Combustor dome assembly

Abstract

A combustor dome assembly includes an inner liner, an outer liner, a dome disposed on the inner liner and the outer liner, and a fairing coupled to the inner liner and the outer liner, wherein the dome is disconnected from the fairing and defines an annular surface facing the fairing that extends from an outer diameter of the dome to an inner diameter of the dome.

Description

Technical Field

[0001] This disclosure relates to a combustor dome assembly for a gas turbine engine. Background Technology

[0002] The combustor in a turbine engine receives a mixture of fuel and highly compressed air, which is ignited to produce hot combustion gases. These hot gases are used to provide torque in the turbine, thus providing mechanical power and thrust. A typical combustor layout is at least partially constructed of metal, which is heavy and requires multi-layered wall structures and advanced cooling to protect the combustor from extremely high temperatures. The expansion of the metal at high temperatures also creates gaps, interfering with airflow and reducing fuel efficiency. Attached Figure Description

[0003] The complete and enabling disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings for those skilled in the art, wherein:

[0004] Figure 1 This is a schematic diagram of a gas turbine engine.

[0005] Figure 2 This is a schematic diagram of the burner dome assembly.

[0006] Figure 3 This is a front and rear view of the burner dome assembly.

[0007] Figure 4 This is a front and rear view of another burner dome assembly.

[0008] Figure 5 This is a front and rear view of another burner dome assembly. Detailed Implementation

[0009] Reference will now be made in detail to the present embodiments of this disclosure, one or more of which are illustrated in the accompanying drawings. Detailed description uses numerical and letter names to refer to features in the drawings. The same or similar names in the drawings and description have been used to refer to the same or similar parts of this disclosure.

[0010] As used herein, the term "exemplary" means "as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0011] The singular forms “one,” “a,” and “the” include plural references unless the context clearly indicates otherwise.

[0012] The terms "outer" and "inner" refer to relative positions within a turbine engine, measured from the engine's centerline. For example, "outer" refers to a position farther from the centerline, while "inner" refers to a position closer to the centerline.

[0013] As used in this article, the terms “first,” “second,” “third,” and other ordinal numbers are used to distinguish one component from another and are not intended to indicate the position or importance of the components.

[0014] In this article, “metal” refers to pure metals or metal alloys, excluding other compounds containing metal elements, such as metal oxides (e.g., aluminum oxide, titanium oxide, etc.) or metal salts (e.g., sodium chloride).

[0015] As used herein, ceramic matrix composites or “CMCs” refer to composite materials comprising a ceramic matrix reinforced with ceramic fibers. Some examples of CMCs acceptable for use herein include, but are not limited to, materials having a matrix and reinforcing fibers composed of oxides, carbides, nitrides, oxycarbides, oxynitrides, and mixtures thereof. Examples of non-oxide materials include, but are not limited to: CMCs having a silicon carbide matrix and silicon carbide fibers (which, when manufactured by silicon melt infiltration, will contain residual free silicon); silicon carbide / silicon matrix mixtures and silicon carbide fibers; silicon nitride matrix and silicon carbide fibers; and silicon carbide / silicon nitride matrix mixtures and silicon carbide fibers. Furthermore, CMCs may have a matrix and reinforcing fibers composed of oxide ceramics. Specifically, oxide-oxide CMCs may consist of a matrix and reinforcing fibers comprising oxide-based materials such as alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, and mixtures thereof. Therefore, as used herein, the term "ceramic matrix composite" includes, but is not limited to, carbon fiber reinforced carbon (C / C), carbon fiber reinforced silicon carbide (C / SiC), and silicon carbide fiber reinforced silicon carbide (SiC / SiC). In one embodiment, ceramic matrix composites exhibit increased elongation, fracture toughness, thermal shock resistance, and anisotropic properties compared to (unreinforced) monolithic ceramic structures.

[0016] This disclosure generally relates to combustor dome assemblies for gas turbine engines. The use of CMC materials in combustor designs is ideal because CMC materials have a higher heat capacity than metals. Although some combustor designs have incorporated CMC for parts of the combustor, these designs still rely on metal-made domes and other combustor components. The advantages of using CMC in the dome design include, but are not limited to: reduced cooling, weight reduction, and shorter combustor length due to the replacement of heavier metal components and a simplified internal design. Incorporating CMC materials can also improve airflow control by eliminating attachment gaps between the dome and bushing, reduce weight by eliminating additional deflectors, and reduce dome cooling. Domes are typically attached to metal components, such as cowlings, which can introduce temperature gradients and thermal stresses during operation.

