Gas turbine engine combustor with ceramic matrix composite (CMC) liner and CMC dome

Abstract

A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a metal shroud structure including a single yoke outer shroud attachment flange and a single yoke inner shroud attachment flange, a CMC outer liner, and a CMC inner liner. An outer connection connects the outer hood connection flange, the CMC dome structure, and the CMC outer liner in an outer stacked arrangement, and an inner connection connects the inner hood connection flange, the CMC dome structure, and the CMC inner liner in an inner stacked arrangement.

Description

Technical Field

[0001] The present disclosure relates to combustors for gas turbine engines, and more particularly, to combustors having a ceramic matrix composite (CMC) liner and a CMC dome connected to a metal shroud structure. Background Art

[0002] A gas turbine engine typically includes a combustor. The combustor may be an annular combustor including a combustor liner. The combustor liner may include an outer liner and an inner liner connected to a dome, with a combustion chamber defined between the inner and outer liner. The outer and inner liners may also be connected to a shroud structure. The shroud structure may typically be a metal structure, but in some cases, the outer and inner liners may be formed from a CMC material. In some cases, the dome may also be formed from a CMC material. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages of the present disclosure will be apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings, in which like reference numbers generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine according to aspects of the present disclosure.

[0005] Figure 2 is a partial cross-sectional side view of an exemplary combustor according to aspects of the present disclosure.

[0006] Figure 3 According to aspects of the present disclosure Figure 2 Detail of FIG. 96 is an enlarged partial cross-sectional view of the outer connection portion.

[0007] Figure 4 According to aspects of the present disclosure Figure 2 FIG100 is an enlarged partial cross-sectional view of the inner connection portion.

[0008] Figure 5 Depicting aspects of the present disclosure Figure 3 An alternative external connection to the one shown.

[0009] Figure 6 Depicting aspects of the present disclosure Figure 4 An alternative inner connection to the one shown.

[0010] Figure 7 Depicting aspects of the present disclosure Figure 3 An alternative external connection to the one shown.

[0011] Figure 8Depicted according to aspects of the present disclosure Figure 4 An alternative inner connection to the one shown.

[0012] Figure 9 According to aspects of the present disclosure Figure 2 Detail of the figure 430 intercepted Figure 2 A partial cross-sectional view of a portion of the combustion section.

[0013] Figure 10 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0014] Figure 11 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0015] Figure 12 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0016] Figure 13 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0017] Figure 14 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0018] Figure 15 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0019] Figure 16 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown.

[0020] Figure 17 Depicted according to aspects of the present disclosure Figure 9 Alternative combustion section arrangements to those shown. DETAILED DESCRIPTION

[0021] Features, advantages, and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings, and claims. Furthermore, the following detailed description is exemplary and is intended to provide further explanation without limiting the claimed disclosure.

[0022] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the present disclosure.

[0023] As used herein, the terms “first” and “second” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0024] The terms "upstream" and "downstream" refer to relative directions of fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0025] As used herein, the terms "axial," "axially," and "longitudinal" refer to directions and orientations extending generally parallel to the centerline axis of a turbine engine. Furthermore, the terms "radial" and "radially" refer to directions and orientations extending generally perpendicular to the centerline axis of a turbine engine. Furthermore, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc about the centerline axis of a turbine engine.

[0026] The terms "outer" and "inner" refer to relative directions relative to a radial direction extending perpendicular to the centerline axis. For example, "outer" refers to an element or a portion of an element farther from the centerline axis in the radial direction (e.g., one side of the element), while "inner" refers to an element or a portion of an element closer to the centerline axis in the radial direction (e.g., one side of the element).

[0027] The terms "outward" and "inward" refer to relative directions relative to a radial direction extending from a defined portion of an element. For example, "outward" refers to a direction extending radially from a defined portion of an element away from a centerline axis in a radial direction. The term "inward" refers to a direction extending radially from a defined portion of an element toward a centerline axis in a radial direction.

[0028] Unless otherwise indicated herein, the terms "coupled," "fixed," "attached," "connected," and the like refer to both direct coupling, fixing, attachment, or connection as well as indirect coupling, fixing, attachment, or connection through one or more intermediate components or features.

[0029] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0030] As used herein throughout the specification and claims, approximating language is applied to modify any quantitative expression that can be permitted to vary without resulting in a change in the basic function to which it is related. Thus, values ​​modified by terms such as "about," "approximately," and "substantially" are not limited to the precise values ​​specified. In at least some cases, approximate language can correspond to the precision of an instrument used to measure a value, or the precision of a method or machine used to construct or manufacture a component and / or system. For example, approximate language can refer to within a margin of 1%, 2%, 4%, 10%, 15%, or 20% of a single value, a range of values, and / or an endpoint of a defined range of values.

[0031] Here and throughout the specification and claims, range limitations are combined and interchanged. Unless context or language indicates otherwise, such ranges are identified and include all subranges contained therein. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0032] As used herein, the term "composite" refers to a material having two or more constituent materials. A composite material can be a combination of at least two or more metals, non-metals, or a combination of metal and non-metal elements or materials. Examples of composite materials can include, but are not limited to, polymer matrix composites (PMCs), ceramic matrix composites (CMCs), and metal matrix composites (MMCs). A composite material can be formed from a matrix material and reinforcing elements such as fibers (referred to herein as reinforcing fibers).

[0033] As used herein, CMC refers to a class of materials having reinforcing fibers in 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, aluminum oxide (Al2O3), silicon dioxide (SiO2), aluminosilicates (such as mullite), or mixtures thereof), or mixtures thereof.

[0034] Some 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, aluminum oxide (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.

[0035] Typically, a specific CMC can be referred to by its fiber type / matrix type combination. For example, C / SiC is carbon fiber reinforced silicon carbide, SiC / SiC is silicon carbide fiber reinforced silicon carbide, SiC / SiN is silicon carbide fiber reinforced silicon nitride, SiC / SiC-SiN is a silicon carbide fiber-reinforced silicon carbide / silicon nitride matrix mixture, and so on. In other examples, a CMC can be composed of a matrix and reinforcing fibers comprising oxide-based materials such as aluminum oxide (Al2O3), silicon dioxide (SiO2), aluminosilicates, and mixtures thereof. Aluminosilicates can include crystalline materials such as mullite (3Al2O3·2SiO2), as well as glassy aluminosilicates.

[0036] In certain non-limiting examples, the reinforcing fibers can be bundled (e.g., to form fiber bundles) and / or coated before being included in the matrix. The fiber bundles can be impregnated with a slurry composition before or after forming a preform. The preform can then be subjected to heat treatment and subsequent chemical treatment to obtain a component formed of a CMC material with a desired chemical composition. For example, the preform can undergo solidification or burnout to produce a high coke residue in the preform, and then undergo melt infiltration with silicon, or undergo solidification or pyrolysis to produce a silicon carbide matrix in the preform, and then undergo chemical vapor infiltration with silicon carbide. Additional steps can be taken to improve the densification of the preform, before or after chemical vapor infiltration, by injecting the preform with a liquid resin or polymer, and then performing a heat treatment step to fill the voids with silicon carbide. As used herein, CMC materials can be formed using any known or later developed method (including but not limited to melt infiltration, chemical vapor infiltration, polymer impregnation pyrolysis (PIP) or any combination thereof).

[0037] As used herein, the term "metal" refers to materials including metals such as, but not limited to, titanium, iron, aluminum, stainless steel, 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.

[0038] A gas turbine engine typically includes a combustor. The combustor may be an annular combustor including a combustor liner, which may include an outer liner and an inner liner connected to a dome structure, wherein a combustion chamber is defined between the inner liner and the outer liner. The outer liner, the inner liner, and the dome structure may also be connected to the shroud structure via a double yoke (or clevis type) connection. The shroud structure may typically be a metal structure and include an outer double yoke clevis and an inner double yoke clevis for connecting the outer liner, the inner liner, and the dome structure to the shroud structure. The double yoke (clevis type) connection, while effectively connecting the combustor components together, increases the overall radial profile of the combustor and increases the weight of the shroud structure because the shroud structure is typically metal.

