Combustor for turbine engine comprising insulating member

Abstract

A combustor for a turbine engine includes a combustion chamber for combustion of fuel and air, and the combustion of fuel and air produces heat. The mixer assembly is disposed at the front end of the combustor for receiving and mixing fuel and air and injecting the fuel and air into the combustion chamber for combustion. An insulating member is attached to the at least one structural member, and the insulating member at least partially defines a combustion chamber. The insulating member has a functional thickness and is fastened to the at least one structural member without reducing the functional thickness of the insulating member.

Description

Technical Field

[0001] This disclosure generally relates to a turbine engine having a burner and insulating components (e.g., a heat shield). Background Technology

[0002] For example, turbine engines used in aircraft typically include a fan and a turbocharger arranged in fluid communication with each other. The combustor receives fuel and air, produces a fuel-air mixture, and burns the mixture. The combustion of fuel and air generates heat. A heat shield protects the combustor components from the heat generated by combustion. Attached Figure Description

[0003] Features and advantages will become apparent from the following more detailed description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally denote identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 This is a schematic cross-sectional view of a turbine engine taken along the longitudinal centerline axis of the turbine engine according to the present disclosure.

[0005] Figure 2 It is a schematic cross-sectional view of the burner taken along the longitudinal centerline axis of the burner according to this disclosure.

[0006] Figure 3A This is a partial cross-sectional view of the heat shield mounting assembly taken along the longitudinal centerline of the burner according to this disclosure.

[0007] Figure 3B This is a schematic diagram of the spring plate according to this disclosure.

[0008] Figure 4A This is a partial cross-sectional view of the heat shield mounting assembly taken along the longitudinal centerline of the burner according to this disclosure.

[0009] Figure 4B This is a schematic diagram of the spring plate according to this disclosure.

[0010] Figure 5 This is a partial cross-sectional view of the heat shield mounting assembly taken along the longitudinal centerline of the burner according to this disclosure.

[0011] Figure 6A This is a partial cross-sectional view of the liner mounting assembly taken orthogonally to the longitudinal centerline axis of the burner, according to the present disclosure, showing a plurality of first attachment configurations.

[0012] Figure 6B This is a partial cross-sectional view of the liner mounting assembly taken orthogonally to the longitudinal centerline axis of the burner, according to the present disclosure, showing multiple second attachment configurations.

[0013] Figure 6C is a partial cross-sectional view of a liner mounting assembly taken at section 6C-6C as indicated Figure 6A and Figure 6B is a partial cross-sectional view of a liner mounting assembly taken at section 6D-6D as indicated

[0014] Figure 6D is a partial cross-sectional view of a liner mounting assembly taken at section 6C-6C as indicated Figure 6A and Figure 6B is a partial cross-sectional view of a liner mounting assembly taken at section 6D-6D as indicated

[0015] Figure 6E is a schematic cross-sectional view of a threaded fastener according to the present disclosure.

[0016] Figure 7A is a partial cross-sectional view of a liner mounting assembly taken at section 7B-7B as indicated

[0017] Figure 7B is a partial cross-sectional view of a liner mounting assembly taken at section 7B-7B as indicated Figure 7A

[0018] Figure 8A is a partial cross-sectional view of a liner mounting assembly taken at section 7B-7B as indicated

[0019] Figure 8B is a partial cross-sectional view of a liner mounting assembly taken at section 8B-8B as indicated Figure 8A

[0020] Figure 8C is a partial cross-sectional view of a liner mounting assembly taken at section 8B-8B as indicated DETAILED DESCRIPTION

[0021] The features, advantages, and embodiments of the present disclosure are illustrated or described in or by the accompanying drawings and claims. It is to be understood that the detailed description and specific examples presented are intended to provide further explanation of the disclosure and are not intended to limit the disclosure.

[0022] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is merely for illustration. One of ordinary skill in the related art will recognize that other components and configurations can be used without departing from the present disclosure.

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

[0024] ​​The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0025] The terms "forward" and "rearward" refer to relative positions within a turbine engine or carrier, and to the normal operating posture of the turbine engine or carrier. For example, in the case of a turbine engine, "forward" refers to the position on the turbine engine closer to the propeller or fan, and "rearward" refers to the position on the turbine engine further away from the propeller or fan.

[0026] As used herein, the terms “low” and “high” or their respective comparatives (e.g., “lower” and “higher”, if applicable), when used with compressors, combustors, turbines, shafts, fans, or turbine engine components, refer, unless otherwise specified, to relative pressure, relative speed, relative temperature, or relative power output within the engine. For example, a “low power” setting defines an engine or combustor configured to operate at a power output lower than that of an engine or combustor at a “high power” setting. The terms “low” or “high” in the foregoing terminology may additionally or alternatively be understood as relative to a minimum permissible speed, pressure, or temperature, or relative to the minimum or maximum permissible speed, pressure, or temperature for normal, desired, steady-state, or other operations of the engine.

[0027] Unless otherwise specified herein, the terms “connection,” “fix,” “fasten,” “link,” etc., refer to both direct connection, fixation, fastening, or linking, and indirect connection, fixation, fastening, or linking through one or more intermediate components or features.

[0028] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0029] As used in this article, a “turbocharged engine” includes the compressor section, the combustor, and the turbine section.

[0030] As used herein, "turbofan engine" includes a turbocharged engine and a fan that directs air into the turbocharged engine, and is rated for use in regional, narrow-body, or wide-body aircraft. The maximum takeoff thrust of a turbofan engine rated for a regional aircraft is in the range of 10,000 to 20,000 lbf (10,000 lbf to 20,000 lbf). The maximum takeoff thrust of a turbofan engine rated for a narrow-body aircraft is in the range of 15,000 to 30,000 lbf (15,000 lbf to 30,000 lbf). The maximum takeoff thrust of a turbofan engine rated for a wide-body aircraft is in the range of 40,000 to 110,000 lbf (40,000 lbf to 110,000 lbf).

[0031] As used herein, the term "pipeline engine" refers to a turbofan engine having a fan casing or nacelle circumferentially surrounding the fan.

[0032] As used in this article, "ductless fan engine" or "open fan engine" refers to a turbofan engine that does not have a fan casing or nacelle surrounding the fan.

[0033] From now on, the term "turbofan engine" will refer to either "pipeline engine" or "open fan engine".

[0034] As used throughout this specification and claims, approximate language is used to modify any quantitative or geometric representation that may be varied without altering its underlying function. Therefore, values ​​or geometries modified by one or more terms (e.g., “substantially” and “basically”) are not limited to the specified exact values ​​or exact geometries.

[0035] As used herein, the term "composite material" refers to a material having two or more constituent materials. A composite material can be a combination of at least two or more metals, nonmetals, or metal and nonmetal elements or materials. Examples of composite materials can be, but are not limited to, polymer matrix composites (PMCs), ceramic matrix composites (CMCs), and metal matrix composites (MMCs). Composite materials can be formed from a matrix material and reinforcing elements, such as fibers (referred to herein as reinforcing fibers).

[0036] As used herein, CMC (or ceramic matrix composite) refers to a class of materials having reinforcing fibers within a ceramic matrix. Typically, the reinforcing fibers provide structural integrity to the ceramic matrix. Some examples of reinforcing fibers may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), non-oxide carbon-based materials (e.g., carbon), oxide ceramics (e.g., silicon oxycarbide, silicon oxynitride, alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates (e.g., mullite) or mixtures thereof) or mixtures thereof.

[0037] Examples of ceramic matrix materials may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), oxide ceramics (e.g., silicon oxycarbide, silicon oxynitride, alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, or mixtures thereof), or mixtures thereof. Optionally, ceramic particles (e.g., oxides of Si, Al, Zr, Y, and combinations thereof) and inorganic fillers (e.g., pyrophyllite, wollastonite, mica, talc, kyanite, and montmorillonite) may also be included in the ceramic matrix.

[0038] Generally, a specific CMC can be identified by its combination or fiber / matrix type. For example, C / SiC is used for carbon fiber reinforced silicon carbide, SiC / SiC for silicon carbide fiber reinforced silicon carbide, SiC / SiN for silicon carbide fiber reinforced silicon nitride, and SiC / SiC-SiN for silicon carbide fiber reinforced silicon carbide / silicon nitride matrix mixtures, etc. In other examples, a CMC can consist of a matrix and reinforcing fibers, with the reinforcing fibers including oxide-based materials such as alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, and mixtures thereof. Aluminosilicates can include crystalline materials such as mullite (3Al₂O₃·2SiO₂) and glassy aluminosilicates.

[0039] In some non-limiting examples, reinforcing fibers may be bundled (e.g., forming fiber bundles) and / or coated before being incorporated into the matrix. The fiber bundles may be impregnated with a slurry composition before or after the formation of the preform. The preform may then undergo heat treatment and subsequent chemical processing to obtain a part formed from a CMC material having the desired chemical composition. For example, the preform may undergo curing or burn-out to produce a high carbon residue in the preform, followed by melt infiltration with silicon, or curing or pyrolysis to produce a silicon carbide matrix in the preform, followed by chemical vapor infiltration with silicon carbide. Additional steps may be taken before or after chemical vapor infiltration to enhance the densification of the preform by injecting a liquid resin or polymer into the preform followed by a heat treatment step to fill voids with silicon carbide. The CMC material used herein can be formed using any known or later developed methods, including but not limited to melt infiltration, chemical vapor infiltration, polymer impregnation pyrolysis (PIP), or any combination thereof.

[0040] As used herein, the term "metal" means a material that includes metals, such as, but not limited to, titanium, iron, aluminum, stainless steel, cobalt, and nickel alloys. A metallic material or alloy may be a combination of at least two or more elements or materials, at least one of which is a metal.

[0041] Gas turbine engines typically include a combustor, in which fuel and air are mixed and burned, generating heat. To protect the combustor components from the high temperatures of the combustion gases, insulating members, such as heat shields or liner panels, are placed between the high-temperature combustion gases and sensitive components (e.g., fuel nozzles, mixer assemblies, and structural members, including domes and liner housings). The liner may be segmented and include multiple liner panels. The insulating members define the combustion chamber. The structural members are typically metallic, while in some cases, the insulating members may be formed of CMC material. In some cases, the dome or other structural members may also be formed of CMC material. When connecting the insulating members and structural members together, attachment configurations including fastening components are typically used, and gaps exist between the various components.

[0042] Attachment configurations and fastening assemblies may include metal fasteners, such as bolts. Reducing the functional thickness (e.g., holes, recesses, countersunk holes, etc.) for assembling fastening assemblies can facilitate heat transfer through insulating members, thereby reducing the insulation performance of the insulating members. Furthermore, during operation of a gas turbine engine, metal fasteners provide a conductive path for heat transfer from the combustion chamber to structural members. Including insulating material in the attachment configuration can reduce heat transfer through the attachment configuration. This disclosure provides an attachment configuration without reducing the functional thickness, without metal fasteners within or through the functional thickness of the insulating member, and with insulating material to reduce heat transfer therethrough.