[0017] The dome is formed using CMC material with a substantially flat surface and spaced apart from the cowling, reducing the overall thickness of the dome and thus lowering the temperature gradient and thermal stress. A pressure seal is formed to secure the dome to the bushing of the combustor dome assembly, pressing the dome against the bushing. Specifically, the dome is designed with a front and a rear section, with the front section having a larger annular shape than the rear section. Increased gas pressure upstream of the combustor holds the front section of the dome against the bushing, allowing the dome to be attached to the cowling with fewer or no fasteners. In this configuration, the overall profile of the dome is reduced, allowing the combustor dome assembly to operate with less thermal stress.

[0018] Referring now to the accompanying drawings, where the same numbers denote the same elements in each figure, Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In one embodiment, the gas turbine engine is a high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." For example... Figure 1 As shown, the gas turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline 12 provided for reference), a radial direction R perpendicular to the longitudinal centerline 12, and a circumferential direction C extending about the longitudinal centerline 12. Generally, the gas turbine engine 10 includes a fan section 14 and a turbine 16, the turbine 16 being disposed downstream of the fan section 14 in the axial direction A.

[0019] The depicted exemplary turbine 16 typically includes a generally tubular outer casing 18 defining an annular inlet 20. The casing 18 encloses a compressor section in a series flow sequence, including a supercharger or low-pressure (LP) compressor 22, a high-pressure (HP) compressor 24, and a core conduit located between the LP compressor 22 and the HP compressor 24; a combustion section 26; a turbine section including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30; and a turbine exhaust nozzle 32. A high-pressure (HP) shaft 34 (which may additionally or alternatively be a spool) drives the HP turbine 28 to the HP compressor 24. A low-pressure (LP) shaft 36 (which may additionally or alternatively be a spool) drives the LP turbine 30 to the LP compressor 22. The compressor section, combustion section 26, turbine section, and turbine exhaust nozzle 32 collectively define a working gas flow path 37.

[0020] In the depicted embodiment, fan section 14 includes a fan 38 having a plurality of fan blades 40 spaced apart and coupled to disk 42. As shown, the fan blades 40 extend generally radially outward from disk 42. Each fan blade 40 is operatively coupled to a suitable pitch-changing mechanism 44 by means of the fan blades 40, which is configured to collectively change the pitch of the fan blades 40, e.g., synchronously. Gas turbine engine 10 also includes a power gearbox 46, and the fan blades 40, disk 42, and pitch-changing mechanism 44 are rotatable together about a longitudinal centerline 12 via a LP shaft 36 across the power gearbox 46. The power gearbox 46 includes a plurality of gears for adjusting the rotational speed of the fan 38 relative to the LP shaft 36, allowing the fan 38 to rotate at a more efficient fan speed.

[0021] Still referencing Figure 1 In an exemplary embodiment, the disc 42 is covered by a rotatable front hub 48 (sometimes referred to as a "rotor") of the fan section 14. The front hub 48 is aerodynamically shaped to facilitate airflow through the plurality of fan blades 40. Furthermore, the exemplary fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 38 and / or turbine 16. It should be understood that, in the depicted embodiment, the nacelle 50 is supported relative to the turbine 16 by a plurality of circumferentially spaced outlet guide blades 52. Additionally, a downstream section 54 of the nacelle 50 extends over the outer portion of the turbine 16, thereby defining a bypass airflow passage 56 therebetween.

[0022] During operation of the gas turbine engine 10, a volume of air 58 enters the gas turbine engine 10 through the associated inlet 60 of the compartment 50 and the fan section 14. As this volume of air 58 flows over the fan blades 40, a first portion 62 of the air is directed or directed into the bypass airflow passage 56, and a second portion 64 of the air (as indicated by the arrow) is directed or directed into the working gas flow path 37, or more specifically, into the LP compressor 22. The ratio between the first portion 62 and the second portion 64 of the air is commonly referred to as the bypass ratio. The pressure of the second portion 64 of the air increases as it is directed through the HP compressor 24 and into the combustion section 26, where it mixes with fuel and burns to provide combustion gases 66.

[0023] Combustion gas 66 is directed through HP turbine 28, where a portion of its thermal and / or kinetic energy is extracted via a series of stages consisting of HP turbine stator blades 68 connected to housing 18 and HP turbine rotor blades 70 connected to HP shaft 34, thereby rotating HP shaft 34 and supporting the operation of HP compressor 24. Combustion gas 66 is then directed through LP turbine 30, where a second portion of its thermal and kinetic energy is extracted via a series of stages consisting of LP turbine stator blades 72 connected to housing 18 and LP turbine rotor blades 74 connected to LP shaft 36, thereby rotating LP shaft 36 and supporting the operation of LP compressor 22 and / or the rotation of fan 38.