[0039] The present disclosure provides a combustor in which a shroud structure includes a single yoke or single connection flange on both the outer and inner sides of the shroud structure for connecting a CMC outer liner, a CMC inner liner, and a CMC dome structure to a metal shroud structure. According to the present disclosure, the shroud structure includes an outer shroud connection flange that connects to an outer liner connection flange of the CMC outer liner and an outer dome connection flange of the CMC dome structure. By including a single outer shroud connection flange on the shroud structure, various stacking arrangements of the outer shroud connection flange, the outer liner connection flange, and the outer dome connection flange can be included to provide a simplified outer structure between the outer components. Similarly, by including a single inner shroud connection flange on the shroud structure, various stacking arrangements of the inner shroud connection flange, the inner liner connection flange, and the inner dome connection flange can be included to provide a simplified inner structure between the inner components. In addition, by eliminating the second connection flange from the shroud structure used on a double yoke (clevis-type) connection, the overall radial height of the metal shroud structure is reduced, and the weight of the metal shroud structure is also reduced.

[0040] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10 (referred to herein as "engine 10") that may incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present disclosure is also applicable to turbomachinery in general, including turbojets, turboprops, and turboshaft gas turbine engines, including marine turbine engines, industrial turbine engines, and auxiliary power units. The present disclosure is also applicable to non-ducted fan (or open rotor) turbine engines. Figure 1 As shown, the engine 10 has a longitudinal centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99 for reference. Generally, the engine 10 may include a fan assembly 14 and a turbo-engine 16 disposed downstream of the fan assembly 14.

[0041] The turbocharged engine 16 may generally include a casing 18 defining an annular inlet 20 leading to a core airflow path 23 of the turbocharged engine 16. The casing 18 surrounds or at least partially forms, in serial flow relationship: a compressor section 21 having a low-pressure compressor (LPC) 22 and a high-pressure compressor (HPC) 24; a combustion section 26; a turbine section 27 including a high-pressure turbine (HPT) 28 and a low-pressure turbine (LPT) 30; and an ejection exhaust nozzle section 32. A high-pressure rotor shaft 34 drivingly connects the HPT 28 to the HPC 24. A low-pressure rotor shaft 36 drivingly connects the LPT 30 to the LPC 22. The low-pressure rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, as shown Figure 1 As shown, the low pressure rotor shaft 36 may be connected to the fan shaft 38 through a reduction gearbox 40 , such as in an indirect drive or geared configuration.

[0042] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the turbocharger engine 16. The nacelle 44 may be supported relative to the turbocharger engine 16 by a plurality of circumferentially spaced outlet guide vanes (or struts) 46. In addition, at least a portion of the nacelle 44 may extend over an outer portion of the turbocharger engine 16 to define a bypass airflow passage 48 therebetween.

[0043] Figure 2 According to aspects of the present disclosure Figure 1 A partial cross-sectional side view of an exemplary combustion section 26 of a turbocharged engine 16 is shown. Figure 2 The exemplary combustion section 26 shown in FIG is an annular combustion section extending circumferentially about the combustor centerline axis 12′, which is coincident with the longitudinal centerline axis 12 of the engine 10. Although the combustion section 26 is annular about the combustor centerline axis 12′, Figure 2 Only the upper portion of the combustion section 26 is shown in the cross-sectional view of FIG. The combustion section 26 includes an annular burner outer shell 64 and an annular burner inner shell 65 surrounding the burner 29. The burner 29 includes an annular burner liner 50 arranged between the annular burner outer shell 64 and the annular burner inner shell 65. Figure 2 As shown, the annular combustor liner 50 includes an annular CMC inner liner 52 and an annular CMC outer liner 54, each of which extends circumferentially about the combustor centerline axis 12' to form an annular liner. The CMC outer liner 54 and the CMC inner liner 52 can be a single-piece liner or can be composed of multiple separate segments that can be connected together to form an annular liner. Each of the annular CMC outer liner 54 and the annular CMC inner liner 52 is composed of a CMC material as defined above. A CMC dome structure 56 composed of CMC material includes a dome plate 59 that extends between an outer dome attachment flange 55 and an inner dome attachment flange 67 of the CMC dome structure 56. The CMC dome structure 56 extends between the CMC outer liner 54 and the CMC inner liner 52 and also extends circumferentially about the combustor centerline axis 12' to define an annular CMC dome structure. The CMC dome structure 56 may be a single-piece CMC dome structure or may be constructed from a plurality of separate segments that may be connected together to form the annular CMC dome structure 56 .

[0044] As will be described in more detail below, the CMC liner 52 and the CMC outer liner 54 are connected to the CMC dome structure 56 to define a combustion chamber 62 therebetween. The CMC liner 52 and the CMC outer liner 54 extend from the CMC dome structure 56 to the HPT 28 ( Figure 1 ), thereby, at least in part, defining a hot gas path between the CMC dome structure 56 and the HPT 28. Additionally, as will be described in greater detail below, a metallic shroud structure 60 is connected to the CMC liner 52, the CMC outer liner 54, and the CMC dome structure 56 via outer and inner connectors 92, 94, thereby defining a pressure plenum 66 therein. The outer and inner connectors 92, 94 will be described in greater detail below. The shroud structure 60 extends circumferentially about the combustor centerline axis 12' and may be structured as a single-piece shroud structure or may be constructed as a plurality of separate shroud segments that are connected together to form the annular shroud structure 60. The shroud structure 60 may generally be constructed of a metallic material as defined above.

[0045] The combustion section 26 also includes a plurality of swirler assemblies 58 ( Figure 2 In addition, a plurality of fuel nozzle assemblies 70 ( Figure 2 One is shown in FIG. 5 ) connected to the combustor casing 64 , and each fuel nozzle assembly 70 extends through a corresponding shroud opening 61 in the shroud structure 60 and connects with a corresponding swirler assembly 58 .

[0046] like Figure 2 As shown, the combustion section 26 includes a diffuser 25, and a combustor outer shell 64 and a combustor inner shell 65 are connected to the diffuser 25. The diffuser 25 is in fluid communication with the HPC 24 and, as will be described below, provides a flow of compressed air 82 into a plenum 84 defined between the combustor outer shell 64 and the combustor inner shell 65. The combustor outer shell 64 and the combustor inner shell 65 also surround the combustor liner 50 and define an outer flow channel 88 between the combustor outer shell 64 and the CMC outer liner 54 and an inner flow channel 90 between the combustor inner shell 65 and the CMC inner liner 52. The CMC outer liner 54 may include a plurality of dilution openings 68 ( Figure 2 ), and the CMC liner 52 may include a plurality of dilution openings 69 ( Figure 2 Dilution openings 68 provide fluid communication between outer flow passage 88 and combustion chamber 62 through CMC outer liner 54 , and dilution openings 69 provide fluid communication between inner flow passage 90 and combustion chamber 60 through CMC inner liner 52 .

[0047] Common Reference Figure 1 and Figure 2During operation of engine 10, a quantity of air 72 (schematically indicated by arrows) enters engine 10 from upstream end 98 through nacelle 44 and / or associated nacelle inlet 76 of fan assembly 14. As air 72 passes through fan blades 42, a portion of air 72 is forced by fan blades 42 through fan assembly 14 and directed or channeled into bypass airflow passage 48 as bypass airflow 78. Another portion of air 72 is directed or channeled into LPC 22 via annular inlet 20 as compressor inlet air 80. As compressor inlet air 80 flows from annular inlet 20 through LPC 22 and HPC 24 toward combustion section 26, LPC 22 and HPC 24 progressively compress compressor inlet air 80 to form compressed air 82. Figure 2 As shown, compressed air 82 flows through diffuser 25 and into plenum 84 of combustion section 26 to pressurize plenum 84. A first portion of the compressed air 82 in plenum 84 (schematically indicated by arrows representing compressed air 83) flows from plenum 84 through shroud opening 61 into pressure plenum 66 of shroud structure 60. The compressed air 83 in pressure plenum 66 flows through swirler assembly 58, where it mixes with fuel provided to swirler assembly 58 by fuel nozzle assembly 70 to produce a fuel-air mixture 79. The fuel-air mixture 79 is then injected from swirler assembly 58 into combustion chamber 62, where it is ignited by an igniter (not shown) and combusted within combustion chamber 62 to produce combustion gases 86 within combustion chamber 62.

