302A among a plurality of hot side plates 302A. Multiple seals 366 (e.g., C-shaped seals) may be provided at the interface between the separator sleeve 407 and the multiple structural elements 306. Figure 6B As shown, multiple cold side plates 302B are mounted on multiple hot side plates 302A. The multiple cold side plates 302B are mounted on C-shaped slots 362C of the multiple hot side plates 302A. Multiple retaining members 408 are used to push the multiple cold side plates 302B against the multiple hot side plates 302A to retain the multiple cold side plates 302B. Multiple fasteners 404 are used to connect the multiple retaining members 408 to multiple clips 406. Each retaining member of the multiple retaining members 408 is clamped between each of the multiple fasteners 404 and each of the multiple clips 406. Multiple seals (e.g., C-shaped seals) 386 are provided between the multiple retaining members 408 and the multiple cold side plates 302B. Figure 6A and 6B The two embodiments shown are referred to as “axial bolts on hangers without clamps” because the multiple structural elements 306 are not directly connected to the multiple fasteners 404.

[0051] Figure 6C This is a schematic cross-sectional view of one of the multiple hot side plates 302A of the structural element 306 mounted to the external mesh structure 300 according to another embodiment of the present disclosure. Figure 6C The embodiments shown are similar in many respects to Figure 6B The illustrated embodiments are similar. Figure 6C The illustrated embodiments and Figure 6B One difference between the illustrated embodiments is that, in Figure 6B In the middle, multiple structural elements 306 have pointed shapes, while Figure 6C In the illustrated embodiment, multiple structural elements 306 have a circular shape (e.g., a circular or elliptical cross-sectional shape). Figure 6C As shown, a plurality of structural elements 306 have a circular shape, which is adapted to fit into a corresponding cavity formed by a pair of thermal side plates of a plurality of thermal side plates 302A.

[0052] Figure 7A This is a schematic cross-sectional view of one of a plurality of hot side plates 302A of a structural element 306 mounted to an external mesh structure 300 according to another embodiment of the present disclosure. Figure 7A As shown, multiple hot side panels 302A are connected to multiple clips 402, which in turn are connected to multiple structural elements 306. The multiple clips 402 have a hook-like shape (e.g., a C-shape). The first end 402A of the hook-shaped clips 402 is connected to the multiple hot side panels 302A. The second end 402B of the hook-shaped clips 402 is connected to the multiple structural elements 306 using multiple fasteners 490 (e.g., I-shaped clips). Each of the multiple fasteners 490 is inserted through a pair of clips in the multiple clips 402 and through one of the multiple structural elements 306 clamped between the pair of clips in the multiple clips 402. Multiple cold side panels 302B are mounted to the multiple clips 402. The multiple fasteners 490 (e.g., I-shaped clips) are configured to hold the multiple cold side panels 302B against the multiple clips 402. Figure 5A As shown, the plurality of structural elements 306 may include a plurality of grooves 306A. A plurality of resilient sealing members 306B (e.g., C-shaped seals) may be disposed between the plurality of structural elements 306 and the plurality of clips 402.

[0053] Figure 7B This is a schematic cross-sectional view of one of a plurality of hot side plates 302A of a structural element 306 mounted to an external mesh structure 300 according to another embodiment of the present disclosure. Figure 7B As shown, multiple hot side plates 302A are connected to multiple clips 402, which in turn are connected to multiple structural elements 306. The multiple clips 402 have a hook-like shape (e.g., a C-shape). The first end 402A of the hook-shaped clips 402 is connected to the multiple hot side plates 302A. The second end 402B of the hook-shaped clips 402 is connected to the multiple structural elements 306 using multiple fasteners 490 (e.g., I-shaped clips). Multiple cold side plates 302B are mounted to the multiple clips 402. The multiple fasteners 490 (e.g., I-shaped clips) are configured to hold the multiple cold side plates 302B against the multiple clips 402. Each of the multiple fasteners 490 is fastened to each of the multiple structural elements 306 via an insertion member 494 using another fastener 492 (e.g., a screw). Figure 7B As shown, multiple resilient sealing members 306B (e.g., C-shaped seals) can be disposed between multiple structural elements 306 and multiple clips 402.