[0043] In burners employing CMC insulation components, although the structural members are metallic, the use of CMC materials with a lower coefficient of thermal expansion than metallic materials can lead to relative movement between the CMC insulation components and the metallic structural members. By implementing an attachment configuration that allows relative movement, internal stresses caused by otherwise constrained thermal growth can be reduced. This disclosure provides an attachment configuration for attaching the burner's insulation components to the burner's structural members using fastening assemblies, allowing relative movement between the insulation components and the structural members.

[0044] In the following description, relative to Figure 1 Turbo engine 10 and Figure 1 and Figure 2 For the combustor 26, the terms "axial" and "axially" refer to the direction and orientation in which it extends substantially parallel to the longitudinal centerline axis 12 of the turbine engine 10. Furthermore, the terms "radial" and "radially" refer to the direction and orientation in which it extends substantially perpendicular to the longitudinal centerline axis 12 of the turbine engine 10. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to the direction and orientation in which it extends in an arc around the longitudinal centerline axis 12 of the turbine engine 10.

[0045] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 10 taken along the longitudinal centerline axis 12 of the turbine engine 10 according to an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 provided as a reference) and a radial direction R orthogonal to the axial direction A. Typically, the turbine engine 10 includes a fan section 14 and a turbocharger engine 16 disposed downstream of the fan section 14.

[0046] The turbocharged engine 16 comprises, in series flow relationship, a compressor section 21, a combustor (also referred to as combustor 26), and a turbine section 27. The turbocharged engine 16 is substantially enclosed within a housing 18, which is substantially tubular and defines an annular inlet 20 about a longitudinal centerline axis 12. Figure 1 As schematically shown, compressor section 21 includes a turbocharger or low-pressure (LP) compressor 22, downstream of which a high-pressure (HP) compressor 24 follows. Combustor 26 is located downstream of compressor section 21. Turbine section 27 is located downstream of combustor 26 and includes a high-pressure (HP) turbine 28, downstream of which a low-pressure (LP) turbine 30 follows. Turbocharged engine 16 also includes an injection nozzle section 32, a high-pressure (HP) shaft 34 or spool, and a low-pressure (LP) shaft 36 located downstream of turbine section 27. HP shaft 34 drivesly connects HP turbine 28 to HP compressor 24. HP turbine 28 and HP compressor 24 rotate synchronously via HP shaft 34. LP shaft 36 drivesly connects LP turbine 30 to LP compressor 22. LP turbine 30 and LP compressor 22 rotate synchronously via LP shaft 36. Compressor section 21, combustor 26, turbine section 27, and injection nozzle section 32 together define the core airflow path.

[0047] for Figure 1 In the illustrated embodiment, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 typically extend outward from disk 42 along the radial direction R. In the case of a variable pitch fan, multiple fan blades 40 are operably coupled to an actuating member 44 by means of the fan blades 40, enabling them to rotate relative to disk 42 about a pitch axis P. The actuating member 44 is configured to collectively and uniformly change the pitch of the fan blades 40. The fan blades 40, disk 42, and actuating member 44 are rotatable together about a longitudinal centerline axis 12 via a fan shaft 45, which is powered by an LP shaft 36 across a power gearbox (also referred to as gearbox assembly 46). Thus, fan 38 is drivenly coupled to and powered by a turbocharged engine 16, and the turbocharged engine 10 is an indirectly driven engine. Gearbox assembly 46 in Figure 1 The diagram is schematically shown. Gearbox assembly 46 is a reduction gearbox assembly used to regulate the rotational speed of fan shaft 45 and fan 38 relative to LP shaft 36 when power is transmitted from LP shaft 36 to fan shaft 45.

[0048] Still referencing Figure 1In an exemplary embodiment, the disk 42 is covered by a fan hub 48 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 40. Furthermore, the fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 38 and the turbocharged engine 16. The nacelle 50 is supported relative to the turbocharged engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced around the nacelle 50 and the turbocharged engine 16. Additionally, a downstream section 54 of the nacelle 50 extends above the outer portion of the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 56 therebetween.

[0049] During operation of the turbine engine 10, a volume of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the fan section 14. As the volume of air 58 passes through the fan blades 40, a first portion of the air (also referred to as bypass air 62) is directed into the bypass airflow passage 56, and a second portion of the air (also referred to as core air 64) is directed into the upstream section of the core air flow path through the annular inlet 20 of the LP compressor 22. The ratio between bypass air 62 and core air 64 is commonly referred to as the bypass ratio. The pressure of the core air 64 is then increased, producing compressed air 65. The compressed air 65 is directed through the HP compressor 24 and into the combustor 26, where it is mixed with fuel and ignited to produce combustion gases 66.

[0050] Combustion gas 66 is directed into and expanded in HP turbine 28, where a portion of the thermal or kinetic energy from combustion gas 66 is extracted via one or more stages of HP turbine stator blades 68 and HP turbine rotor blades 70 connected to HP shaft 34. This causes HP shaft 34 to rotate, supporting the operation of HP compressor 24 (self-sustaining cycle). Thus, combustion gas 66 performs work on HP turbine 28. Combustion gas 66 is then directed into and expanded in LP turbine 30. Here, a second portion of thermal or kinetic energy is extracted from combustion gas 66 via one or more stages of LP turbine stator blades 72 and LP turbine rotor blades 74 connected to LP shaft 36. This causes LP shaft 36 to rotate, supporting the operation of LP compressor 22 (self-sustaining cycle) and supporting the rotation of fan 38 via gearbox assembly 46. Thus, combustion gas 66 performs work on LP turbine 30.

[0051] Combustion gas 66 is then directed through the injector exhaust nozzle section 32 of the turbocharged engine 16 to provide propulsive thrust. Simultaneously, bypass air 62 is directed through bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of the turbocharged engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injector exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through the turbocharged engine 16.

[0052] The turbine engine 10 includes a fuel system that supplies fuel to a combustor 26. Fuel is mixed with compressed air 65 from an HP compressor 24 and ignited in the combustor 26 to produce combustion gases 66. The fuel system may include a fuel tank or fuel supply device for storing fuel therein, a fuel supply line, and a fuel injector. Fuel is supplied from the fuel tank along the fuel supply line to the fuel injector, which introduces fuel into the combustor 26. The fuel system may include one or more flow control devices or valves along the fuel supply line for controlling the amount of fuel supplied to the combustor 26. The fuel injector may be located at the front end of the combustor 26. Therefore, fuel supplied along the fuel supply line is provided at the front end of the combustor 26.

[0053] Figure 1 The turbine engine 10 shown is merely an example. In other exemplary embodiments, the turbine engine 10 can have any suitable configuration. For example, in other exemplary embodiments, the fan 38 can be configured in another suitable manner (e.g., as a fixed-pitch fan), and can also be supported using any other suitable fan frame configuration. The turbine engine 10 can also be a direct-drive engine without a power gearbox. For a direct-drive engine, the fan speed is the same as the LP shaft speed.

[0054] Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In still other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, propeller fan engine, turbojet engine, turboprop engine, or turboshaft engine.

[0055] Figure 2 Is it like this? Figure 1 A cross-sectional side view of the combustor 26 of the turbocharged engine 16 shown. Figure 2As shown, the combustor 26 typically includes a combustor liner 80 and a dome assembly 90. The combustor liner 80 has an inner liner 82 and an outer liner 86. The combustor liner 80 and the dome assembly 90 together define a combustion chamber 102. Both the inner liner 82 and the outer liner 86 can extend circumferentially about a longitudinal centerline axis 134 of the combustor, which may correspond to a turbine engine 10 ( Figure 1 The longitudinal centerline axis 12 of the combustor 26 is defined. The inner liner 82 and outer liner 86 are connected to the cowl 98, and the pressure boosting chamber 110 is defined between the cowl 98, the inner liner 82, the outer liner 86, and the dome assembly 90. The combustor 26 also includes a mixer assembly 94 connected to the fuel nozzle assembly 116, having a mixer assembly axis 95. Although... Figure 2 A single mixer assembly 94 and a single fuel nozzle assembly 116 are depicted, but the burner 26 may include a plurality of mixer assemblies 94 and corresponding fuel nozzle assemblies 116, wherein each corresponding mixer assembly 94 is circumferentially spaced from the fuel nozzle assembly 116 about the longitudinal centerline axis 134 of the burner.

[0056] like Figure 2 As shown, the inner liner 82 is enclosed within the inner housing 108, and the outer liner 86 is enclosed within the outer housing 106. An outer flow passage 130 is defined between the outer liner 86 and the outer housing 106, and an inner flow passage 132 is defined between the inner liner 82 and the inner housing 108. Both the outer housing 106 and the inner housing 108 can extend circumferentially about the longitudinal centerline axis 134 of the burner. The inner liner 82 and the outer liner 86 can extend from the dome assembly 90 to the HP turbine 28 (…). Figure 1 The turbine nozzle 126 at the inlet of the combustor liner 80 at least partially defines the hot gas path between the combustor liner 80 and the HP turbine 28. The combustion chamber 102 may more specifically define a main combustion zone 122 where the initial chemical reaction of the fuel-oxidant mixture 120 occurs to produce combustion gas 66, and / or where the combustion gas 66 further flows downstream within the combustion chamber 102 and between the HP turbine 28 and the LP turbine 30 (…). Figure 1 Before entering the turbine nozzle 126 at the inlet, recirculation of combustion gases 66 can occur. The outer liner 86 can be a multi-layered liner including an outer liner housing 84 and insulating members. The insulating members are outer liner panels 88, which are connected to the outer liner housing 84 via a plurality of outer liner housing-to-panel connecting members 92. Similarly, the inner liner 82 can be a multi-layered liner including an inner liner housing 96 and insulating members, wherein the insulating members are inner liner panels 100, which are connected to the inner liner housing 96 via a plurality of inner liner housing-to-panel connecting members 104.

[0057] like Figure 2As shown, after the LP compressor 22 and HP compressor 24, compressed air 65 flows into the burner 26 and pressurizes the diffuser chamber 128. A first portion of the compressed air 65, schematically indicated by arrow 65(a), flows from the diffuser chamber 128 into the pressure chamber 110, where the air 65(a) is mixed by the mixer assembly 94 with fuel supplied by the fuel nozzle assembly 116. The fuel-oxidizer mixture 120 is then injected by the mixer assembly 94 into the combustion chamber 102. The fuel-oxidizer mixture 120 is ignited and burned by the igniter 124 to produce combustion gases 66 within the main combustion zone 122 of the combustion chamber 102. Typically, the LP compressor 22 ( Figure 1 ) and HP compressor 24 ( Figure 1 More compressed air 65 than is required for combustion is supplied to the diffuser cavity 128. Therefore, the second portion of the compressed air 65, schematically indicated by arrow 65(b), can be used for various purposes other than combustion. For example, as... Figure 2 As shown, a portion of the air 65(b) can be directed into the outer flow passage 130, and another portion of the compressed air 65(b) can be directed into the inner flow passage 132. Furthermore, or alternatively, at least a portion of the compressed air 65(b) can be discharged from the diffuser cavity 128 for other purposes, such as to the HP turbine 28 (…). Figure 1 ) or LP Turbo 30 ( Figure 1 At least one of them provides cooling air.