[0048] A second portion of the compressed air 82 in the plenum 84 (schematically shown as arrows representing compressed air 85 and compressed air 87) can be directed into outer flow passage 88 and inner flow passage 90, respectively. A portion of the compressed air 85 flowing through the outer flow passage 88 (schematically shown as compressed air 85a) can be directed through the plurality of dilution openings 68 of the CMC outer liner 54 into the combustion chamber 62 to provide quenching of the combustion gases 86. Similarly, a portion of the compressed air 87 flowing through the inner flow passage 90 (schematically shown as compressed air 87a) can be directed through the plurality of dilution openings 69 of the CMC inner liner 52 into the combustion chamber 62 to provide quenching of the combustion gases 86.

[0049] Still a common reference Figure 1 and Figure 2 The combustion gas 86 generated in the combustion chamber 62 is passed through the turbine nozzle 74 ( Figure 2 ) flows into HPT 28( Figure 1 ), thereby rotating the HPT 28, which drives the high pressure rotor shaft 34, thereby driving the HPC 24 to support the operation of the HPC 24. Figure 1As shown, combustion gases 86 are then directed from HPT 28 to LPT 30, thereby rotating LPT 30, which drives low-pressure rotor shaft 36, thereby driving LPC 22 to support operation of LPC 22 and / or driving rotation of fan shaft 38 via reduction gearbox 40. Combustion gases 86 are then discharged through jet exhaust nozzle section 32 of turbocharger engine 16 to provide propulsion at downstream end 99 of engine 10.

[0050] Figure 3 According to aspects of the present disclosure Figure 2 An enlarged partial cross-sectional view of the outer connection portion 92 taken at detail 96 of FIG. Figure 3 In the aspect of FIG. 1 , the shroud structure 60 includes a single yoke shroud attachment flange 102 extending from a shroud flange root portion 104 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 3 In the aspect of the present invention, the shroud attachment flange 102 is generally arranged to extend from a central portion 106 of a shroud flange root portion 104. The shroud flange root portion 104 includes a first outer barrier wall portion 108 extending radially outward from an upstream end 112 of the shroud attachment flange 102 and a second outer barrier wall portion 110 extending radially inward from an upstream end 122 of the shroud attachment flange 102. The shroud attachment flange 102 also includes a shroud attachment flange opening 114 therethrough.

[0051] The CMC outer liner 54 includes an upstream end 118 (see also FIG. 1 ) of the CMC outer liner 54 in the longitudinal direction L. Figure 2 ) extends to the outer lining connection flange 116. Figure 3 In an aspect of the present invention, the outer liner connection flange 116 includes an outer liner connection flange opening 120 therethrough. An outer liner connection flange bushing 122 can be installed within the outer liner connection flange opening 120, and the outer liner connection flange bushing 122 includes an outer liner connection flange bushing opening 124 therethrough.

[0052] The CMC dome structure 56 includes an outer dome connection flange 55 extending from an outer side 126 of the dome plate 59 in the longitudinal direction L. The outer dome connection flange 55 includes an outer dome connection flange opening 128 therethrough. An outer dome connection flange bushing 130 may be mounted within the outer dome connection flange opening 128, and the outer dome connection flange bushing 130 includes an outer dome connection flange bushing opening 132 therethrough.

[0053] Figure 3The outer connector 92 of the embodiment of the present invention further includes a first outer connector bushing 134 and a second outer connector bushing 136. The first outer connector bushing has an opening 138 therethrough, an outer diameter 140, and a flange 135. The second outer connector bushing 136 has an opening 142 therethrough, an outer diameter 144, and a flange 137. The outer diameter 140 of the first outer connector bushing 134 is slightly smaller than the inner diameter of the outer liner connection flange bushing opening 124. The first outer connector bushing 134 is inserted through the outer liner connection flange bushing opening 124 so that the outer liner connection flange bushing 122 and the first outer connector bushing 134 are slidingly engaged with each other to allow radial movement of the CMC outer liner connection flange 116. Similarly, the outer diameter 144 of the second outer connector bushing 136 is slightly smaller than the inner diameter of the outer dome connection flange bushing opening 132. The second outer connection bushing 136 is inserted through the outer dome connection flange bushing opening 132 such that the outer dome connection flange bushing 130 and the second outer connection bushing 136 are slidingly engaged with each other to allow radial movement of the CMC outer dome connection flange 55 .

[0054] The outer connector fastener 146 (e.g., a bolt) includes a head 148 and a shank 150. The shank 150 is inserted through the opening 138 of the first outer connector bushing 134, through the housing attachment flange opening 114, and through the opening 142 of the second outer connector bushing 136 until the head 148 engages the flange 135 of the first outer connector bushing 134. A retaining member 152 (e.g., a nut) is threadedly engaged with the shank 150 and torqued to engage the inner side 154 of the first outer connector bushing 134 with the outer side 156 of the housing attachment flange 102 and to engage the outer side 158 of the second outer connector bushing 136 with the inner side 160 of the housing attachment flange 102.

[0055] therefore, Figure 3 The aforementioned arrangement provides an outer stacking arrangement 162 relative to the radial direction R, wherein the outer dome connection flange 55 is arranged on the inner side 164 of the outer stacking arrangement 162, the outer liner connection flange 116 is arranged on the outer side 166 of the outer stacking arrangement 162, and the outer cover connection flange 102 is arranged between the outer dome connection flange 55 and the outer liner connection flange 116.

[0056] Additionally, an upstream end 168 of the outer liner attachment flange 116 is disposed adjacent the first outer baffle wall portion 108 with a gap 170 therebetween such that the upstream end 168 of the outer liner attachment flange 116 and the first outer baffle wall portion 108 define an outer liner attachment flange stop 172. The outer liner attachment flange stop 172 acts as a seal to limit or restrict the amount of compressed air 85 that may pass from the outer flow passage 88 through the gap 170 and between the outer liner attachment flange 116 and the outer shroud attachment flange 102 into the combustion chamber 62.

[0057] Similarly, the upstream end 174 of the outer dome attachment flange 55 is disposed adjacent the second outer baffle wall portion 110 with a gap 176 therebetween such that the upstream end 174 of the outer dome attachment flange 55 and the second outer baffle wall portion 110 define an outer dome attachment flange baffle 178. The outer dome attachment flange baffle 178 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 176 and between the outer dome attachment flange 55 and the outer shroud attachment flange 102 into the combustion chamber 62.

[0058] Figure 4 According to aspects of the present disclosure Figure 2 An enlarged partial cross-sectional view of the inner connecting portion 94 taken at detail view 100 of FIG. Figure 4 In the aspect of FIG. 1 , the shroud structure 60 includes a single yoke inner shroud attachment flange 180 extending from an inner shroud flange root portion 182 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 4 In the aspect of the present invention, the inner shroud attachment flange 180 is generally arranged to extend from a central portion 184 of an inner shroud flange root portion 182. The inner shroud flange root portion 182 includes a first inner baffle wall portion 186 extending radially outward from an upstream end 190 of the inner shroud attachment flange 180 and a second inner baffle wall portion 188 extending radially inward from the upstream end 190 of the inner shroud attachment flange 180. The inner shroud attachment flange 180 also includes an inner shroud attachment flange opening 192 therethrough.

[0059] The CMC liner 52 includes an upstream end 196 (see also FIG. 1 ) of the CMC liner 52 in the longitudinal direction L. Figure 2 ) extends from the liner connection flange 194. Figure 4 In the aspect of FIG. 1 , the liner connection flange 194 includes a liner connection flange opening 198 therethrough. A liner connection flange bushing 200 can be installed within the liner connection flange opening 198 and includes a liner connection flange bushing opening 202 therethrough.

[0060] The CMC dome structure 56 includes an inner dome connection flange 57 extending from an inner side 204 of a dome plate 59 in a longitudinal direction L. The inner dome connection flange 57 includes an inner dome connection flange opening 206 therethrough. An inner dome connection flange bushing 208 can be mounted within the inner dome connection flange opening 206, and the inner dome connection flange bushing 208 includes an inner dome connection flange bushing opening 210 therethrough.