[0024] Combustion gas 66 is then directed through turbine exhaust nozzle 32 of turbine 16 to provide propulsive thrust. Simultaneously, as a first portion of air 62 is directed through bypass airflow passage 56, the pressure of the first portion of air 62 increases significantly, and it is then discharged from fan exhaust nozzle 76 of gas turbine engine 10, also providing propulsive thrust. HP turbine 28, LP turbine 30, and turbine exhaust nozzle 32 at least partially define a hot gas path 78 for directing combustion gas 66 through turbine 16.

[0025] However, it should be understood that Figure 1 The exemplary gas turbine engine 10 depicted herein is merely an example, and in other exemplary embodiments, the gas turbine engine 10 may have any other suitable configuration. For example, although the depicted gas turbine engine 10 is configured as a ducted gas turbine engine (i.e., including the outer nacelle 50), in other embodiments, the gas turbine engine 10 may be a ductless gas turbine engine (such that the fan 38 is a ductless fan, and the outlet guide vane 52 cantilevered out from the housing 18).

[0026] Additionally or alternatively, although the depicted gas turbine engine 10 is configured as a geared gas turbine engine (i.e., including a power gearbox 46) and a variable-pitch gas turbine engine (i.e., including a fan 38 configured as a variable-pitch fan), in other embodiments, the gas turbine engine 10 may additionally or alternatively be configured as a direct-drive gas turbine engine (such that the LP shaft 36 rotates at the same speed as the fan 38), a fixed-pitch gas turbine engine (such that the fan 38 includes fan blades 40 that cannot rotate about the pitch axis P), or a combination of both. It should also be understood that, in other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may (if appropriate) be incorporated into, for example, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet gas turbine engine.

[0027] Now for reference Figure 2 A schematic cross-sectional view of a combustion section 26 according to an exemplary embodiment of the present disclosure is provided. The combustion section 26 may be incorporated in a manner similar to... Figure 1 In an engine constructed in the manner of an exemplary gas turbine engine 10.

[0028] Combustion section 26 includes a burner dome assembly 100. The burner dome assembly 100 includes an inner bushing 102 and an outer bushing 104. In this context, the "inner" bushing 102 is located inside the "outer" bushing 104 in the radial direction R. For the depicted embodiment, the inner bushing 102 and the outer bushing 104 are formed of a ceramic matrix composite (CMC) material as described above. In other forms, the inner bushing 102 and the outer bushing 104 may be formed of another material, such as a metal.

[0029] The burner dome assembly 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Although directions A, R, and C are generally defined relative to the inner liner 102, Figure 2 In an exemplary embodiment, directions A, R, and C are aligned with the axial direction A, radial direction R, and circumferential direction C of the gas turbine engine 10 described above.

[0030] The burner dome assembly 100 extends in the axial direction A between a front end 106 and a rear end 108. An inner bushing 102 and an outer bushing 104 define a combustion chamber 110 between the front end 106 and the rear end 108, in which a fuel-air mixture is burned.

[0031] The gas turbine engine 10 includes a cowling 112. The cowling 112 is connected to an outer bushing 104 and an inner bushing 102. Specifically, the cowling 112 is a structural member that connects CMC components (such as the inner bushing 102 and outer bushing 104) to other parts of the gas turbine engine 10. The cowling 112 helps guide the compressed air flow from the compressor section into the combustion chamber 110. The cowling 112 is formed of metal, such as steel, including high-strength steel alloys with melting points exceeding 1000°F. The cowling 112 is secured to the inner bushing 102 and outer bushing 104 using suitable fasteners 114 (such as bolts or pin joints). Figure 2 In the middle, the fairing 112 is fixed to the inner bushing 102 and the outer bushing 104 by bolts and nuts.

[0032] The burner dome assembly 100 includes a dome 116. The dome 116 forms the front wall of the combustion chamber 110. The dome 116 is configured to facilitate the flow of compressed air from the compressor section into the combustion chamber 110. The dome 116 is disposed on the inner bushing 102 and the outer bushing 104. Specifically, the dome 116 is pressurized and sealed to the inner bushing 102 and the outer bushing 104. That is, the air pressure in front of the dome 116 is greater than the air pressure inside the combustion chamber 110, and the pressure difference pushes the dome 116 against the inner bushing 102 and the outer bushing 104. The dome 116 is formed of CMC material.

[0033] Dome 116 defines fuel injector orifice 118, in Figure 2 The dome 116, shown in dashed lines, is used to receive fuel injectors. Compressed air from the compressor section of the gas turbine engine 10 flows into the combustion chamber 110, where it mixes with fuel from fuel injectors in fuel injector orifices and is ignited to produce combustion gases in the combustion chamber 110. The dome 116 may include a plurality of fuel injector orifices 118 to accommodate a plurality of fuel injectors (see, for example...). Figure 3-5 ).