[0058] Return to common reference Figure 1 and Figure 2 The combustion gases 66 generated in the combustion chamber 102 flow through the turbine nozzle 126 and enter the HP turbine 28, thereby rotating the HP shaft 34 and supporting the operation of the HP compressor 24. Figure 1 As shown, the combustion gas 66 is then directed through the LP turbine 30, thereby rotating the LP shaft 36 to support the operation of the LP compressor 22 and / or the rotation of the fan shaft 45. The combustion gas 66 is then discharged through the injection exhaust nozzle section 32 of the turbocharged engine 16 to provide propulsion at the downstream end.

[0059] Refer again Figure 2Furthermore, as will be described in more detail below, the dome assembly 90 includes a dome 112 and a heat shield 114 connected to the dome 112 via one or more dome heat shield connectors 118. During combustion of the fuel-oxidizer mixture 120, heat is generated. This heat is greatest at the upstream end of the combustion chamber 102, close to the mixer assembly 94 and the fuel nozzle assembly 116. The heat shield 114 is an insulating member connected to the dome 112 to thermally protect the mixer assembly 94, the fuel nozzle assembly 116, the dome assembly 90, and other adjacent components from the heat and high temperatures of the combustion gases 66 in the combustion chamber 102. The heat shield 114 may be made of a ceramic matrix composite (CMC) material or any other suitable thermal insulation material to inhibit heat transfer from the high-temperature areas of the combustion chamber 102 to other components of the burner 26. The one or more dome heat shield connectors 118 may be metallic and therefore have much better thermal conductivity than the heat shield 114. Using this metal dome heat shield connector 118 provides a potential path for heat transfer outside the heat shield 114, reaching the dome assembly 90, and approaching the mixer assembly 94 and the fuel nozzle assembly 116.

[0060] Mixer assembly 94 redirects a portion of air 65(a) through itself, in front of heat shield 114, and ultimately into combustion chamber 102. This portion of air 65(a) does not mix with fuel to form fuel-oxidant mixture 120, but instead flows through gap 115 between heat shield 114 and dome 112 and into combustion chamber 102, conductively transferring heat from gap 115 to combustion chamber 102, thereby further reducing heat transfer to dome 112.

[0061] In the following description, relative to Figures 3A to 8C For various liner mounting components, the terms "axial" and "axially" refer to the direction and orientation extending substantially parallel to the longitudinal centerline axis 134 of the burner. Furthermore, the terms "radial" and "radially" refer to the direction and orientation extending substantially perpendicular to the longitudinal centerline axis 134 of the burner. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to the direction and orientation extending in an arc around the longitudinal centerline axis 134 of the burner.

[0062] Figures 3A to 8C Exemplary liner mounting assemblies 300, 400, 500, 600, 700, and 800 are described. Liner mounting assemblies 300, 400, 500, 600, 700, and 800 can attach liner panels 302, 402, 502, 602, 702, and 802 to housings 304, 404, 504, and 604, also referred to herein as liner housings. The description of liner mounting assemblies 300, 400, 500, 600, 700, and 800 can alternatively be applied to burner 26 (…).Figure 2 In other places, such as as a dome heat shield mounting assembly. In these embodiments, the following description of the lining panels 302, 402, 502, 602, 702 and 802 can be applied to the heat shield (e.g., Figure 2 The following descriptions of the housing materials 304, 404, 504, and 604 can also be applied to domes (e.g., heat shield 114), and housing materials 304, 404, 504, and 604. Figure 2 (Dome 112). Therefore, in the following description, lining panels 302, 402, 502, 602, 702, and 802 are also referred to as insulating members, and housings 304, 404, 504, and 604 are also referred to as structural members. In the example of the dome insulation cover mounting assembly, the insulating member is the insulation cover, and the structural member is the dome.

[0063] Figure 3A A partial schematic cross-sectional view of a liner mounting assembly 300 for attaching a liner panel 302 to a housing 304 is shown, the liner mounting assembly 300 having a minimum path for heat transfer from the combustion chamber 102 to the housing 304. The liner panel 302 is attached to the housing 304 via one or more first attachment configurations or dovetail joints 306 that constrain the liner panel 302 in three dimensions relative to the housing 304. Each dovetail joint 306 includes a tail 308 projecting from the outer surface 310 of the liner panel 302 and a pin 312 projecting from the housing 304. Rotational constraint relative to the burner longitudinal centerline axis 134 is achieved by using a rigid mechanical stop (not shown) that prevents the tail 308 from rotating about the burner longitudinal centerline axis 134 beyond a specified tolerable rotation angle. The dovetail joints 306 provide radial travel limitation for the liner panel 302 relative to the housing 304. The dovetail joint 306 is an attachment configuration and also includes a seal 314. The seal 314 may be an O-ring, spline seal, or other suitable component of this type, and provides compressibility between the tail 308 and pin 312 of the dovetail joint 306. The seal 314 is mechanically compliant because it is slightly compressible, allowing it to absorb any gaps or play between the tail 308 and pin 312 in the assembled state. Furthermore, the compressibility of the seal 314 allows relative movement of the liner panel 302 relative to the housing 304, the relative movement being due to the turbine engine 10 (… Figure 1 Vibration during operation, thermal expansion due to the difference between the lining panel 302 and the housing 304, or manipulation during the assembly of the lining mounting assembly 300.

[0064] In the illustrated embodiment, the tail portion 308 is integrated with and extends from the lining panel 302. The pin 312 is integrated with and extends from the housing 304. An equivalent configuration includes the tail portion 308 integrated with and extending from the housing 304, and the pin 312 integrated with and extending from the lining panel 302.

[0065] The liner mounting assembly 300 also includes a second attachment configuration. The second attachment configuration includes a ball plate assembly 316. The ball plate assembly 316 includes a plate member 318 and a plurality of spherical ceramic balls 320 for radially constraining the liner panel 302 relative to the housing 304. To allow for flexibility in assembly and operation, the plate member may be constructed of a metallic material, preferably spring steel. Each of the plurality of spherical ceramic balls 320 is assembled within one of a plurality of spherical cavities 322 arranged in the plate member 318. The plate member 318 generally has a Z-shaped cross-section, including a first portion 324 at one end relative to the longitudinal centerline axis 134 of the burner, a second portion 326 at the opposite end, and a transition portion 328 therebetween. The second portion 326 of the plate member 318 includes a plurality of mounting holes 332, each for assembling the ball plate assembly 316 to the housing 304 in one of a plurality of fastening assemblies 330, while in the first portion 324 the spherical ceramic balls 320 contact the liner panel 302.

[0066] Each fastening assembly 330 assembles the ball plate assembly 316 to the housing 304 and includes a bolt 334 and a nut 336 in a compression bolt assembly configuration. Each fastening assembly 330 holds the ball plate assembly 316 relative to the housing 304 in both the radial and axial directions relative to the longitudinal centerline axis 134 of the burner. The fastening assembly 330 holds the ball plate assembly 316 in the rotational direction relative to the longitudinal centerline axis 134 of the burner. In summary, the fastening assembly 330 secures the ball plate assembly 316 relative to the housing 304. Alternatively, the ball plate assembly 316 can be assembled to the housing 304 by one or more rivets, screws, or other fasteners, or can be engaged by welding, bonding, metal forming, or any other suitable method required for functional or manufacturing considerations, or any combination of fasteners and / or engagement methods.

[0067] Figure 3B This is a schematic diagram of the ball plate assembly 316 according to this disclosure. Figure 3B As shown, the plate assembly 316 includes two mounting holes 332. The plate assembly 316 may alternatively include more or fewer than two mounting holes, and therefore the liner mounting assembly 300 ( Figure 3A ) may include more or fewer than two dovetail joints 306 ( Figure 3BThe mounting holes 332 and fastening components 330 can be arranged in any determinable manner to optimize or improve the assembly of the ball plate assembly 316 to the liner panel 302. Figure 3A This can improve the maintenance of the lining mounting assembly 300 or reduce costs.

[0068] To maintain the integrity of the dovetail joint 306 and prevent damage to the following components: Figure 3A Excessive stress on the components of the liner panel 302, housing 304, tail 308, and pin 312 must be maintained to compress the assembly, even though operational events may cause relative motion and cyclic stress. Such operational events include bending, vibration, fretting, etc., of one or more individual components or the liner mounting assembly 300. That is, under all operating conditions, the tail 308 must maintain tight contact between the tail 308 and pin 312 or through the seal 314 (…). Figure 3A A radial force acting inward is provided on the pin 312. To maintain the radial force applied to the pin 312 by the tail 308, the ball plate assembly 316 provides radial force on the outer surface 310 of the plurality of spherical ceramic balls 320 and the lining panel 302. Figure 3A The interface between the two surfaces exerts an inward force on the liner panel 302. Despite relative radial movement, deformation, or vibration relative to the burner longitudinal centerline axis 134, due to the flexibility of the ball plate assembly 316, and more specifically, due to the flexibility of the plate member 318, relative to the burner longitudinal centerline axis 134 (… Figure 3A The inward force is maintained. In the free state, the radial dimension of the ball plate assembly 316 from the second part 326 to the spherical ceramic ball 320 is x. 3,1 Assembling the ball plate assembly 316 into the liner mounting assembly 300 requires bending the plate member 318 to reduce the radial dimension to x. 3,2 Smaller than radial dimension x 3,1 And is defined by the radial distance between the inner surface 342 of the housing 304 and the outer surface 310 of the lining panel 302. Due to the bending of the plate member 318, the ball plate assembly acts as a spring, applying an inward force on the outer surface 310 of the lining panel 302 at the fastening assembly 330 and an outward force on the inner surface 342 of the housing 304. Therefore, the tail 308 applies an outward force on the pin 312 and the seal 314. The bending of the plate member 318 is maintained because the radial dimension x 3,1 and x 3,2 The magnitude of the difference is greater than the magnitude of any relative movement or relative deformation of the components of the liner housing assembly.