[0061] Figure 4The inner connector 94 of the embodiment of the present invention further includes a first inner connector bushing 212 and a second inner connector bushing 216. The first inner connector bushing 212 has an opening 220 therethrough, has an outer diameter 222, and has a flange 214. The second inner connector bushing 216 has an opening 224 therethrough, has an outer diameter 226, and has a flange 218. The outer diameter 222 of the first inner connector bushing 212 is slightly smaller than the inner diameter of the liner connection flange bushing opening 202. The first inner connector bushing 212 is inserted through the liner connection flange bushing opening 202 such that the liner connection flange bushing 200 and the first inner connector bushing 212 are slidably engaged with each other to allow radial movement of the CMC liner connection flange 194. Similarly, the outer diameter 226 of the second inner connector bushing 216 is slightly smaller than the inner diameter of the inner dome connection flange bushing opening 210. The second inner connector bushing 216 is inserted through the inner dome connection flange bushing opening 210 such that the inner dome connection flange bushing 208 and the second inner connector bushing 216 are slidingly engaged with each other to allow radial movement of the CMC inner dome connection flange 57 .

[0062] The inner connector fastener 228 (e.g., a bolt) includes a head 230 and a shank 232. The shank 232 is inserted through the opening 220 of the first inner connector bushing 212, through the inner shroud attachment flange opening 192, and through the opening 224 of the second inner connector bushing 216 until the head 230 engages the flange 214 of the first inner connector bushing 212. A retaining member 234 (e.g., a nut) is threadedly engaged with the shank 232 and torqued to engage an outer side 236 of the first inner connector bushing 212 with an inner side 238 of the inner shroud attachment flange 180 and an inner side 240 of the second inner connector bushing 216 with an outer side 242 of the inner shroud attachment flange 180.

[0063] therefore, Figure 4 The aforementioned arrangement provides an inner stacking arrangement 244 relative to the radial direction R, wherein the liner connection flange 194 is arranged on the inner side 246 of the inner stacking arrangement 224, the inner dome connection flange 57 is arranged on the outer side 248 of the inner stacking arrangement 244, and the inner cover connection flange 180 is arranged between the liner connection flange 194 and the inner dome connection flange 57.

[0064] Additionally, an upstream end 250 of the liner attachment flange 194 is disposed adjacent the second inner baffle wall portion 188 with a gap 252 therebetween such that the upstream end 250 of the liner attachment flange 194 and the second inner baffle wall portion 188 define a liner attachment flange baffle 254. The liner attachment flange baffle 254 acts as a seal to limit or restrict the amount of compressed air 87 that can pass from the inner flow passage 90 through the gap 252 and between the liner attachment flange 194 and the inner shroud attachment flange 180 into the combustion chamber 62.

[0065] Similarly, the upstream end 256 of the inner dome attachment flange 57 is disposed adjacent to the first inner baffle wall portion 186 with a gap 258 therebetween, such that the upstream end 256 of the inner dome attachment flange 57 and the first inner baffle wall portion 185 define an inner dome attachment flange baffle 260. The inner dome attachment flange baffle 260 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 252 and between the inner dome attachment flange 57 and the inner shroud attachment flange 180 into the combustion chamber 62.

[0066] Figure 5 Depicting aspects of the present disclosure Figure 3 An alternative external connection 92a is shown. Figure 5 In, with Figure 3 Elements identical to those of the aspects of FIG. 1 include the same reference numerals, and the same reference numerals are used for the elements of FIG. Figure 3 The description of those elements provided in the aspects also applies to Figure 5 In terms of Figure 5 In the aspect of FIG. 1 , the shroud structure 60 includes a single yoke shroud attachment flange 262 extending from a shroud flange root portion 264 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 5 In the aspect of the present invention, the shroud attachment flange 262 is generally arranged to extend from an outer portion 266 of a shroud flange root portion 264. The shroud flange root portion 264 includes an outer baffle wall portion 268 extending radially inward from an upstream end 270 of the shroud attachment flange 262. The shroud attachment flange 262 also includes a shroud attachment flange opening 272 therethrough.

[0067] The alternative outer connection 92a also includes an outer connection bushing 274 having an opening 276 therethrough, having an outer diameter 278, and having a flange 280 disposed on an inner side 282 of the outer connection bushing 274. The outer diameter 278 of the outer connection bushing 274 is slightly smaller than the inner diameter of the outer liner connection flange bushing opening 124 and slightly smaller than the inner diameter of the outer dome connection flange bushing opening 132, such that the outer liner connection flange bushing 122 and the outer dome connection flange bushing 130 slidingly engage the outer connection bushing 274. The outer side 284 of the outer connection bushing 274 is inserted through the outer dome connection flange bushing opening 132 and through the outer liner connection flange bushing opening 124 until the outer side 284 of the outer connection bushing 274 engages the inner side 286 of the outer shroud connection flange 262. Figure 52. The outer connector fastener 146 is implemented in an embodiment of the present invention to form the alternative outer connector 92a by inserting the shank 150 of the outer connector fastener 146 through the outer cover connection flange opening 272 and through the opening 276 of the outer connector bushing 274. The retaining member 152 is threadedly engaged with the shank 150 of the outer connector fastener 146 so that the head 148 of the outer connector fastener 146 engages the outer side 288 of the outer cover connection flange 262 and so that the retaining member 152 engages the flange 280 of the outer connector bushing 274. The retaining member 152 is torqued to tighten the connection.

[0068] therefore, Figure 5 The aforementioned arrangement provides an outer stacking arrangement 290 relative to the radial direction R, wherein the outer dome connection flange 55 is arranged on the inner side 292 of the outer stacking arrangement 290, the outer cover connection flange 262 is arranged on the outer side 294 of the outer stacking arrangement 290, and the outer liner connection flange 116 is arranged between the outer dome connection flange 55 and the outer cover connection flange 262.

[0069] Additionally, the upstream end 168 of the outer liner attachment flange 116 is disposed adjacent the outer baffle wall portion 268 with a gap 296 therebetween such that the upstream end 168 of the outer liner attachment flange 116 and the outer baffle wall portion 268 define an outer liner attachment flange baffle 298. The outer liner attachment flange baffle 298 acts as a seal to limit or restrict the amount of compressed air 85 that may pass from the outer flow passage 88 through the gap 296 and between the outer liner attachment flange 116 and the outer dome attachment flange 55 into the combustion chamber 62.

[0070] Similarly, the upstream end 174 of the outer dome attachment flange 55 is disposed adjacent the outer baffle wall portion 268 with a gap 300 therebetween such that the upstream end 174 of the outer dome attachment flange 55 and the outer baffle wall portion 268 define an outer dome attachment flange baffle 302. The outer dome attachment flange baffle 302 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 300 and between the outer dome attachment flange 55 and the outer liner attachment flange 116 into the combustion chamber 62.

[0071] Figure 6 Depicting aspects of the present disclosure Figure 3 An alternative inner connection 94a is shown. Figure 6 In, with Figure 4 Elements identical to those of the aspects of FIG. 1 include the same reference numerals, and the same reference numerals are used for the elements of FIG. Figure 4 The description of those elements provided in the aspects also applies to Figure 6 In terms of Figure 6In the aspect of FIG. 1 , the shroud structure 60 includes a single yoke inner shroud attachment flange 304 extending from an inner shroud flange root portion 306 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 6 In the aspect of FIG. 3 , the inner shroud attachment flange 304 is generally arranged to extend from an inner portion 308 of an inner shroud flange root portion 306. The inner shroud flange root portion 306 includes an inner baffle wall portion 310 extending radially outward from an upstream end 312 of the inner shroud attachment flange 304. The inner shroud attachment flange 304 also includes an inner shroud attachment flange opening 314 therethrough.

[0072] The alternative inner connection portion 94a also includes an inner connection portion bushing 316 having an opening 318 therethrough, having an outer diameter 320, and having a flange 322 disposed on an outer side 324 of the inner connection portion bushing 316. The outer diameter 320 of the inner connection portion bushing 316 is slightly smaller than the inner diameter of the inner liner connection flange bushing opening 202 and slightly smaller than the inner diameter of the inner dome connection flange bushing opening 210, such that the inner liner connection flange bushing 200 and the inner dome connection flange bushing 208 slidingly engage the inner connection portion bushing 316. The inner side 326 of the inner connection portion bushing 316 is inserted through the inner dome connection flange bushing opening 210 and through the inner liner connection flange bushing opening 202 until the inner side 326 of the inner connection portion bushing 316 engages the outer side 328 of the inner shroud connection flange 304. Figure 6 In an embodiment of the present invention, the inner connector fastener 228 is implemented to form the alternative inner connector 94a by inserting the shank 232 of the inner connector fastener 228 through the inner cover connection flange opening 314 and through the opening 318 of the inner connector bushing 316. The retaining member 234 is threadedly engaged with the shank 232 of the inner connector fastener 228 so that the head 230 of the inner connector fastener 228 engages the inner side 330 of the inner cover connection flange 304 and the retaining member 234 engages the flange 322 of the inner connector bushing 316. The retaining member 234 is torqued to tighten the connection.