[0054] Figure 8AThis is a schematic cross-sectional view of one of a plurality of hot side plates 302A of a structural element 306 mounted to an external mesh structure 300 according to another embodiment of the present disclosure. Figure 8A As shown, multiple hot side plates 302A are connected to multiple clips 402, which in turn are connected to multiple structural elements 306. The multiple clips 402 have a hook-like shape (e.g., an S-shape). The first end 402A of the hook-shaped clips 402 is connected to the multiple hot side plates 302A. The second end 402B of the hook-shaped clips 402 is connected to the multiple structural elements 306 using a press clip 500. The press clip 500 presses against a pair of clips in the multiple clips 402 to bias the pair of clips in the multiple clips 402 against one of the structural elements 306. Each press clip 500 is inserted at the second end 402B of the pair of clips in the multiple clips 402. Multiple cold side plates 302B are mounted to the multiple clips 402. The multiple pressing clips 500 are also configured to hold the multiple cold side plates 302B against the multiple clips 402 by pressing against the surfaces of the multiple cold side plates. For example... Figure 8A As shown, the plurality of structural elements 306 may include a plurality of grooves 306A (cooling grooves). A plurality of resilient sealing members 306B (e.g., C-shaped seals) may be disposed between the plurality of structural elements 306 and the plurality of clips 402.

[0055] Figure 8B This is a schematic cross-sectional view of one of the multiple hot side plates 302A of the structural element 306 mounted to the external mesh structure 300 according to another embodiment of the present disclosure. Figure 8B The embodiments shown are similar in many respects to Figure 8A The illustrated embodiment is similar. However, instead of multiple press clips 500, Figure 8B The illustrated embodiment uses multiple press clips 502. The multiple press clips 502 are of different types and have edges for easy and quick detachment from the multiple clips 402.

[0056] Figure 9A This is a schematic perspective view of one of a plurality of hot side plates 302A and one of a plurality of cold side plates 302B mounted to a structural element 306 of an external mesh structure 300 according to another embodiment of the present disclosure. Figure 9AAs shown, each of the plurality of hot side plates 302A is mounted to a structural element 306 of the outer mesh structure 300, and the interface 902A between each hot side plate 302A and the corresponding structural element 306 has an S-shaped configuration. Similarly, each of the plurality of cold side plates 302B is mounted to a structural element 306 of the outer mesh structure 300, and the interface 902B between each cold side plate 302B and the corresponding structural element 306 has an S-shaped configuration.

[0057] Figure 9B This is a schematic cross-sectional view of one of a plurality of hot side plates 302A and one of a plurality of cold side plates 302B mounted to a structural element 306 of an external mesh structure 300 according to an embodiment of the present disclosure. Figure 9B The interface 902B between each of the plurality of cold side plates 302B and the corresponding structural element 306 has an S-shaped structure, while the interface 902A between each of the plurality of hot side plates 302A and the corresponding structural element 306 has a tapered structure.

[0058] Figure 9C This is a schematic cross-sectional view of one of a plurality of hot side plates 302A or one of a plurality of cold side plates 302B mounted to structural element 306 according to an embodiment of the present disclosure, showing various conical or stepped configurations of interfaces 902A, 902B.

[0059] Figure 9D This is a schematic diagram of one of a plurality of hot side plates 302A or one of a plurality of cold side plates 302B mounted to structural element 306 according to various embodiments of the present disclosure, showing the polygonal (e.g., square) configuration of interfaces 902A, 902B.

[0060] As described in the preceding paragraphs, the connection interfaces between the multiple hot side plates 302A and / or the multiple cold side plates 302B and the outer mesh structure 300 can be configured to be resistant to thermal expansion. Furthermore, the connection interfaces between the multiple hot side plates 302A and the outer mesh structure 300 can be configured to improve performance by minimizing or essentially eliminating air leakage, thus ensuring that the interfaces do not affect NO. x / Aerodynamics of the thermal field and film cooling. The interface between the multiple hot side plates 302A and the outer mesh structure 300 can be an inverted "S" shaped interface, a conical interface, a stepped interface with axial bolts on the hanger without clamps, a variable clamp with axial bolts for stress relief and to accommodate thermal growth, etc.