[0069] Because the function of the lining panel 302 is in the combustion chamber 102 ( Figure 2 High-temperature combustion and burner 26 (in) Figure 2The liner panel 302 provides insulation between the combustion chamber 102 and the other components of the burner 26, thus providing continuous insulation. The amount of insulation provided by the liner panel 302 is related to the functional thickness t of the liner panel 302. L Proportional. Functional thickness t L It is the thickness of the lining panel 302 in the generally radial direction or in the direction in which the lining panel 302 inhibits heat transfer. The configuration of the lining mounting assembly 300 allows the functional thickness t to be maintained throughout the process. L And without gaps or functional thickness t L The reduction in heat transfer maintains the thermal insulation performance of the liner panel 302. Furthermore, the configuration of the liner mounting assembly allows for assembly of the liner panel 302 to the housing 304 without any heat-conducting elements (e.g., metal fasteners) penetrating the liner panel 302. This penetration would allow a certain amount of heat to be transferred from the combustion chamber 102 to the burner 26 via the fasteners.

[0070] When present, a portion of the air 65(a) flowing through the gap 340 between the liner panel 302 and the housing 304 convectively transfers heat from the outer surface 310 of the liner panel 302. This is in contrast to other equivalent burners 26 (where this portion of air 65(a) does not flow). Figure 2 In contrast, the flow of air in this part of 65(a) maintains a lower temperature in the gap 340.

[0071] The temperature of the outer surface 310 of the liner panel 302 is higher than the temperature of the housing 304. To minimize conductive heat transfer from the liner panel 302 to the housing 304, the spherical ceramic balls 320 are made of a thermally insulating ceramic material. All spherical ceramic balls 320 are in substantially point contact with the liner panel 302, thereby minimizing the heat transfer path from the liner panel 302 to the housing 304. Exemplary materials for other components of the liner mounting assembly 300, such as the plate member 318, the housing 304, and the bolts 334, include many relatively conductive materials, such as metals. The addition of insulators (e.g., the plurality of spherical ceramic balls 320) provides a barrier to the conductive path of heat transfer that would otherwise exist between the outer surface 310 of the liner panel 302 and the housing 304.

[0072] Returning to the dovetail joint 306, a gap 344 is maintained between the outer surface 310 of the liner panel 302 and the pin 312 by means of a radially inward biasing force applied to the liner panel 302 by the ball plate assembly 316, and a gap 345 is maintained between the tail 308 and the pin 312. The gap 344 allows a portion of the air 65(a) to flow between the pin 312 and the outer surface 310, thereby minimizing heat transfer through the gap 344. The seal 314 may be made of an insulating material (e.g., rubber), a composite material, or any other suitable material, as discussed, to provide mechanical compliance in the dovetail joint 306 while reducing conductive heat transfer from the tail 308 to the pin 312. Contact exists between the tail 308 and the pin 312. However, this contact is limited by the functional thickness t of the liner panel 302. L The radial outer side is within the flow path of a portion of the air 65(a) flowing through the gap 340. A portion of the air 65(a) convectively transfers heat from the tail 308 and pin 312 through the flow of the gap 340, lowering the temperature of both and reducing heat transfer in the dovetail joint 306 from the tail 308 of the lining panel 302 to the pin 312 of the housing 304.

[0073] Figure 3A A single ball plate assembly is shown. However, the liner mounting assembly 300 may comprise multiple ball plate assemblies 316. These multiple ball plate assemblies 316 may be arranged in a circle about the longitudinal centerline axis 134 of the burner to provide symmetrical net force on the liner panel 302. Such multiple ball plate assemblies 316 may consist of two, four, or any other number of ball plate assemblies to provide the desired net force or as an aid to assembly. Similarly, as... Figure 3B The ball plate assembly 316 shown is typically rectangular in a two-dimensional planar view viewed radially relative to the longitudinal centerline axis 134 of the burner. To aid in force balancing or assembly, the ball plate assembly can be any other simple or complex two-dimensional planar shape, including arcuate, circular, or annular, or it can have a rectangular shape but with the same... Figure 3B The ball plate assembly 316 shown has different lengths, widths, or aspect ratios.

[0074] In addition, such as Figure 3BThe ball plate assembly 316 shown and applied to the liner mounting assembly 300 has a rectangular array of thirteen spherical ceramic balls 320, arranged in alternating three rows and two rows. The spherical ceramic balls 320 can be of any size and can be equal or unequal in size to each other. Multiple spherical ceramic balls 320 may comprise more or fewer than thirteen individual spherical ceramic balls 320 arranged in any useful array. Such configurations or reconfigurations can be made to optimize one or more considerations regarding performance, cost, manufacturability, or maintenance. Considerations include the force of the ball plate assembly 316 on the liner panel 302, the convective heat transfer of a portion of the air 65(a) through the gap 340, the conductive heat transfer through the spherical ceramic balls 320, the manufacture or assembly of the liner mounting assembly 300 or its components, and the maintenance or cost of the liner housing assembly.

[0075] Figure 4A and Figure 4B Partial schematic cross-sectional views are shown of the liner mounting assembly 400 and the ball bearing assembly for attaching the liner panel 402 to the housing 404, respectively. The liner mounting assembly 400 has a minimum path for heat transfer from the combustion chamber 102 to the housing 404. The liner mounting assembly 400 and the ball bearing assembly are functionally related to, as described above... Figure 3A and Figure 3B The liner mounting assembly 300 and the plate assembly 316 are substantially similar, but have one or more fastening assemblies 430 with different configurations, including one or more dovetail joints 406 and plate assemblies 416 with different configurations. The descriptive elements of the liner mounting assembly 300 also apply to the liner mounting assembly 400, and therefore, only the differences between the two are described. Similarly, the elements of the plate assembly 316 also apply to the plate assembly 416, and therefore, only the differences between the two are described. The remaining descriptions of the liner mounting assembly 300 and the plate assembly 316 also apply to this embodiment, and further detailed descriptions are omitted here.

[0076] The lining panel 402 is attached to the housing 404 via a fastening assembly 430 including a dovetail joint 406. The first attachment configuration is the dovetail joint 406, which constrains the lining panel 402 in three dimensions relative to the housing 404. The dovetail joint 406 includes a tail 408 projecting from the outer surface 410 of the heat shield and a pin end 412 of a threaded fastener 434. The dovetail joint 406 also includes a seal 414 assembled to the tail 408 at the dovetail interface between the tail 408 and the pin end 412.

[0077] Now for joint reference Figure 4A and Figure 4BThe liner mounting assembly 400 also includes a second attachment configuration in the form of a ball plate assembly 416 for constraining the liner panel 402 radially relative to the housing 404. The ball plate assembly 416 includes a plate member 418 and a plurality of spherical ceramic balls 420, each spherical ceramic ball being assembled within one of a plurality of spherical cavities 422 arranged in the plate member 418.

[0078] The plate member 418 includes a first portion 424, a second portion 426, and a transition portion 428 therebetween. The plate member additionally includes an arcuate portion 429 at one end outside the first portion 424 relative to the longitudinal centerline axis 134 of the burner. A plurality of mounting holes 432 are provided for assembling the ball plate assembly 416 to the housing 404 using one or more fastening assemblies 430.

[0079] As shown in the figure, a threaded fastener 434 applied to the dovetail joint 406 is additionally used to secure the ball plate assembly 416 to the housing 404 at the fastening assembly 430, thereby reducing the overall complexity of the liner mounting assembly 400 relative to the liner mounting assembly 300. A nut 436 is screwed onto the threaded fastener 434. The pin end 412 and the nut 436 secure the plate member 418 and the housing 404 between them. Figure 4A As shown, the pin end 412 is integrated with the threaded fastener 434 of the fastening assembly 430. Relative to Figure 3A In the housing 304 of the liner mounting assembly 300, the pin 312 is excluded from the housing 404, and instead the pin end 412 of the threaded fastener 434 is used, resulting in a simpler-shaped housing 404. This, in turn, can lead to simpler or lower-cost manufacturing, assembly, or maintenance. Furthermore, integrating the pin end 412 into the threaded fastener 434 allows for the use of more robust materials compared to integrating the pin 312 into the housing 304.

[0080] The ball plate assembly 416 has a free radial dimension x between the second part 426 and the plurality of spherical ceramic balls 420. 4,1 When the ball plate assembly 416 is assembled into the liner mounting assembly 400, the radial dimension is reduced to x. 4,1 This radial compression causes bending or flexing behavior in the plate member 418. The reaction force from the bending of the plate member 418 causes the ball plate assembly to exert a radially inward force on the outer surface 410 of the heat shield at the spherical ceramic ball 420. Furthermore, the bending of the plate member 418 causes the ball plate assembly 416 to contact the inner surface 342 of the housing 404 at the second portion 426 and the arcuate portion 429 and exert a radially outward force thereon.

[0081] When assembled in the liner mounting assembly 400, the radial inward force of the ball plate assembly 416 on the liner panel 402 ensures that a radial inward force is applied to the pin end 412 by the tail 408 through the seal 414. Therefore, the seal 414 is mechanically compliant and capable of absorbing at least a portion of any relative deflection or vibration between the tail 408 and the pin end 412.

[0082] Heat transfer between the liner panel 402 and the housing 404 is mitigated by maintaining a gap between the liner panel 402 and the housing 404, and by including insulating components in the pre-existing conductive path of the liner mounting assembly 400. Examples of insulating components that provide a barrier in the pre-existing conductive path of the liner mounting assembly 400 include spherical ceramic balls 420 and seals 414 mounted between the liner panel 402 and the housing 404.

[0083] By allowing a portion of the air 65(a) to flow through the gap 440 between the lining panel 402 and the housing 404, heat transfer from the outer surface 410 of the lining panel 402 to the housing 404 is partially mitigated; this portion of the air 65(a) convectively transfers heat from the outer surface 410. The radial inward bias of the lining panel 402 and the tail 408, imposed by the bending of the plate member 418 during assembly, maintains both the gap 444 between the outer surface 410 of the lining panel 402 and the pin end 412, and the gap 445 between the tail 408 and the pin end 412. Since the threaded fastener can be made of a conductive material (e.g., metal), the gap 444 maintained between the pin end 412 and the outer surface 410 of the lining panel 402 prevents direct conductive heat transfer from the outer surface 410 of the lining panel 402 to the threaded fastener 434 and subsequently to the housing 404. A seal 414 positioned between the lining panel 402 and the pin end 412 reduces conductive heat transfer between the tail 408 and the threaded fastener 434 by offsetting the contact between the tail 408 and the pin end 412 and maintaining a gap 445, thereby preventing direct conductive heat transfer between the tail 408 and the pin end 412. Furthermore, the gap 445 between the tail 408 and the pin end 412 allows air 65(b) to flow through the gap 440, additionally flowing through and between the tail 408 and the pin end 412, thereby convectively transferring heat away from the tail 408.

[0084] In the illustrated embodiment, the tail portion 408 is integrated with and extends from the lining panel 402. The pin end 412 is integrated with the threaded fastener 434. An equivalent configuration includes the tail portion 408 integrated with the threaded fastener 434 and the pin end 412 integrated with and extending from the lining panel 402.