[0073] therefore, Figure 6 The aforementioned arrangement provides an inner stacking arrangement 332 relative to the radial direction R, wherein the inner cover connection flange 304 is arranged on an inner side 334 of the inner stacking arrangement 332, the inner dome connection flange 57 is arranged on an outer side 336 of the inner stacking arrangement 332, and the liner connection flange 194 is arranged between the inner cover connection flange 304 and the inner dome connection flange 57.

[0074] Additionally, the upstream end 250 of the liner attachment flange 194 is disposed adjacent the inner baffle wall portion 310 with a gap 338 therebetween such that the upstream end 250 of the liner attachment flange 194 and the inner baffle wall portion 310 define a liner attachment flange baffle 340. The liner attachment flange baffle 340 acts as a seal to limit or restrict the amount of compressed air 87 that may pass from the inner flow passage 90 through the gap 338 and between the liner attachment flange 194 and the inner dome attachment flange 57 into the combustion chamber 62.

[0075] Similarly, the upstream end 256 of the inner dome attachment flange 57 is disposed adjacent the inner baffle wall portion 310 with a gap 342 therebetween such that the upstream end 256 of the inner dome attachment flange 57 and the inner baffle wall portion 310 define an inner dome attachment flange baffle 344. The inner dome attachment flange baffle 344 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 342 and between the inner dome attachment flange 57 and the liner attachment flange 194 into the combustion chamber 62.

[0076] Figure 7 Depicted according to aspects of the present disclosure Figure 3 An alternative external connection 92b is shown. Figure 7 In, with Figure 3 Elements identical to those of the aspects of FIG. 1 include the same reference numerals, and the same reference numerals are used for the elements of FIG. Figure 3 The description of those elements provided in the aspects also applies to Figure 7 In terms of Figure 7 In the aspect of FIG. 5 , the shroud structure 60 includes a single yoke shroud attachment flange 346 extending from a shroud flange root portion 348 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 7 In the aspect of the present invention, the shroud attachment flange 346 is generally arranged to extend from an inner portion 350 of a shroud flange root portion 348. The shroud flange root portion 348 includes an outer barrier wall portion 352 extending radially outward from an upstream end 354 of the shroud attachment flange 346. The shroud attachment flange 346 also includes a shroud attachment flange opening 356 therethrough.

[0077] The alternative outer connection 92b also includes an outer connection bushing 358 having an opening 360 therethrough, an outer diameter 362, and a flange 364 disposed on an outer side 366 of the outer connection bushing 358. The outer diameter 362 of the outer connection bushing 358 is slightly smaller than the inner diameter of the outer liner connection flange bushing opening 124 and slightly smaller than the inner diameter of the outer dome connection flange bushing opening 132, such that the outer liner connection flange bushing 122 and the outer dome connection flange bushing 130 slidingly engage the outer connection bushing 356. The inner side 368 of the outer connection bushing 358 is inserted through the outer liner connection flange bushing opening 124 and through the outer dome connection flange bushing opening 132 until the inner side 368 of the outer connection bushing 358 engages the outer side 370 of the outer shroud connection flange 346. Figure 7 3. The outer connection fastener 146 is implemented in an embodiment of the present invention to form the alternative outer connection 92b by inserting the shank 150 of the outer connection fastener 146 through the outer cover connection flange opening 356 and through the opening 360 of the outer connection bushing 358. The retaining member 152 is threadedly engaged with the shank 150 of the outer connection fastener 146 so that the head 148 of the outer connection fastener 146 engages the inner side 372 of the outer cover connection flange 346 and so that the retaining member 152 engages the flange 364 of the outer connection bushing 358. The retaining member 152 is torqued to tighten the connection.

[0078] therefore, Figure 7 The aforementioned arrangement provides an outer stacking arrangement 374 relative to the radial direction R, wherein the outer cover connection flange 346 is arranged on the inner side 376 of the outer stacking arrangement 374, the outer liner connection flange 116 is arranged on the outer side 378 of the outer stacking arrangement 374, and the inner dome connection flange 55 is arranged between the outer cover connection flange 346 and the outer liner connection flange 116.

[0079] Additionally, the upstream end 168 of the outer liner attachment flange 116 is disposed adjacent the outer baffle wall portion 352 with a gap 380 therebetween such that the upstream end 168 of the outer liner attachment flange 116 and the outer baffle wall portion 352 define an outer liner attachment flange baffle 382. The outer liner attachment flange baffle 382 acts as a seal to limit or restrict the amount of compressed air 85 that may pass from the outer flow passage 88 through the gap 380 and between the outer liner attachment flange 116 and the outer dome attachment flange 55 into the combustion chamber 62.

[0080] Similarly, the upstream end 174 of the outer dome attachment flange 55 is disposed adjacent the outer baffle wall portion 352 with a gap 384 therebetween such that the upstream end 174 of the outer dome attachment flange 55 and the outer baffle wall portion 352 define an outer dome attachment flange baffle 386. The outer dome attachment flange baffle 386 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 384 and between the outer dome attachment flange 55 and the outer liner attachment flange 116 into the combustion chamber 62.

[0081] Figure 8 Depicted according to aspects of the present disclosure Figure 4 An alternative inner connection 94b is shown. Figure 8 In, with Figure 4 Elements identical to those of the aspects of FIG. 1 include the same reference numerals, and the same reference numerals are used for the elements of FIG. Figure 4 The description of those elements provided in the aspects also applies to Figure 8 In terms of Figure 8 In the aspect of FIG. 1 , the shroud structure 60 includes a single yoke inner shroud attachment flange 388 extending from an inner shroud flange root portion 390 of the shroud structure 60 in a longitudinal direction L relative to the combustor centerline axis 12 ′. Figure 8 In the aspect of the present invention, the inner shroud attachment flange 388 is generally arranged to extend from an outer portion 392 of an inner shroud flange root portion 390. The inner shroud flange root portion 390 includes an inner baffle wall portion 394 extending radially inward from an upstream end 396 of the inner shroud attachment flange 388. The inner shroud attachment flange 388 also includes an inner shroud attachment flange opening 398 therethrough.

[0082] The alternative inner connector 94b also includes an inner connector bushing 400 having an opening 402 therethrough, having an outer diameter 404, and having a flange 406 disposed on an inner side 408 of the inner connector bushing 400. The outer diameter 404 of the inner connector bushing 400 is slightly smaller than the inner diameter of the liner connection flange bushing opening 202 and slightly smaller than the inner diameter of the inner dome connection flange bushing opening 210 such that the liner connection flange bushing 200 and the inner dome connection flange bushing 208 slidingly engage the inner connector bushing 400. The outer side 410 of the inner connector bushing 400 is inserted through the liner connection flange bushing opening 202 and through the inner dome connection flange bushing opening 210 until the outer side 410 of the inner connector bushing 400 engages the inner side 412 of the inner shroud connection flange 388. Figure 894b by inserting the shank 232 of the inner connector fastener 228 through the inner shroud connection flange opening 398 and through the opening 402 of the inner connector bushing 400. The retaining member 234 is threadedly engaged with the shank 232 of the inner connector fastener 228 so that the head 230 of the inner connector fastener 228 engages the outer side 414 of the inner shroud connection flange 388 and the retaining member 234 engages the flange 406 of the inner connector bushing 400. The retaining member 234 is torqued to tighten the connection.

[0083] therefore, Figure 8 The aforementioned arrangement provides an inner stacking arrangement 416 relative to the radial direction R, wherein the liner connection flange 194 is arranged on an inner side 418 of the inner stacking arrangement 416, the inner cover connection flange 388 is arranged on an outer side 420 of the inner stacking arrangement 416, and the inner dome connection flange 57 is arranged between the liner connection flange 194 and the inner cover connection flange 388.

[0084] Additionally, the upstream end 250 of the liner attachment flange 194 is disposed adjacent the inner baffle wall portion 394 with a gap 422 therebetween such that the upstream end 250 of the liner attachment flange 194 and the inner baffle wall portion 394 define a liner attachment flange baffle 424. The liner attachment flange baffle 424 acts as a seal to limit or restrict the amount of compressed air 87 that may pass from the inner flow passage 90 through the gap 422 and between the liner attachment flange 194 and the inner dome attachment flange 57 into the combustion chamber 62.