[0061] 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, a plurality of hot-side plates mounted to the hot side of the inner mesh structure, and a plurality of cold-side plates mounted to the cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot-side plates mounted to the hot side of the outer mesh structure, and a plurality of cold-side plates mounted to the cold side of the outer mesh structure. The burner further includes a plurality of clips configured to connect the plurality of hot-side plates and the plurality of cold-side plates to a plurality of structural elements of the inner and outer mesh structures.

[0062] According to the burner described in the foregoing clauses, the plurality of hot side plates are connected to the plurality of clips, which in turn are connected to the plurality of structural elements.

[0063] According to any one of the foregoing clauses, the plurality of cold side plates are connected to the plurality of clips.

[0064] The burner according to any one of the foregoing clauses further includes a plurality of retaining members configured to push the plurality of cold side plates against the plurality of clips to retain the plurality of cold side plates; and a plurality of fasteners configured to connect the retaining members to the plurality of clips and the structural element.

[0065] The burner according to any one of the foregoing clauses further includes a plurality of resilient members disposed between the plurality of structural elements and the plurality of clips to provide a seal between the plurality of structural elements and the plurality of clips.

[0066] The burner according to any one of the foregoing clauses further includes a plurality of fasteners that connect the plurality of clips to the structural element and push the plurality of cold side plates against the plurality of clips to retain the plurality of cold side plates.

[0067] The burner according to any one of the foregoing clauses further includes a plurality of fasteners configured to hold the plurality of cold side plates against the plurality of clips, each of the plurality of fasteners being fastened to each of the plurality of structural elements via an insert member using another fastener.

[0068] Another aspect of this disclosure is to provide a burner including an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, a plurality of hot side plates mounted to the hot side of the inner mesh structure, and a plurality of cold side plates mounted to the cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot side plates mounted to the hot side of the outer mesh structure, and a plurality of cold side plates mounted to the cold side of the outer mesh structure. The burner further includes a plurality of clips configured to connect the plurality of hot side plates to the plurality of cold side plates.

[0069] According to any one of the foregoing clauses, the plurality of hot side plates are connected to the plurality of clips, and each pair of clips is connected together using fasteners.

[0070] The burner according to any one of the foregoing clauses further includes a spacer sleeve, the spacer sleeve being configured as a spacer between each pair of clips in the plurality of clips.

[0071] According to any one of the foregoing clauses, the plurality of hot side plates are connected to a plurality of structural elements of the inner mesh structure and the outer mesh structure.

[0072] According to any one of the foregoing clauses, the plurality of cold side plates are mounted on the plurality of hot side plates.

[0073] The burner according to any one of the foregoing clauses further includes a plurality of retaining members configured to push the plurality of cold side plates against the plurality of hot side plates.

[0074] A further 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, a plurality of hot side plates mounted to the hot side of the inner mesh structure, and a plurality of cold side plates mounted to the cold side of the inner mesh structure. The outer liner includes an outer mesh structure, a plurality of hot side plates mounted to the hot side of the outer mesh structure, and a plurality of cold side plates mounted to the cold side of the outer mesh structure. The combustor further includes a plurality of clips configured to connect the plurality of hot side plates and the plurality of cold side plates to a plurality of structural elements of the inner and outer mesh structures.

[0075] According to any one of the foregoing clauses, in the turbine engine, the plurality of hot side plates are connected to the plurality of clips, which in turn are connected to the plurality of structural elements.

[0076] The turbine engine according to any one of the foregoing clauses, wherein the plurality of cold side plates are connected to the plurality of clips.

[0077] The turbine engine according to any one of the foregoing clauses further includes a plurality of retaining members configured to push the plurality of cold side plates against the plurality of clamps to retain the plurality of cold side plates; and a plurality of fasteners configured to connect the retaining members to the plurality of clamps and the structural elements.

[0078] The turbine engine according to any one of the foregoing clauses further includes a plurality of elastic members disposed between the plurality of structural elements and the plurality of clips.

[0079] The turbine engine according to any one of the foregoing clauses further includes a plurality of fasteners for engaging the plurality of clips to the structural element and for pushing the plurality of cold side plates against the plurality of clips to retain the plurality of cold side plates.