[0085] Figure 5A partial schematic cross-sectional view of the liner mounting assembly 500 is shown, which has information regarding... Figure 3A and Figure 3B The features and related information of the lining installation component 300 are discussed. Figure 4A and Figure 4B The liner mounting assembly 400 discusses a combination of features. For example, the liner mounting assembly 500 has a first fastening assembly 530, configured similarly to the fastening assembly 330 of the liner mounting assembly 300, for the purpose of assembling the ball plate assembly 516 to the housing 504. The ball plate assembly includes a plate member 518, which, when assembled in the liner mounting assembly 500, is shaped relative to its free state to apply a radially inward force on the liner panel 502. Furthermore, a second fastening assembly 531, having an integrated dovetail joint 506, configured similarly to the fastening assembly 430, assembles the liner panel 502 to the housing 504. The first attachment configuration includes the dovetail joint 506.

[0086] The configuration of the liner mounting assembly 500 allows for design flexibility relative to the liner mounting assemblies 300 and 400. For example... Figure 5 As shown, the presence of two separate components allows the second fastening assembly 531 to be located at a remote position relative to the first fastening assembly 530, if such positioning is advantageous for the manufacture, assembly, maintenance, or cost of a single component or the entire liner mounting assembly 500. For example, the liner mounting assembly 500 allows for the removal and replacement of the liner panel 502 without requiring the removal of the ball plate assembly 516 from the liner mounting assembly 500.

[0087] Now for reference Figure 6A The schematic cross-sectional view shown, taken longitudinally at the rear end of the burner, indicates that the liner mounting assembly 600 includes a liner panel 602 assembled to a housing 604, circumferentially arranged about the burner's longitudinal centerline axis 134. The liner panel 602 is assembled to the housing 604 at a plurality of fastening assemblies 606. The fastening assemblies 606 are a first attachment configuration arranged circumferentially about the burner's longitudinal centerline axis 134, constraining the liner panel 602 relative to the housing 604 in all dimensions.

[0088] Figure 6B A partial schematic cross-sectional view of the liner mounting assembly 600, viewed longitudinally relative to the longitudinal centerline axis 134 of the burner, is shown at the front end of the burner. The assembly includes a plurality of liner panels 602, a housing 604, and a plurality of fastening assemblies 614 for securing the liner panels 602 to the housing 604. The fastening assemblies 614 are a second attachment configuration arranged circumferentially about the longitudinal centerline axis 134 of the burner, for constraining the liner panels 602 radially relative to the housing 604.

[0089] Figure 6CIt shows in Figure 6A and Figure 6B The diagram shows a partial schematic cross-sectional view of the liner mounting assembly 600 taken at section 6C-6C, viewed in the circumferential direction. Figure 6D It shows in Figure 6A and Figure 6B The diagram shows a partial cross-sectional view of the lining mounting assembly 600 taken at section 6D-6D in the circumferential direction.

[0090] Common Reference Figures 6A to 6D Each of the plurality of liner panels 602 is secured to the housing 604 at its rear end by a fastening assembly 606, which holds the liner panel 602 radially, rotatably, and axially. Each of the plurality of liner panels 602 is radially constrained by a spline ring 616 and kept concentrically aligned with the spline ring 616. The spline ring 616 is in turn radially constrained by a fastening assembly 614 and kept concentrically aligned with the housing 604. The spline ring 616 allows the liner panels 602 to undergo thermal growth and / or local relative movement with respect to the housing 604 in the rotational and axial directions relative to the longitudinal centerline axis 134 of the burner, while maintaining the alignment of the liner panels 602 with the housing 604. This degree of freedom is necessary at the front end of the burner 26, closest to the highest hot zone of the mixer assembly 94 and the combustion chamber 102, to compensate for the thermal growth of the liner panels 602 and the movement or vibration caused by the operation of the turbine engine 10.

[0091] The thermal insulation provided by the lining panel 602 and the functional thickness t of the lining panel 602 L Proportional. Functional thickness t L It is the thickness of the lining panel 602 in the generally radial direction or in the direction in which the lining panel 602 inhibits heat transfer. The configuration of the lining mounting assembly 600 allows the functional thickness t to be maintained throughout the process. L And without gaps or functional thickness t L The reduction in [something] thus maintains the thermal insulation performance of the lining panel 602.

[0092] Fastening assembly 606 includes a threaded fastener 608 having a threaded end 612 and a saddle end 610. The threaded end 612 of the threaded fastener 608 is assembled through a mounting hole in the housing 604 and held by a nut 636. The saddle end 610 of the threaded fastener 608 includes a front tab 618 and a rear tab 620 positioned in front of and behind a block feature 622 of the liner panel 602, respectively, jointly constraining the liner panel 602 in the forward and rearward directions.

[0093] To constrain the rotational and radial movement of block feature 622 relative to threaded fastener 608, and thus constrain the rotational and radial movement of lining panel 602 relative to housing 604, a pin-connected joint 624 is assembled via axially aligned holes in front tab 618, rear tab 620, and block feature 622. An annular metal insert 626 is press-fitted into block feature 622. Insert 626 is sized to have an interference fit in block feature 622, such that insert 626 is fixed relative to block feature 622. Pin 628 passes through holes in front tab 618 and rear tab 620 and is assembled through insert 626. Pin 628 is sized to have an interference fit with holes in front tab 618 and rear tab 620, but the fit between pin 628 and insert 626 allows relative rotation between pin 628 and insert 626, referred to as a sliding fit or clearance fit. The material of block feature 622 can be the same as that of lining panel 602, and therefore, block feature 622 can be a relatively brittle material compared to pin 628. Insert 626 is metallic and softer than pin 628 to provide a suitable interface with pin 628 and to withstand relative movement of pin 628, preventing excessive bending or torsional stress in block feature 622 or lining panel 602. Due to the relative movement between insert 626 and pin 628, insert 626 is designed to wear relative to pin 628 and can be replaced when wear exceeds a defined wear threshold. Worn insert 626 is removed by pressing it out and replaced by pressing in a new insert 626.

[0094] In burner 26 ( Figure 2 At the front end of the burner, a fastening assembly 614 secures a splined ring 616. The splined ring 616, in turn, radially positions a plurality of liner panels 602 relative to the longitudinal centerline axis 134 of the burner. Each fastening assembly 614 includes a threaded fastener 630 having a threaded end 632 and a head 634, which is assembled through the housing 604 and fastened with a nut 636. The plurality of fastening assemblies 614 are arranged in a circular array about the longitudinal centerline axis 134 of the burner. When assembled into the fastening assembly 614, the head 634 has transverse holes 638 arranged generally in the circumferential direction. The splined ring 616 is assembled through the transverse holes 638 in each head 634 of each of the threaded fasteners 630 of each of the plurality of fastening assemblies 614, such that the splined ring 616 is supported at regular intervals around the circumference of the plurality of liner panels 602.

[0095] To assemble the spline ring 616 and the threaded fastener 630, the spline ring 616 can be separated, allowing one end of the spline ring 616 to pass through the transverse hole 638 in each threaded fastener 630.

[0096] like Figure 6EAs shown, the threaded fastener 631 can be configured to have a hole 639 and a slot 641. Specifically, the slot 641 of the threaded fastener 631 allows the spline ring 616 to be continuous. The spline ring 616 can be assembled to the threaded fastener 631 by passing the spline ring 616 laterally through the slot 641 of each threaded fastener 631.

[0097] The lining panel 602 at least partially defines the combustion chamber 102 and is exposed to the heat generated by combustion. The outer casing 604 is made of air 65(b)( Figure 2 Part of the flow cooling. This arrangement results in a significant temperature difference between the liner panel 602 and the housing 604. If the liner mounting assembly 600 does not allow for thermal expansion, this temperature difference and its variability can cause significant internal stresses on various components. Furthermore, the liner panel 602 and the housing 604 may be constructed of materials with different thermal expansion characteristics, which may cause relative deformation or relative movement between them, and if fully constrained relative to each other, stresses may also be generated. Over time and through cycling, these stresses may lead to degradation, wear, or failure. The spline ring 616 includes alternating peak segments 642 and valley segments 644. In the free state, the peak segments 642 define the free-state large diameter of the spline ring 616, and in the free state, the valley segments 644 define the free-state small diameter of the spline ring 616.

[0098] The spline ring 616 makes substantially point contact with the lining panel 602 at the valley segment 644 and is assembled through the transverse hole 638 at the peak segment 642. The point contact between the lining panel 602 and the spline ring 616 allows for relative sliding contact between them. This relative sliding contact, in turn, allows for axial and rotational freedom of movement between the lining panel 602 and the housing 604. The flexibility of the spline ring 616 allows for diametrical freedom of expansion and contraction of the lining panel 602 and the housing 604 relative to each other. These degrees of freedom of movement, as provided by the spline ring 616, allow for relative movement, deformation, displacement, and thermal growth of the lining panel 602 and the housing 604 relative to each other.

[0099] The large diameter of the spline ring 616, as defined by peak segment 642, and the small diameter of the spline ring 616, as defined by valley segment 644, are determined as needed to define the required radial space between the liner panel 602 and the housing 604. In the assembled state, peak segment 642 is slightly radially compressed, defining an assembled large diameter smaller than the free large diameter, and valley segment 644 is radially outwardly expanded, defining an assembled small diameter larger than the free small diameter. These deformations allow the spline ring 616 to maintain at least a slight radially inward force on the liner panel 602 under all operating conditions. The spline ring 616 is made of a flexible material, preferably spring steel, capable of withstanding the movement, deformation, and thermal expansion and contraction of the liner panel 602 relative to the housing 604, while still maintaining the radial force on the liner panel 602 to radially position the liner panel 602 relative to the longitudinal centerline axis 134 of the burner.

[0100] At the front end, such as Figures 6B to 6D As shown, a surface coating 640, such as diamond-like carbon (DLC), is applied to the radially outer surfaces of a plurality of liner panels 602. The surface coating 640 provides a functional surface for contact with the spline ring 616, which is more suitable for resisting wear from relative movement and vibration of the spline ring 616 relative to the liner panel 602 compared to the originally exposed surface of the liner panel 602. The surface coating 640 can be applied by vapor deposition, more specifically by chemical vapor deposition (CVD), and even more specifically by plasma-enhanced chemical vapor deposition (PE-CVD).

[0101] In addition, the surface coating 640 acts as a thermal insulator, providing resistance to conductive heat transfer between the lining panel 602 and the housing 604 via the spline ring 616.

[0102] Surface coating 640 is applied circumferentially at least near each contact point between the plurality of liner panels 602 and spline ring 616. Surface coating 640 may be circumferentially discontinuous or circumferentially continuous. If surface coating 640 is circumferentially discontinuous, the segments of surface coating span at least a sufficiently large circumferential span to remain within the interface between liner panels 602 and spline ring 616 during relative rotation between liner panels 602 and housing 604 caused by varying thermal expansion or other operational events of the various components (including at least liner panels 602, housing 604, and spline ring 616). Alternatively, surface coating 640 may be applied along the entire circumferential span of the corresponding liner panel 602 for the purpose of simplifying or reducing manufacturing or assembly costs.