[0085] Similarly, the upstream end 256 of the inner dome attachment flange 57 is disposed adjacent the inner baffle wall portion 394 with a gap 426 therebetween such that the upstream end 256 of the inner dome attachment flange 57 and the inner baffle wall portion 394 define an inner dome attachment flange baffle 428. The inner dome attachment flange baffle 428 acts as a seal to limit or restrict the amount of compressed air 83 that can pass from the plenum 66 through the gap 426 and between the inner dome attachment flange 57 and the liner attachment flange 194 into the combustion chamber 62.

[0086] Figures 9 to 17 Various combinations of outer and inner connections are depicted for connecting the shroud structure 60, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 in the combustion section 26. Figures 9 to 17 In, with Figure 2 The swirler assembly 58 is shown schematically as compared to the illustrated swirler assembly 58 , with the fuel nozzle assembly 70 removed solely to enhance clarity of the remaining structure. Figure 9 According to aspects of the present disclosure Figure 2 Detail of the figure 430 intercepted Figure 2 A partial cross-sectional view of a portion of the combustion section 26 of FIG. Figure 9 In FIG. 1 , the cover structure 60 includes an outer cover connection flange 102 and an inner cover connection flange 180. The cover structure 60, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via an outer connection 92 and via an inner connection 94. The outer connection 92 corresponds to Figure 3 and the inner connection portion 94 corresponds to Figure 4 Thus, the outer connection 92 includes an outer stacking arrangement 162 ( Figure 3 ), and the inner connection portion 94 includes an inner stacking arrangement 244 ( Figure 4 ).

[0087] Figure 10 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26a is an alternative to the combustion section shown. Figure 10 In FIG. 5 , the alternative cover structure 60a includes an outer cover connection flange 346 and an inner cover connection flange 180. The alternative cover structure 60a, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection 92b and via inner connection 94. The outer connection 92b corresponds to Figure 7 and the inner connection portion 94 corresponds to Figure 4 Thus, the outer connection 92b includes an outer stacking arrangement 374 ( Figure 7 ), and the inner connection portion 94 includes an inner stacking arrangement 244 ( Figure 4 ).

[0088] Figure 11 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26b is an alternative to the combustion section shown. Figure 11 In FIG. 5 , the alternative cover structure 60b includes an outer cover connection flange 262 and an inner cover connection flange 180. The alternative cover structure 60b, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection portions 92a and via inner connection portions 94. The outer connection portions 92a correspond to Figure 5 and the inner connection portion 94 corresponds to Figure 4 Thus, the outer connection 92a includes an outer stacking arrangement 290 ( Figure 5 ), and the inner connection portion 94 includes an inner stacking arrangement 244 ( Figure 4 ).

[0089] Figure 12 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26c is an alternative to the combustion section shown. Figure 12In FIG. 5 , the alternative cover structure 60c includes an outer cover connection flange 102 and an inner cover connection flange 304. The alternative cover structure 60c, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection 92 and via inner connection 94a. The outer connection 92 corresponds to Figure 3 aspect, and the inner connecting portion 94a corresponds to Figure 6 Thus, the outer connection 92 includes an outer stacking arrangement 162 ( Figure 3 ), and the inner connection portion 94a includes an inner stacking arrangement 332 ( Figure 6 ).

[0090] Figure 13 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26d is an alternative to the combustion section shown. Figure 13 In FIG. 5 , the alternative cover structure 60 d includes an outer cover connection flange 346 and an inner cover connection flange 304 . The alternative cover structure 60 d , the CMC dome structure 56 , the CMC outer liner 54 , and the CMC inner liner 52 are connected together via outer connection 92 b and via inner connection 94 a . The outer connection 92 b corresponds to Figure 7 aspect, and the inner connecting portion 94a corresponds to Figure 6 Thus, the outer connection 92b includes an outer stacking arrangement 374 ( Figure 7 ), and the inner connection portion 94a includes an inner stacking arrangement 332 ( Figure 6 ).

[0091] Figure 14 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26e is an alternative to the combustion section shown. Figure 14 In FIG. 5 , the alternative cover structure 60e includes an outer cover connection flange 262 and an inner cover connection flange 304. The alternative cover structure 60e, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection portions 92a and via inner connection portions 94a. The outer connection portion 92a corresponds to Figure 5 aspect, and the inner connecting portion 94a corresponds to Figure 6 Thus, the outer connection 92a includes an outer stacking arrangement 290 ( Figure 5 ), and the inner connection portion 94 includes an inner stacking arrangement 332 ( Figure 6 ).

[0092] Figure 15 Depicted according to aspects of the present disclosure Figure 9 The arrangement of the combustion section 26f is an alternative to the combustion section shown. Figure 15In FIG. 5 , the alternative cover structure 60 f includes an outer cover connection flange 102 and an inner cover connection flange 388. The alternative cover structure 60 f, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection 92 and via inner connection 94 b. The outer connection 92 corresponds to Figure 3 , and the inner connecting portion 94b corresponds to Figure 8 Thus, the outer connection 92 includes an outer stacking arrangement 162 ( Figure 3 ), and the inner connection portion 94b includes an inner stacking arrangement 416 ( Figure 8 ).

[0093] Figure 16 Depicting aspects of the present disclosure Figure 9 The arrangement of the combustion section 26g is an alternative to the combustion section shown. Figure 10 In FIG. 5 , the alternative cover structure 60 g includes an outer cover connection flange 346 and an inner cover connection flange 388. The alternative cover structure 60 g, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection portions 92 b and via inner connection portions 94 b. The outer connection portions 92 b correspond to Figure 7 , and the inner connecting portion 94b corresponds to Figure 8 Thus, the outer connection 92b includes an outer stacking arrangement 374 ( Figure 7 ), and the inner connection portion 94b includes an inner stacking arrangement 416 ( Figure 8 ).

[0094] Figure 17 Depicting aspects of the present disclosure Figure 9 The arrangement of the combustion section 26h is an alternative to the combustion section shown. Figure 17 In FIG. 5 , the alternative cover structure 60h includes an outer cover connection flange 262 and an inner cover connection flange 388. The alternative cover structure 60h, the CMC dome structure 56, the CMC outer liner 54, and the CMC inner liner 52 are connected together via outer connection 92a and via inner connection 94b. The outer connection 92a corresponds to Figure 5 , and the inner connecting portion 94b corresponds to Figure 8 Thus, the outer connection 92a includes an outer stacking arrangement 290 ( Figure 5 ), and the inner connection portion 94b includes an inner stacking arrangement 416 ( Figure 8 ).

[0095] The aforementioned aspects provide different, yet similar, techniques for connecting a CMC dome structure and a CMC liner to a metal shroud structure within the combustion section of a gas turbine engine. The inclusion of single-yoke connection flanges on both the outside and inside of the metal shroud structure provides the ability to implement a variety of connection arrangements not possible with conventional double-yoke (or clevis-type) shroud connection flanges. The reduced number of connection flanges on the metal shroud structure also reduces the overall weight of the combustor and also reduces the radial height of the combustion section at the connection.

[0096] While the above description generally relates to gas turbine engines, gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0097] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0098] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner, The CMC outer liner includes an outer liner connection flange extending at an upstream end of the CMC outer liner in the longitudinal direction; a CMC inner liner including an inner liner connection flange extending in the longitudinal direction; an outer connection portion connecting the outer dome connection flange, the outer cover connection flange, and the outer liner connection flange in an outer stacking arrangement relative to a radial direction extending outward from the combustor centerline axis; and an inner connection portion connecting the inner dome connection flange, the inner cover connection flange, and the inner liner connection flange in an inner stacking arrangement extending in the radial direction.

[0099] A combustor according to the preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0100] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0101] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0102] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0103] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0104] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0105] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0106] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0107] A combustor according to any preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0108] The combustor of any preceding clause, wherein the outer shroud flange root portion includes an outer baffle wall portion extending radially inwardly from an upstream end of the outer shroud attachment flange, the upstream end of the outer liner attachment flange being disposed adjacent the outer baffle wall portion to define an outer liner attachment flange baffle, and the upstream end of the outer dome attachment flange being disposed adjacent the outer baffle wall portion to define an outer dome attachment flange baffle.