[0080] The turbine engine according to any one of the foregoing clauses further includes a plurality of fasteners configured to hold the plurality of cold side plates against the plurality of clamps, each of the plurality of fasteners being fastened to each of the plurality of structural elements via an insert member using another fastener.

[0081] 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 by comprise: an inner liner and an outer liner defining a combustion chamber, the inner liner comprising an inner mesh structure, a plurality of hot-side panels mounted to a hot side of the inner mesh structure, and a plurality of cold-side panels mounted to a cold side of the inner mesh structure, and the outer liner comprising an outer mesh structure, a plurality of hot-side panels mounted to a hot side of the outer mesh structure, and a plurality of cold-side panels mounted to a cold side of the outer mesh structure; and a plurality of clips configured to couple the plurality of hot-side panels and the plurality of cold-side panels of the inner liner to a plurality of structural elements of the inner mesh structure and / or to couple the plurality of hot-side panels and the plurality of cold-side panels of the outer liner to a plurality of structural elements of the outer mesh structure.

2. The burner of claim 1, wherein wherein the plurality of hot-side panels of the inner liner and / or the plurality of hot-side panels of the outer liner are coupled to the plurality of clips, and each pair of clips of the plurality of clips is in turn coupled to the plurality of structural elements of the inner mesh structure and / or the plurality of structural elements of the outer mesh structure, respectively.

3. The burner of claim 1, wherein wherein the plurality of cold-side panels of the inner liner and / or the plurality of cold-side panels of the outer liner are mounted on the plurality of clips.

4. The burner of claim 1, wherein further comprising a plurality of retention members configured to urge the plurality of cold-side panels of the inner liner and / or the plurality of cold-side panels of the outer liner against the plurality of clips to retain the plurality of cold-side panels of the inner liner and / or the plurality of cold-side panels of the outer liner; and a plurality of fasteners coupling the plurality of retention members to the plurality of clips and the plurality of structural elements of the inner mesh structure and / or coupling the plurality of retention members to the plurality of clips and the plurality of structural elements of the outer mesh structure.

5. The burner of claim 1, wherein further comprising a plurality of elastic members disposed between the plurality of structural elements of the inner mesh structure and the plurality of clips to provide a seal between the plurality of structural elements of the inner mesh structure and the plurality of clips and / or disposed between the plurality of structural elements of the outer mesh structure and the plurality of clips to provide a seal between the plurality of structural elements of the outer mesh structure and the plurality of clips.

6. The burner of claim 1, wherein further comprising a plurality of fasteners to couple the plurality of clips to the plurality of structural elements of the inner mesh structure and urge the plurality of cold-side panels of the inner liner against the plurality of clips to retain the plurality of cold-side panels of the inner liner and / or to couple the plurality of clips to the plurality of structural elements of the outer mesh structure and urge the plurality of cold-side panels of the outer liner against the plurality of clips to retain the plurality of cold-side panels of the outer liner.

7. The burner of claim 1, wherein Further comprising a plurality of fasteners configured to hold the plurality of cold side panels of the inner liner against the plurality of clips, each fastener of the plurality of fasteners fastened to each structural element of the plurality of structural elements of the inner reticulation using another fastener via an insert member, and / or hold the plurality of cold side panels of the outer liner against the plurality of clips, each fastener of the plurality of fasteners fastened to each structural element of the plurality of structural elements of the outer reticulation using the another fastener via an insert member.

8. A burner characterized by, Comprising: an inner liner and an outer liner defining a combustion chamber, the inner liner comprising an inner reticulation, a plurality of hot side panels mounted to a hot side of the inner reticulation, and a plurality of cold side panels mounted to a cold side of the inner reticulation, and the outer liner comprising an outer reticulation, a plurality of hot side panels mounted to a hot side of the outer reticulation, and a plurality of cold side panels mounted to a cold side of the outer reticulation; and a plurality of clips configured to couple the plurality of hot side panels of the inner liner to the plurality of cold side panels of the inner liner, and / or couple the plurality of hot side panels of the outer liner to the plurality of cold side panels of the outer liner.