[0103] The surface coating 640 is applied axially at the location of the spline ring 616. Taking into account any movement of the lining panel 602 relative to the housing 604, and consequently relative to the spline ring 616, caused by different thermal expansions or other operational events of the various components (including at least the lining panel 602, the housing 604, and the spline ring 616), the location and axial span of the surface coating 640 are at least long enough to remain within the interface between the spline ring 616 and the lining panel 602.

[0104] Figure 7A A partial schematic cross-sectional view of the liner mounting assembly 700, taken orthogonal to the longitudinal centerline axis 134 of the burner and viewed longitudinally, is shown. Figure 7B It shows that in such Figure 7A The diagram shows a partial schematic cross-sectional view of the liner mounting assembly 700, taken at section 7B-7B and viewed circumferentially. The liner mounting assembly 700 is related to... Figures 6A to 6D The described liner mounting assembly 600 is substantially similar, except for the fastening assembly 706 as described below. Therefore, components of the liner mounting assembly 700 that are identical or similar to those of the liner mounting assembly 600 discussed above will use the same reference numerals. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0105] Now refer to the longitudinal view at the rear end of the burner. Figure 7A The liner mounting assembly 700 includes one or more liner panels 702 (one shown) arranged circumferentially and assembled to the housing 604. The plurality of liner panels 702 are assembled to the housing 604 at a first attachment configuration (also referred to as fastening assembly 706).

[0106] For reference again Figure 7A and Figure 7B This diagram illustrates a fastening assembly 706 for attaching a liner panel 702 to a housing 604. The fastening assembly 706 restrains the relative axial, radial, or rotational displacement of the liner panel 702 relative to the housing 604. The fastening assembly 706 includes a threaded fastener 708 having a head 710 and a threaded end 712. At the threaded end 712, the threaded fastener 708 is attached to the housing 604 by attaching a nut 636 to the threaded end 712. At the end opposite the threaded end 712, the head 710 is assembled to the liner panel 702 at a slotted receiver 722. Figure 7B As shown, the head 710 and the slotted receiver 722 typically have corresponding tapered shapes. This tapered geometry helps to precisely position the lining panel 702 axially relative to the housing 604.

[0107] Furthermore, one or more seals 724 may be installed in the fastening assembly 706, located between the head 710 and the slotted receiver 722. Seal 724 is functionally similar to seal 314. Figure 3A ) and seal 414 ( Figure 4A The seal 724 is slightly compressible, allowing the seal 724 to absorb any gaps or play between the head 710 and the slotted receiver 722, and permitting a degree of radial, axial, rotational, or thermal growth of the liner panel 702 relative to the housing 604. Furthermore, the seal 724 can help insulate the housing 604 from the heat of the liner panel 702. Firstly, the seal 724 can be air 65(a)( Figure 2 A portion of the flow provides a gap, allowing it to flow between the head 710 and the slotted receiver 722, and convectively transferring heat from the liner panel 702 to the combustion chamber 102. Secondly, the seal 724 may be made of a thermally insulating material, thereby providing an insulator in the conductive path of the fastening assembly 706 from the liner panel 702 to the housing 604 via the threaded fastener 708.

[0108] Finally, in fastening assembly 706, a Belleville washer 726 is installed on the threaded fastener 708 between the housing 604 and the slotted receiver 722 radially. The Belleville washer 726 acts as a spring in the radial direction, further allowing for a small radial deflection or diametrical thermal growth of the liner panel 702 relative to the housing 604. By acting on the liner panel 702 in the radial direction, the Belleville washer 726 functions in a similar manner to the seal 724. However, the seal 724 also acts on the liner panel 702 in the axial direction.

[0109] Figure 8A A partial schematic cross-section of the liner mounting assembly 800, taken at the rear of the burner 26 in a longitudinal view, is shown. Figure 8B It shows that in such Figure 8A The diagram shows a partial schematic cross-sectional view taken at section 8B-8B. Liner mounting assembly 800 and related... Figure 7A and Figure 7B The described liner mounting assembly 700 is substantially similar, except for a first attachment configuration in the form of fastening assembly 806, which includes a spline ring 816, as described below. Therefore, components of the liner mounting assembly 800 that are identical or similar to those of the liner mounting assembly 700 discussed above will use the same reference numerals. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0110] Now refer to the longitudinal view at the rear end of the burner. Figure 8AThe liner mounting assembly 800 includes a liner having one or more liner panels 802 (one shown) arranged circumferentially and assembled to the housing 604. The plurality of liner panels 702 are assembled to the housing 604 at a plurality of fastening assemblies 706 (one shown) by means of spline rings 816, the spline rings 816 being similar in shape and function to spline rings 616.

[0111] The fastening assembly 806 includes features of the liner panel 802. Specifically, the liner panel 802 includes a plurality of posts 808, each post having a base 810, a handle 812, and a hook 814. The handle 812 and the hook 814 are assembled through holes in the housing 604. The interface between the handle 812 and the housing 604 constrains the rotation of the liner panel 802 relative to the housing 604. In the assembly of the liner mounting assembly 800, the handle 812 and the hook 814 are inserted through the housing 604, and a spline ring 816 is inserted into the hook 814 radially outward from the housing 604. The spline ring 816 includes alternating peak segments 842 and valley segments 844. The peak segments 842 generally establish the large diameter of the spline ring 816 in its free state, while the valley segments 844 generally establish the small diameter of the spline ring 816 in its free state. During assembly, spline ring 816 is compressed, causing the assembled large diameter corresponding to peak segment 842 to decrease relative to the free large diameter. Additionally or alternatively, the assembled small diameter, established by valley segment 844, increases relative to the free small diameter. The flexibility of spline ring 616 allows this compression and allows peak segment 842 to maintain an outward radial force on hook 814 and valley segment 844 to maintain an inward radial force on housing 604. These radial forces maintain the radial alignment of the lining panels 802 relative to housing 604 despite any movement, deformation, or relative diametrical thermal expansion or contraction of the lining panels 802 or housing 604 relative to each other.

[0112] The fastening assembly 806 also includes a Bainckie washer 726, which is assembled on the post 808 at the shank 812, between the housing 604 and the base 810 of the post 808. The Bainckie washer 726 acts as a spring in the radial direction between the lining panel 802 and the housing 604, allowing the lining panel 802 and the housing 604 to expand and contract relative to each other while maintaining the radial position of the lining panels 802 and the housing 604 relative to each other. Thus, the Bainckie washer 726 has a function similar to that of the spline ring 816.

[0113] Figure 8C A partial schematic cross-sectional view is shown of an alternative configuration of the liner mounting assembly 801, which has an alternative to the first attachment configuration (fastening assembly 807). Fastening assembly 807 is identical to fastening assembly 806, except that the fastening assembly 807 of the liner mounting assembly 801 lacks the Bainck washer 726. (As mentioned above regarding...) Figure 8A and Figure 8BThe spline ring 816 and Bausch washer 726 discussed serve a similar purpose. While both are used in the fastening assembly 806 of the liner mounting assembly 800 (intended to provide greater support and centering force to radially align the plurality of liner panels 802 with the housing 604), their simultaneous application may be redundant. In an alternative embodiment of the liner mounting assembly 801, using the fastening assembly 807, the radial alignment of the plurality of liner panels 802 and the housing 604 relative to each other is provided solely by the interaction between the spline ring 816, the hook 814 of the post 808, and the housing 604.

[0114] refer to Figure 2 and Figures 3A to 8C The liner panels (e.g., liner panels 88, 100, 302, 402, 502, 602, 702, 802) and liner housings (e.g., liner housings 82, 84, 304, 404, 504, 604) extend circumferentially about the longitudinal centerline axis 134 of the burner. Therefore, the mounting assembly extends in the radial direction, and the above description relates to radial forces, inward forces, outward forces, and radial dimensions. As described above, regarding... Figures 3A to 8C The described mounting components can also be applied to heat shields (e.g., heat shield 114). Figure 2 )) and domes (e.g., dome 112) Figure 2 The mounting components are arranged between the heat shield and the dome mounting components. In these examples, the mounting components are arranged to extend in the axial direction. Therefore, the previous description of the forces and dimensions applied to the heat shield and dome mounting components refers to axial force, rearward force, forward force, and axial dimension.

[0115] In the preceding discussion of the various liner mounting assemblies, the fastening assemblies were referenced to their relative positions within the burner, such as "rear" and "front". Alternative embodiments are considered where the fastening assemblies are located at or near opposite ends of the burner, or in the middle of the burner.

[0116] Insulating components, such as heat shields or lining panels, are attached to structural components within the burner, such as domes or shells. Attachment configurations that maintain the thickness of the insulating component provide optimal insulation performance. Furthermore, when combined with a second attachment configuration that allows for degrees of freedom of movement, deformation, and thermal growth, a first attachment configuration that constrains the insulating component to the structural component in three dimensions provides durability by reducing internal stress within the insulating component.

[0117] Further aspects are provided by the following items.

[0118] A combustor for a turbine engine, the combustor comprising: a combustion chamber for combustion of fuel and air, the combustion of the fuel and air generating heat; a mixer assembly disposed at a front end of the combustor for receiving and mixing the fuel and air, and injecting the fuel and air into the combustion chamber for combustion; at least one structural member; and an insulating member that at least partially defines the combustion chamber, has a functional thickness, and is fastened to the at least one structural member without reducing the functional thickness.

[0119] According to the burner described in the foregoing clause, the insulating member is attached to at least one structural member via a first attachment configuration and a second attachment configuration, the first attachment configuration constraining the insulating member in a radial dimension, an axial dimension, and a rotational dimension, and the second attachment configuration constraining the insulating member only in one of the radial dimension, the axial dimension, and the rotational dimension.

[0120] According to the burner described in the foregoing clause, the first attachment configuration includes a dovetail joint, the dovetail joint including a tail and a pin, wherein the tail or the pin is integrated with and extends from the insulating member.

[0121] According to the burner described in the foregoing clause, the tail portion or the pin is integrated with and extends from the at least one structural member.

[0122] According to any of the preceding clauses, the first attachment configuration includes a fastening assembly comprising a threaded fastener, and the threaded fastener comprising the tail or the pin.

[0123] According to any of the foregoing clauses of the burner, the dovetail joint further includes a seal disposed between the tail and the pin.

[0124] According to the burner described in the foregoing clause, the seal is mechanically compliant and provides a gap between the tail and the pin.