[0109] The combustor of any preceding clause, wherein the outer shroud flange root portion includes an outer baffle wall portion extending radially outward from an upstream end of the outer shroud attachment flange, the upstream end of the outer liner attachment flange being disposed adjacent the outer baffle wall portion to define an outer liner attachment flange baffle, and the upstream end of the outer dome attachment flange being disposed adjacent the outer baffle wall portion to define an outer dome attachment flange baffle.

[0110] The combustor of any preceding clause, wherein the inner shroud flange root portion includes an inner baffle wall portion extending radially inwardly from an upstream end of the inner shroud attachment flange, the upstream end of the liner attachment flange being disposed adjacent the inner baffle wall portion to define a liner attachment flange baffle, and the upstream end of the inner dome attachment flange being disposed adjacent the inner baffle wall portion to define an inner dome attachment flange baffle.

[0111] The combustor of any preceding clause, wherein the inner shroud flange root portion includes an inner baffle wall portion extending radially outward from an upstream end of the inner shroud attachment flange, the upstream end of the liner attachment flange being disposed adjacent the inner baffle wall portion to define an inner liner attachment flange baffle, and the upstream end of the inner dome attachment flange being disposed adjacent the inner baffle wall portion to define an inner dome attachment flange baffle.

[0112] The combustor of any preceding clause, wherein the outer connector comprises at least one outer connector bushing extending through at least one of the outer liner attachment flange and the outer dome attachment flange, an outer connector fastener extending through the at least one outer connector bushing, and a retaining member connected to the outer connector fastener.

[0113] The combustor of any preceding clause, wherein the at least one outer connector liner comprises a first outer connector liner and a second outer connector liner.

[0114] The combustor according to any preceding clause, wherein an inner side of the first outer connector bushing contacts an outer side of the outer shroud attachment flange, an outer side of the first outer connector bushing contacts a head of the outer connector fastener, an outer side of the second outer connector bushing contacts an inner side of the outer shroud attachment flange, and an inner side of the second outer connector bushing contacts a retaining member.

[0115] The combustor of any preceding clause, wherein the at least one inner connector liner comprises a first inner connector liner and a second inner connector liner.

[0116] The combustor according to any preceding clause, wherein an inner side of the first inner connector liner contacts an outer side of the inner shroud attachment flange, an outer side of the first inner connector liner contacts a retaining member, an outer side of the second outer connector liner contacts an inner side of the inner shroud attachment flange, and an inner side of the second outer connector liner contacts a head of the inner connector fastener.

[0117] The combustor of any preceding clause, wherein the at least one outer connector liner comprises an outer connector liner extending through the outer dome attachment flange and the outer liner attachment flange, an outer side of the outer connector liner engaging an inner side of the outer shroud attachment flange, and an inner side of the outer connector liner engaging one of a head of an outer connector fastener or a retaining member.

[0118] The combustor of any preceding clause, wherein the at least one inner connector liner comprises an inner connector liner extending through the inner dome attachment flange and the inner liner attachment flange, an inner side of the inner connector liner engaging an outer side of the inner shroud attachment flange, and an outer side of the inner connector liner engaging one of a head of an inner connector fastener or a retaining member.

[0119] The combustor of any preceding clause, wherein the inner connector comprises at least one inner connector bushing extending through at least one of the liner attachment flange and the inner dome attachment flange, an inner connector fastener extending through the at least one inner connector bushing, and a retaining member connected to the inner connector fastener.

[0120] The combustor of any preceding clause, wherein the shroud flange root portion includes a first outer baffle wall portion extending radially outward from an upstream end of the shroud attachment flange, and a second outer baffle wall portion extending radially inward from the upstream end of the shroud attachment flange.

[0121] The combustor of any preceding clause, wherein the upstream end of the outer liner attachment flange is disposed adjacent the first outer baffle wall portion to define an outer liner attachment flange baffle, and the upstream end of the outer dome attachment flange is disposed adjacent the second outer baffle wall portion to define an outer dome attachment flange baffle.

[0122] The combustor of any preceding clause, wherein the inner shroud flange root portion includes a first inner baffle wall portion extending radially outward from an upstream end of the inner shroud attachment flange, and a second inner baffle wall portion extending radially inward from the upstream end of the inner shroud attachment flange.

[0123] The combustor of any preceding clause, wherein the upstream end of the liner attachment flange is disposed adjacent the second inner baffle wall portion to define a liner attachment flange baffle, and the upstream end of the inner dome attachment flange is disposed adjacent the first inner baffle wall portion to define an inner dome attachment flange baffle.

[0124] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer liner connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner dome connecting flange.

[0125] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer cover connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer cover connecting flange and the outer liner connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner dome connecting flange and the inner dome connecting flange.

[0126] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer cover connecting flange arranged on the outer side of the outer stacking arrangement, and the outer liner connecting flange arranged between the outer dome connecting flange and the outer cover connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner dome connecting flange and the inner dome connecting flange.

[0127] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer liner connecting flange, and the inner stacking arrangement includes the inner cover connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner cover connecting flange and the inner dome connecting flange.

[0128] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer cover connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer cover connecting flange and the outer liner connecting flange, and the inner stacking arrangement includes the inner cover connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner cover connecting flange and the inner dome connecting flange.

[0129] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer cover connecting flange arranged on the outer side of the outer stacking arrangement, and the outer liner connecting flange arranged between the outer dome connecting flange and the outer cover connecting flange, and the inner stacking arrangement includes the inner cover connecting flange arranged on the inner side of the inner stacking arrangement, the inner dome connecting flange arranged on the outer side of the inner stacking arrangement, and the inner liner connecting flange arranged between the inner cover connecting flange and the inner dome connecting flange.

[0130] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer liner connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner cover connecting flange arranged on the outer side of the inner stacking arrangement, and the inner dome connecting flange arranged between the inner liner connecting flange and the inner cover connecting flange.

[0131] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to the combustor centerline axis. An outer stacking arrangement in a radial direction extending outward from a centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer cover connecting flange arranged on the inner side of the outer stacking arrangement, the outer liner connecting flange arranged on the outer side of the outer stacking arrangement, and the outer dome connecting flange arranged between the outer cover connecting flange and the outer liner connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner cover connecting flange arranged on the outer side of the inner stacking arrangement, and the inner dome connecting flange arranged between the inner liner connecting flange and the inner cover connecting flange.

[0132] A combustor for a gas turbine engine, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure comprising an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner comprising an outer liner connection flange extending in the longitudinal direction at an upstream end of the CMC outer liner; a CMC inner liner comprising an inner liner connection flange extending in the longitudinal direction; an outer connection portion extending in a longitudinal direction relative to an axis extending from the combustor centerline. An outer stacking arrangement in a radial direction extending outward from the centerline axis connects the outer dome connecting flange, the outer cover connecting flange and the outer liner connecting flange; and an inner connecting portion, the inner connecting portion connects the inner dome connecting flange, the inner cover connecting flange and the inner liner connecting flange in an inner stacking arrangement extending in the radial direction, wherein the outer stacking arrangement includes the outer dome connecting flange arranged on the inner side of the outer stacking arrangement, the outer cover connecting flange arranged on the outer side of the outer stacking arrangement, and the outer liner connecting flange arranged between the outer dome connecting flange and the outer cover connecting flange, and the inner stacking arrangement includes the inner liner connecting flange arranged on the inner side of the inner stacking arrangement, the inner cover connecting flange arranged on the outer side of the inner stacking arrangement, and the inner dome connecting flange arranged between the inner liner connecting flange and the inner cover connecting flange.

[0133] A gas turbine engine includes a compressor section, a turbine section, and a combustion section that receives an airflow from the compressor section, the airflow being provided to a combustion chamber within a combustor of the combustion section, the combustor comprising: a ceramic matrix composite (CMC) dome structure, the CMC dome structure including an outer dome connection flange extending from an outer side of a dome plate in a longitudinal direction relative to a centerline axis of the combustor and an inner dome connection flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure including a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and an inner shroud connection flange extending from an inner side of the shroud structure in the longitudinal direction. a single-yoke inner cover connection flange extending from a root portion of the cover flange; a CMC outer liner, the CMC outer liner including an outer liner connection flange extending at an upstream end of the CMC outer liner in the longitudinal direction; a CMC inner liner, the CMC inner liner including an inner liner connection flange extending in the longitudinal direction; an outer connection portion connecting the outer dome connection flange, the outer cover connection flange and the outer liner connection flange in an outer stacking arrangement relative to a radial direction extending outward from a centerline axis of the combustor; and an inner connection portion connecting the inner dome connection flange, the inner cover connection flange and the inner liner connection flange in an inner stacking arrangement extending in the radial direction.