9. The burner of claim 8, wherein wherein the plurality of hot side panels of the inner liner or the plurality of hot side panels of the outer liner are coupled to the plurality of clips, and each pair of clips of the plurality of clips is in turn coupled together using a fastener.

10. The burner of claim 8, wherein Further comprising a spacer sleeve disposed as a spacer between each pair of clips of the plurality of clips.

11. The burner of claim 8, wherein wherein the plurality of hot side panels of the inner liner are coupled to a plurality of structural elements of the inner reticulation and the plurality of hot side panels of the outer liner are coupled to a plurality of structural elements of the outer reticulation.

12. The burner of claim 8, wherein wherein the plurality of cold side panels of the inner liner are mounted on the plurality of hot side panels of the inner liner, and / or the plurality of cold side panels of the outer liner are mounted on the plurality of hot side panels of the outer liner.

13. The burner of claim 8, wherein Further comprising a plurality of retention members configured to urge the plurality of cold side panels of the inner liner against the plurality of hot side panels of the inner liner, or the plurality of cold side panels of the outer liner against the plurality of hot side panels of the outer liner.

14. A turbine engine characterized by, Comprising: a combustor comprising: (a) an inner liner and an outer liner defining a combustion chamber, the inner liner comprising an inner reticulation, a plurality of hot side panels mounted to a hot side of the inner reticulation, and a plurality of cold side panels mounted to a cold side of the inner reticulation, and the outer liner comprising an outer reticulation, a plurality of hot side panels mounted to a hot side of the outer reticulation, and a plurality of cold side panels mounted to a cold side of the outer reticulation; and (b) a plurality of clips configured to couple the plurality of hot side panels and the plurality of cold side panels of the inner liner to a plurality of structural elements of the inner reticulation, and / or couple the plurality of hot side panels and the plurality of cold side panels of the outer liner to a plurality of structural elements of the outer reticulation.

15. The turbine engine of claim 14, wherein, wherein the plurality of hot side panels of the inner liner and / or the plurality of hot side panels of the outer liner are coupled to the plurality of clips, which are in turn coupled to the plurality of structural elements of the inner net structure and / or to the plurality of structural elements of the outer net structure.

16. The turbine engine of claim 14, wherein, wherein the plurality of cold side panels of the inner liner and / or the plurality of cold side panels of the outer liner are mounted on the plurality of clips.

17. The turbine engine of claim 14, wherein, further comprising a plurality of retention members configured to urge the plurality of cold side panels of the inner liner and / or the plurality of cold side panels of the outer liner against the plurality of clips to retain the plurality of cold side panels of the inner liner and / or the plurality of cold side panels of the outer liner; and a plurality of fasteners coupling the plurality of retention members to the plurality of clips and the plurality of structural elements of the inner net structure or coupling the plurality of retention members to the plurality of clips and the plurality of structural elements of the outer net structure.

18. The turbine engine of claim 14, wherein, further comprising a plurality of elastic members disposed between the plurality of structural elements of the inner net structure and the plurality of clips to provide a seal between the plurality of structural elements of the inner net structure and the plurality of clips and / or disposed between the plurality of structural elements of the outer net structure and the plurality of clips to provide a seal between the plurality of structural elements of the outer net structure and the plurality of clips.

19. The turbine engine of claim 14, wherein, further comprising a plurality of fasteners to couple the plurality of clips to the plurality of structural elements of the inner net structure and urge the plurality of cold side panels of the inner liner against the plurality of clips to retain the plurality of cold side panels of the inner liner and / or to couple the plurality of clips to the plurality of structural elements of the outer net structure and urge the plurality of cold side panels of the outer liner against the plurality of clips to retain the plurality of cold side panels of the outer liner.

20. The turbine engine of claim 14, wherein, further comprising a plurality of fasteners configured to retain the plurality of cold side panels of the inner liner against the plurality of clips, wherein each fastener of the plurality of fasteners is fastened to each of the plurality of structural elements of the inner net structure using another fastener via an insertion member and / or to retain the plurality of cold side panels of the outer liner against the plurality of clips, wherein each fastener of the plurality of fasteners is fastened to each of the plurality of structural elements of the outer net structure using the another fastener via an insertion member.

Images