[0125] According to any of the preceding clauses of the burner, the second attachment configuration includes a ball plate assembly, the ball plate assembly including a plate member comprising: a first portion that contacts the insulating member, the first portion including: a plurality of spherical cavities; and a plurality of spherical ceramic balls, each of the plurality of spherical ceramic balls disposed in each of the plurality of spherical cavities, each of the spherical ceramic balls being substantially in point contact with the insulating member; and a second portion fastened to the at least one structural member, the second portion not contacting the insulating member.

[0126] According to the burner described in the foregoing clause, the ball plate assembly is flexible, having a free-state thickness and an installed thickness in the burner in the installed state, and the installed thickness is less than the free-state thickness, such that the ball plate assembly applies a force to the insulating member in the burner in the installed state.

[0127] The burner according to the foregoing clause further includes an arc-shaped portion that contacts the at least one structural member, applies force to the at least one structural member in the installed state, and does not contact the insulating member.

[0128] According to any of the preceding clauses of the burner, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member, the threaded fastener including: a threaded end; and a saddle end including: a front tab having a hole; and a rear tab having a hole; a block feature integrated with and extending from the insulating member, the block feature having a hole; and a pin assembled through the hole in the front tab, the hole in the rear tab, and the hole in the block feature.

[0129] According to any of the preceding clauses of the burner, the second attachment configuration includes a spline ring having alternating peak and valley segments, the valley segments of the spline ring contacting the insulating member to constrain the insulating member in one of the radial dimension, the axial dimension, or the rotational dimension.

[0130] According to the burner described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0131] According to any of the preceding clauses of the burner, the second attachment configuration further includes a threaded fastener fastened to the at least one structural member, the threaded fastener having a threaded end and a head, the head having a hole in which one of the peak segments of the spline ring is assembled.

[0132] According to any of the preceding clauses of the burner, the second attachment configuration further includes a surface coating on the insulating member, the surface coating being disposed between the spline ring and the insulating member, providing abrasion resistance, providing heat insulation, or providing both abrasion resistance and heat insulation.

[0133] According to any of the preceding clauses of the burner, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member having a threaded end and a head; and a slotted receiver integrated with and extending from the insulating member for receiving and retaining the head.

[0134] According to any of the preceding clauses of the burner, the first attachment configuration includes: a post integrated with the insulating member, the post including: a base extending from the insulating member; a handle assembled through the at least one structural member; and a hook; and a spline ring having alternating peak segments and valley segments, the valley segments of the spline ring contacting the at least one structural member, and one of the peak segments contacting the hook.

[0135] According to the burner described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0136] In any of the preceding clauses, the insulating member is a heat shield or lining panel.

[0137] In any of the preceding clauses, the at least one structural member is a dome or a shell.

[0138] A turbine engine includes: a compressor section providing a compressed air flow; a fuel system providing a fuel supply; a combustor located downstream of the compressor section, receiving the compressed air flow and the fuel supply for burning the compressed air flow and the fuel supply to produce combustion gases; and a turbine section located downstream of the combustor, including a turbine rotated by the combustion gases, wherein the combustor further includes: a combustion chamber for burning fuel and air, the combustion of the fuel and air generating heat; a mixer assembly disposed at a front end of the combustor for receiving and mixing the fuel and the air, and injecting the fuel and the air into the combustion chamber for combustion; at least one structural member; and an insulating member at least partially defining the combustion chamber, having a functional thickness, and fastened to the at least one structural member without reducing the functional thickness.

[0139] According to the turbine engine described in the foregoing clause, the insulating member is attached to at least one structural member via a first attachment configuration and a second attachment configuration, the first attachment configuration constraining the insulating member in a radial dimension, an axial dimension and a rotational dimension, and the second attachment configuration constraining the insulating member only in one of the radial dimension, the axial dimension and the rotational dimension.

[0140] According to any of the foregoing clauses, the burner is a conical head, the slotted receiver is a conical slotted receiver, and the first attachment configuration further includes a seal disposed between the conical head and the conical slotted receiver.

[0141] According to any of the preceding clauses of the burner, the first attachment configuration further includes a Bavarian gasket assembled between the insulating member and the at least one structural member.

[0142] According to any of the preceding clauses, the first attachment configuration includes a dovetail joint, the dovetail joint including a tail and a pin, wherein the tail or the pin is integrated with and extends from the insulating member.

[0143] According to the turbine engine described in the foregoing clause, the tail section or the pin is integrated with and extends from the at least one structural member.

[0144] According to any of the foregoing clauses, the first attachment configuration includes a fastening assembly comprising a threaded fastener, and the threaded fastener comprising the tail or the pin.

[0145] According to any of the foregoing clauses of the turbine engine, the dovetail joint further includes a seal disposed between the tail section and the pin.

[0146] According to the turbine engine described in the foregoing clause, the seal is mechanically compliant and provides a gap between the tail section and the pin.

[0147] According to any of the preceding clauses of the turbine engine, the second attachment configuration includes a ball plate assembly, the ball plate assembly including a plate member comprising: a first portion that contacts the insulating member, the first portion including: a plurality of spherical cavities; and a plurality of spherical ceramic balls, each of the plurality of spherical ceramic balls disposed in each of the plurality of spherical cavities, each of the spherical ceramic balls being substantially in point contact with the insulating member; and a second portion fastened to the at least one structural member, the second portion not contacting the insulating member.

[0148] According to the turbine engine described in the foregoing clause, the ball plate assembly is flexible, having a free-state thickness and an installed thickness in the combustor in the installed state, and the installed thickness is less than the free-state thickness, such that the ball plate assembly applies a force to the insulating member in the combustor in the installed state.

[0149] The turbine engine according to the foregoing clause further includes an arc-shaped portion that contacts the at least one structural member, applies force to the at least one structural member in the installed state, and does not contact the insulating member.

[0150] According to any of the preceding clauses of the turbine engine, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member, the threaded fastener including: a threaded end; and a saddle end including: a front tab having a hole; and a rear tab having a hole; a block feature integrated with and extending from the insulating member, the block feature having a hole; and a pin assembled through the hole in the front tab, the hole in the rear tab, and the hole in the block feature.

[0151] According to any of the preceding clauses of the turbine engine, the second attachment configuration includes a spline ring having alternating peak and valley segments, the valley segments of the spline ring contacting the insulating member to constrain the insulating member in one of the radial dimension, the axial dimension, or the rotational dimension.

[0152] According to the turbine engine described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0153] According to any of the foregoing clauses of the turbine engine, the second attachment configuration further includes a threaded fastener fastened to the at least one structural member, the threaded fastener having a threaded end and a head, the head having a hole in which one of the peak segments of the spline ring is assembled.

[0154] According to any of the foregoing clauses of the turbine engine, the second attachment configuration further includes a surface coating on the insulating member, the surface coating being disposed between the spline ring and the insulating member, providing wear resistance, providing heat insulation, or providing both wear resistance and heat insulation.

[0155] According to any of the preceding clauses of the turbine engine, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member having a threaded end and a head; and a slotted receiver integrated with and extending from the insulating member for receiving and retaining the head.

[0156] According to the turbine engine described in the foregoing clause, the head is a conical head, the slotted receiver is a conical slotted receiver, and the first attachment configuration further includes a seal disposed between the conical head and the conical slotted receiver.

[0157] According to any of the preceding clauses of the turbine engine, the first attachment configuration includes: a post integrated with the insulating member, the post including: a base extending from the insulating member; a shank assembling through the at least one structural member; and a hook; and a spline ring having alternating peak segments and valley segments, the valley segments of the spline ring contacting the at least one structural member, and one of the peak segments contacting the hook.

[0158] According to the turbine engine described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0159] According to any of the foregoing clauses of the turbine engine, the first attachment configuration further includes a Bavarian gasket assembled between the insulating member and the at least one structural member.

[0160] In any of the preceding clauses, the insulating component of the turbine engine is a heat shield or lining panel.

[0161] In any of the preceding clauses, the turbine engine wherein the at least one structural member is a dome or a housing.

[0162] A method of operating a burner, the method comprising: fastening at least one insulating member to at least one structural member, the at least one structural member at least partially defining a combustion chamber; receiving and mixing fuel and air through a mixer assembly to produce a fuel and air mixture; burning the fuel and air mixture in the combustion chamber to generate heat; and insulating the at least one structural member with the insulating member without reducing its functional thickness.

[0163] The method according to the foregoing clauses further includes securing the insulating member to the at least one structural member via a first attachment configuration; constraining the insulating member in radial, axial, and rotational dimensions in the first attachment configuration; securing the insulating member to the at least one structural member via a second attachment configuration; constraining the insulating member in only one of the radial, axial, and rotational dimensions in the second attachment configuration; and allowing the insulating member to move, deform, thermally expand, or thermally contract relative to the at least one structural member in one or both of the radial, axial, or rotational dimensions in the second attachment configuration.

[0164] According to the method described in the foregoing clause, the first attachment configuration includes a dovetail joint, the dovetail joint including a tail and a pin, wherein the tail or the pin is integrated with and extends from the insulating member.

[0165] According to the method described in the foregoing clause, the tail or the pin is integrated with and extends from the at least one structural member.

[0166] According to any of the foregoing descriptions, the first attachment configuration includes a fastening assembly, the fastening assembly including a threaded fastener, and the threaded fastener including the tail or the pin.

[0167] According to any of the foregoing descriptions, the dovetail joint further includes a seal disposed between the tail and the pin and providing a gap between the tail and the pin.

[0168] The method according to the foregoing clause further includes cooling the first attachment configuration by allowing air to flow through the gap between the tail and the pin, allowing air to flow around the tail, and allowing air to flow around the pin.

[0169] According to any of the foregoing descriptions, the second attachment configuration includes a ball plate assembly, the ball plate assembly including a plate member comprising: a first portion that contacts the insulating member, the first portion including: a plurality of spherical cavities; and a plurality of spherical ceramic balls, each of the plurality of spherical ceramic balls disposed in each of the plurality of spherical cavities, each of the spherical ceramic balls being substantially in point contact with the insulating member; and a second portion fastened to the at least one structural member, the second portion not contacting the insulating member.

[0170] The method according to the foregoing clause further includes, in the burner in the installed state, the ball plate assembly applying a force to the insulating member, the force being caused by the deformation of the ball plate assembly relative to the free state in the assembled state.

[0171] According to the method described in the foregoing clause, the ball plate assembly further includes an arcuate portion, and the method further includes applying a force by the arcuate portion to the at least one structural member, the arcuate portion not contacting the insulating member.

[0172] According to any of the foregoing clauses, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member, the threaded fastener including: a threaded end; and a saddle end including: a front tab having a hole; and a rear tab having a hole; a block feature integrated with and extending from the insulating member, the block feature having a hole; and a pin assembled through the hole in the front tab, the hole in the rear tab, and the hole in the block feature.

[0173] The method according to any of the foregoing clauses further includes constraining the insulating member by a spline ring on one of the radial dimension, the axial dimension, or the rotational dimension.