[0134] A gas turbine engine according to the preceding clause, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0135] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0136] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

[0137] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0138] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0139] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

[0140] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0141] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0142] A gas turbine engine according to any of the preceding clauses, wherein the outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

[0143] A gas turbine engine according to any preceding clause, wherein the outer shroud flange root portion includes an outer baffle wall portion extending radially inwardly from an upstream end of the outer shroud attachment flange, the upstream end of the outer liner attachment flange is arranged adjacent to the outer baffle wall portion to define an outer liner attachment flange baffle, and the upstream end of the outer dome attachment flange is arranged adjacent to the outer baffle wall portion to define an outer dome attachment flange baffle.

[0144] A gas turbine engine according to any preceding clause, wherein the outer shroud flange root portion includes an outer baffle wall portion extending radially outward from an upstream end of the outer shroud attachment flange, the upstream end of the outer liner attachment flange is arranged adjacent to the outer baffle wall portion to define an outer liner attachment flange baffle, and the upstream end of the outer dome attachment flange is arranged adjacent to the outer baffle wall portion to define an outer dome attachment flange baffle.

[0145] A gas turbine engine according to any preceding clause, wherein the inner shroud flange root portion includes an inner baffle wall portion extending radially inwardly from an upstream end of the inner shroud attachment flange, the upstream end of the liner attachment flange is arranged adjacent to the inner baffle wall portion to define a liner attachment flange baffle, and the upstream end of the inner dome attachment flange is arranged adjacent to the inner baffle wall portion to define an inner dome attachment flange baffle.

[0146] A gas turbine engine according to any preceding clause, wherein the inner shroud flange root portion includes an inner baffle wall portion extending radially outward from an upstream end of the inner shroud attachment flange, the upstream end of the liner attachment flange is arranged adjacent to the inner baffle wall portion to define a liner attachment flange baffle, and the upstream end of the inner dome attachment flange is arranged adjacent to the inner baffle wall portion to define an inner dome attachment flange baffle.

[0147] A gas turbine engine according to any preceding clause, wherein the outer connection portion includes at least one outer connection portion bushing extending through at least one of the outer liner connection flange and the outer dome connection flange, an outer connection portion fastener extending through the at least one outer connection portion bushing, and a retaining member connected to the outer connection portion fastener.

[0148] A gas turbine engine according to any preceding clause, wherein the inner connection portion includes at least one inner connection portion bushing extending through at least one of the liner connection flange and the inner dome connection flange, an inner connection portion fastener extending through the at least one inner connection portion bushing, and a retaining member connected to the inner connection portion fastener.

[0149] A gas turbine engine according to any preceding clause, wherein the shroud flange root portion includes a first outer barrier wall portion extending radially outward from an upstream end of the shroud attachment flange, and a second outer barrier wall portion extending radially inward from the upstream end of the shroud attachment flange.

[0150] A gas turbine engine according to any preceding clause, wherein the upstream end of the outer liner attachment flange is arranged adjacent to the first outer blocker wall portion to define an outer liner attachment flange blocker, and the upstream end of the outer dome attachment flange is arranged adjacent to the second outer blocker wall portion to define an outer dome attachment flange blocker.

[0151] The gas turbine engine according to any preceding clause, wherein the inner shroud flange root portion includes a first inner baffle wall portion extending radially outward from an upstream end of the inner shroud attachment flange, and a second inner baffle wall portion extending radially inward from the upstream end of the inner shroud attachment flange.

[0152] A gas turbine engine according to any preceding clause, wherein the upstream end of the liner attachment flange is arranged adjacent to the second inner baffle wall portion to define a liner attachment flange baffle, and the upstream end of the inner dome attachment flange is arranged adjacent to the first inner baffle wall portion to define an inner dome attachment flange baffle.

[0153] The gas turbine engine of any preceding clause, wherein the at least one outer connector liner comprises a first outer connector liner and a second outer connector liner.

[0154] A gas turbine engine according to any preceding clause, wherein an inner side of the first outer connection part bushing contacts an outer side of the outer cover connection flange, an outer side of the first outer connection part bushing contacts a head of the outer connection part fastener, an outer side of the second outer connection part bushing contacts an inner side of the outer cover connection flange, and an inner side of the second outer connection part bushing contacts a retaining member.

[0155] The gas turbine engine of any preceding clause, wherein the at least one inner connector liner comprises a first inner connector liner and a second inner connector liner.

[0156] A gas turbine engine according to any preceding clause, wherein an inner side of the first inner connector bushing contacts an outer side of the inner shroud attachment flange, an outer side of the first inner connector bushing contacts a retaining member, an outer side of the second outer connector bushing contacts an inner side of the inner shroud attachment flange, and an inner side of the second outer connector bushing contacts a head of the inner connector fastener.

[0157] A gas turbine engine according to any preceding clause, wherein the at least one outer connector bushing comprises an outer connector bushing extending through the outer dome connection flange and the outer liner connection flange, the outer side of the outer connector bushing engaging the inner side of the outer shroud connection flange, and the inner side of the outer connector bushing engaging one of a head of an outer connector fastener or a retaining member.

[0158] A gas turbine engine according to any preceding clause, wherein the at least one inner connector liner comprises an inner connector liner extending through the inner dome connection flange and the inner liner connection flange, an inner side of the inner connector liner engaging an outer side of the inner shroud connection flange, and an outer side of the inner connector liner engaging one of a head of an inner connector fastener or a retaining member.

[0159] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, other changes and modifications are obvious to those skilled in the art and may be made without departing from the present disclosure. In addition, features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner for a gas turbine engine, characterized in that: The burner comprises: a ceramic matrix composite (CMC) dome structure comprising an outer dome attachment flange extending from an outer side of a dome plate in a longitudinal direction relative to a combustor centerline axis and an inner dome attachment flange extending from an inner side of the dome plate in the longitudinal direction; a shroud structure comprising a single-yoke outer shroud connection flange extending from a root portion of an outer shroud flange of the shroud structure in the longitudinal direction and a single-yoke inner shroud connection flange extending from a root portion of an inner shroud flange of the shroud structure in the longitudinal direction; a CMC outer liner including an outer liner connection flange extending at an upstream end of the CMC outer liner in the longitudinal direction; a CMC liner including a liner connection flange extending at an upstream end of the CMC liner in the longitudinal direction; an outer connection portion connecting the outer dome connection flange, the outer shroud connection flange, and the outer liner connection flange in an outer stacked arrangement with respect to a radial direction extending outward from the combustor centerline axis; and An inner connecting portion connects the inner dome connecting flange, the inner shroud connecting flange, and the inner liner connecting flange in an inner stacked arrangement extending in the radial direction.

2. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

3. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

4. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner cover connection flange arranged between the inner liner connection flange and the inner dome connection flange.

5. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

6. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

7. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner cover connection flange arranged on the inner side of the inner stacking arrangement, the inner dome connection flange arranged on the outer side of the inner stacking arrangement, and the inner liner connection flange arranged between the inner cover connection flange and the inner dome connection flange.

8. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer cover connection flange arranged between the outer dome connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

9. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer cover connection flange arranged on the inner side of the outer stacking arrangement, the outer liner connection flange arranged on the outer side of the outer stacking arrangement, and the outer dome connection flange arranged between the outer cover connection flange and the outer liner connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

10. The burner according to claim 1, characterized in that in, The outer stacking arrangement includes the outer dome connection flange arranged on the inner side of the outer stacking arrangement, the outer cover connection flange arranged on the outer side of the outer stacking arrangement, and the outer liner connection flange arranged between the outer dome connection flange and the outer cover connection flange, and the inner stacking arrangement includes the inner liner connection flange arranged on the inner side of the inner stacking arrangement, the inner cover connection flange arranged on the outer side of the inner stacking arrangement, and the inner dome connection flange arranged between the inner liner connection flange and the inner cover connection flange.

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