[0174] According to the method described in the foregoing clause, the spline ring has peak segments and valley segments, and the method further includes defining an assembled large diameter by the peak segments, the assembled large diameter being smaller than the free large diameter; defining an assembled small diameter, the assembled small diameter being larger than the free small diameter; applying a radially outward force by the spline ring at the peak segments on the at least one structural member; and applying a radially inward force by the spline ring at the valley segments on the insulating member.

[0175] According to any of the foregoing descriptions, the second attachment configuration further includes a threaded fastener fastened to the at least one structural member, the threaded fastener having a threaded end and a head, the head having a hole in which one of the peak segments of the spline ring is assembled.

[0176] According to any of the foregoing descriptions, the second attachment configuration further includes a surface coating on the insulating member, the surface coating being disposed between the spline ring and the insulating member, providing abrasion resistance, providing thermal insulation, or providing both abrasion resistance and thermal insulation.

[0177] According to any of the foregoing descriptions, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member having a threaded end and a head; and a slotted receiver integrated with and extending from the insulating member for receiving and retaining the head.

[0178] According to the method described in the foregoing clause, the head is a conical head, the slotted receiver is a conical slotted receiver, and the first attachment configuration further includes a seal disposed between the conical head and the conical slotted receiver.

[0179] According to any of the foregoing descriptions, the first attachment configuration includes: a post integrated with the insulating member, the post including: a base extending from the insulating member; a handle assembling through the at least one structural member; and a hook; and a spline ring having alternating peak segments and valley segments, the valley segments of the spline ring contacting the at least one structural member, and the peak segments contacting the hook.

[0180] According to the method described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0181] According to any of the foregoing provisions of the method, the first attachment configuration further includes a Bassian gasket assembled between the insulating member and the at least one structural member.

[0182] According to any of the foregoing clauses, the insulating member is a heat shield or lining panel.

[0183] According to any of the preceding clauses of the method, the at least one structural member is a dome or a shell.

[0184] A method of operating a turbine engine, the method comprising: providing a compressed air flow through a compressor section; providing a fuel flow through a fuel system; fastening at least one insulating member of a combustor to at least one structural member of the combustor, the at least one structural member at least partially defining a combustion chamber; receiving and mixing fuel and air through a mixer assembly to produce a fuel-air mixture; burning the fuel-air mixture in the combustion chamber to generate heat; and insulating the at least one structural member with an insulating member having a functional thickness without reducing its functional thickness.

[0185] The method according to the foregoing clauses further includes securing the insulating member to the at least one structural member via a first attachment configuration; constraining the insulating member in radial, axial, and rotational dimensions in the first attachment configuration; securing the insulating member to the at least one structural member via a second attachment configuration; constraining the insulating member in only one of the radial, axial, and rotational dimensions in the second attachment configuration; and allowing the insulating member to move, deform, thermally expand, or thermally contract relative to the at least one structural member in one or both of the radial, axial, or rotational dimensions in the second attachment configuration.

[0186] According to the method described in the foregoing clause, the first attachment configuration includes a dovetail joint, the dovetail joint including a tail and a pin, wherein the tail or the pin is integrated with and extends from the insulating member.

[0187] According to the method described in the foregoing clause, the tail or the pin is integrated with and extends from the at least one structural member.

[0188] According to any of the foregoing descriptions, the first attachment configuration includes a fastening assembly, the fastening assembly including a threaded fastener, and the threaded fastener including the tail or the pin.

[0189] According to any of the foregoing descriptions, the dovetail joint further includes a seal disposed between the tail and the pin and providing a gap between the tail and the pin.

[0190] The method according to the foregoing clause further includes cooling the first attachment configuration by allowing air to flow through the gap between the tail and the pin, allowing air to flow around the tail, and allowing air to flow around the pin.

[0191] According to any of the foregoing descriptions, the second attachment configuration includes a ball plate assembly, the ball plate assembly including a plate member comprising: a first portion that contacts the insulating member, the first portion including: a plurality of spherical cavities; and a plurality of spherical ceramic balls, each of the plurality of spherical ceramic balls disposed in each of the plurality of spherical cavities, each of the spherical ceramic balls being substantially in point contact with the insulating member; and a second portion fastened to the at least one structural member, the second portion not contacting the insulating member.

[0192] The method according to the foregoing clause further includes, in the burner in the installed state, the ball plate assembly applying a force to the insulating member, the force being caused by the deformation of the ball plate assembly relative to the free state in the assembled state.

[0193] According to the method described in the foregoing clause, the ball plate assembly further includes an arcuate portion, and the method further includes applying a force by the arcuate portion to the at least one structural member, the arcuate portion not contacting the insulating member.

[0194] According to any of the foregoing clauses, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member, the threaded fastener including: a threaded end; and a saddle end including: a front tab having a hole; and a rear tab having a hole; a block feature integrated with and extending from the insulating member, the block feature having a hole; and a pin assembled through the hole in the front tab, the hole in the rear tab, and the hole in the block feature.

[0195] The method according to any of the foregoing clauses further includes constraining the insulating member by a spline ring on one of the radial dimension, the axial dimension, or the rotational dimension.

[0196] According to the method described in the foregoing clause, the spline ring has peak segments and valley segments, and the method further includes defining an assembled large diameter by the peak segments, the assembled large diameter being smaller than the free large diameter; defining an assembled small diameter, the assembled small diameter being larger than the free small diameter; applying a radially outward force by the spline ring at the peak segments on the at least one structural member; and applying a radially inward force by the spline ring at the valley segments on the insulating member.

[0197] According to any of the foregoing descriptions, the second attachment configuration further includes a threaded fastener fastened to the at least one structural member, the threaded fastener having a threaded end and a head, the head having a hole in which one of the peak segments of the spline ring is assembled.

[0198] According to any of the foregoing descriptions, the second attachment configuration further includes a surface coating on the insulating member, the surface coating being disposed between the spline ring and the insulating member, providing abrasion resistance, providing thermal insulation, or providing both abrasion resistance and thermal insulation.

[0199] According to any of the foregoing descriptions, the first attachment configuration includes: a threaded fastener fastened to the at least one structural member having a threaded end and a head; and a slotted receiver integrated with and extending from the insulating member for receiving and retaining the head.

[0200] According to the method described in the foregoing clause, the head is a conical head, the slotted receiver is a conical slotted receiver, and the first attachment configuration further includes a seal disposed between the conical head and the conical slotted receiver.

[0201] According to any of the foregoing descriptions, the first attachment configuration includes: a post integrated with the insulating member, the post including: a base extending from the insulating member; a handle assembling through the at least one structural member; and a hook; and a spline ring having alternating peak segments and valley segments, the valley segments of the spline ring contacting the at least one structural member, and the peak segments contacting the hook.

[0202] According to the method described in the foregoing clause, in the free state, the peak segment defines a large diameter in the free state, and in the free state, the valley segment defines a small diameter in the free state. In the installed state, the peak segment defines a large diameter in the installed state that is smaller than the large diameter in the free state, and in the installed state, the valley segment defines a small diameter in the installed state that is larger than the small diameter in the free state.

[0203] According to any of the foregoing provisions of the method, the first attachment configuration further includes a Bassian gasket assembled between the insulating member and the at least one structural member.

[0204] According to any of the foregoing clauses, the insulating member is a heat shield or lining panel.

[0205] According to any of the preceding clauses of the method, the at least one structural member is a dome or a shell.

[0206] 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 present disclosure. Furthermore, even if not explicitly stated above, features described in connection with one embodiment of the present disclosure can be used in conjunction with other embodiments.

Claims

1. A combustor for a turbine engine, characterized in that, The burner includes: A combustion chamber for burning fuel and air, the combustion of which generates heat; A mixer assembly disposed at the front end of the burner for receiving and mixing the fuel and the air, and injecting the fuel and the air into the combustion chamber for combustion; At least one structural member; and An insulating member, which at least partially defines the combustion chamber, has a functional thickness, and is fastened to the at least one structural member without reducing the functional thickness.

2. The burner according to claim 1, characterized in that, The insulating member is attached to the at least one structural member via a first attachment configuration and a second attachment configuration, wherein the first attachment configuration constrains the insulating member in a radial dimension, an axial dimension, and a rotational dimension, and the second attachment configuration constrains the insulating member only in one of the radial dimension, the axial dimension, and the rotational dimension.

3. The burner according to claim 2, characterized in that, The first attachment configuration includes: Threaded fasteners, the threaded fasteners securing to the at least one structural member, the threaded fasteners comprising: Threaded end; and The saddle end includes: A front protrusion having a hole; and A rear protrusion having a hole; Block features, said block features being integrated with and extending from said insulating member, said block features having holes; and A pin, which is assembled by passing through the hole in the front protrusion, the hole in the rear protrusion, and the hole in the block feature.

4. The burner according to claim 2, characterized in that, The first attachment configuration includes: Threaded fasteners, said threaded fasteners being fastened to said at least one structural member, having a threaded end and a head; and A slotted receiver, integrated with and extending from the insulating member, for receiving and retaining the head.

5. The burner according to claim 2, characterized in that, The first attachment configuration includes: A post, integrated with the insulating member, the post comprising: Base, the base extending from the insulating member; A handle, which is assembled through the at least one structural member; and Hook; and A spline ring having alternating peaks and valleys, wherein the valleys of the spline ring contact the at least one structural member, and one of the peaks contacts the hook.

6. The burner according to claim 5, characterized in that, in, In the free state, the peak segment defines the large diameter of the free state, and in the free state, the valley segment defines the small diameter of the free state. In the installed state, the peak segment defines the large diameter of the installed state, which is smaller than the large diameter of the free state, and in the installed state, the valley segment defines the small diameter of the installed state, which is larger than the small diameter of the free state.

7. The burner according to claim 2, characterized in that, The second attachment configuration includes a spline ring having alternating peak and valley segments, the valley segments of the spline ring contacting the insulating member to constrain the insulating member in one of the radial dimension, the axial dimension, or the rotational dimension.

8. The burner according to claim 7, characterized in that, in, In the free state, the peak segment defines the large diameter of the free state, and in the free state, the valley segment defines the small diameter of the free state. In the installed state, the peak segment defines the large diameter of the installed state, which is smaller than the large diameter of the free state, and in the installed state, the valley segment defines the small diameter of the installed state, which is larger than the small diameter of the free state.

9. The burner according to claim 7, characterized in that, The second attachment configuration further includes a threaded fastener fastened to the at least one structural member, the threaded fastener having a threaded end and a head, the head having a hole in which one of the peak segments of the spline ring is assembled.

10. The burner according to claim 7, characterized in that, The second attachment configuration further includes a surface coating on the insulating member, the surface coating being disposed between the spline ring and the insulating member, providing abrasion resistance, providing thermal insulation, or providing both abrasion resistance and thermal insulation.

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