[0034] The dome 116 includes a front portion 120, which includes an outer shoulder 121 defining a first annular surface 122. The first annular surface 122 is disposed on the front portion 120 of the dome 116, facing the fairing 112. The front portion 120 defines an outer diameter 124 and an inner diameter 126 of the front portion 120, and the first annular surface extends from the outer diameter 124 to the inner diameter 126. In this configuration, the outer diameter 124 of the front portion 120 is the overall outer diameter of the dome 116 because the outer shoulder 121 defines the outermost portion of the dome 116. The inner diameter 126 of the front portion 120 is the overall inner diameter of the dome 116 because the front portion 120 includes the innermost portion of the dome 116.

[0035] The first annular surface 122 is "flat," which in this context means a surface such that, when installed in the burner dome assembly 100, at least 90% of its total surface area has a height in the axial direction A that differs from a reference height datum defined by a specified dimension of the surface during manufacturing by within 0-5%. Specifically, the "flat" surface has almost no extension or curve between the outer diameter 124 and the inner diameter 126 of the dome 116. Specifically, the first annular surface 122 may have slight manufacturing tolerance deviations, such as a deviation of 0-5% from the reference flat datum, or localized thickening areas due to embossing, etc. Because the first annular surface 122 is flat, the temperature on the first annular surface 122 is substantially uniform, thereby reducing thermal variations and stress within the dome 116.

[0036] The first annular surface 122 of the dome 116 is disconnected from the cowling 112, i.e., the dome 116 is spaced apart from the cowling 112. In other words, the dome 116 and the cowling 112 do not contact or interact with each other. In this configuration, the amount of the combustor dome assembly 100 located inside the cowling 112 in the radial direction R is reduced, which addresses the space constraints and manufacturing challenges of the gas turbine engine 10. In particular, components with complex geometries are susceptible to low-cycle fatigue (LCF) stresses, such as thermal cycling stresses, while the flat shape of the dome 116 and its arrangement away from the cowling 112 reduce LCF stresses. Furthermore, when the first annular surface 122 is flat, the dome 116 cools faster and is easier to manufacture.

[0037] The dome 116 includes a rear portion 128, which includes an inner shoulder 129 defining a second annular surface 130. The second annular surface 130 is disposed on the rear portion 128 of the dome 116, facing the combustion chamber 110. The rear portion 128 includes an inner surface 132 that engages an inner bushing 102 and an outer surface 134 that engages an outer bushing 104. The second annular surface 130 extends from the inner surface 132 to the outer surface 134. The inner shoulder 129 defines a second outer diameter 136 and a second inner diameter 138, such that the second outer diameter 136 is smaller than the outer diameter 124, and the second inner diameter 138 is larger than the inner diameter 126. The second annular surface 130 extends from the second outer diameter 136 to the second inner diameter 138. That is, the second annular surface 130 is disposed between the outer diameter 124 and the inner diameter 126 of the dome 116, and therefore the second annular surface 130 is shorter than the first annular surface 122 in the radial direction R. The shorter second annular surface 130 allows the inner bushing 102 to engage the inner surface 132 of the rear portion 128, and the outer bushing 104 to engage the outer surface 134 of the rear portion 128.

[0038] As described above, the dome 116 is secured to the inner bushing 102 and the outer bushing 104 by a pressure seal. Specifically, the dimensions of the first annular surface 122 relative to the second annular surface 130 are configured such that a first air pressure acting on the first annular surface 122 is configured to be greater than a second air pressure acting on the second annular surface 130. The pressure seal secures the dome 116 without the need for additional fasteners or welds, reducing the manufacturing and construction time of the burner dome assembly 100.

[0039] The depicted exemplary burner dome assembly 100 includes an annular seal 140 located axially in the direction A behind the cowl 112. The annular seal 140, together with a pressure seal, additionally secures the dome 116 to the inner bushing 102 and the outer bushing 104. The annular seal 140 reduces or inhibits leakage of combustion gases through the cowl 112 to the dome 116 and into the combustion chamber 110. The annular seal 140 may be a suitable material, such as a resilient polymer or a resilient metal, that seals the interface between the dome 116 and the outer bushing 104 and resists the surrounding thermal environment. Alternatively, the burner dome assembly 100 may include different seals, such as rope seals or W-shaped seals, or may not include any additional seals at all.

[0040] refer to Figure 3 The image provides front and rear views of the burner dome assembly 100. Specifically, Figure 3 The view shows the inner bushing 102, the outer bushing 104, and the front portion 120 of the dome 116, including a first annular surface 122. As described above, the dome 116 includes a plurality of fuel injector holes 118 configured to receive fuel injectors. The fuel injector holes 118 are arranged circumferentially around the dome 116.

[0041] To reduce circumferential movement of the dome 116, the dome 116 includes a plurality of alignment slots 142, and the outer bushing 104 includes a plurality of alignment tabs 144 disposed in the plurality of alignment slots 142. The plurality of alignment slots 142 are arranged along the outer diameter 124 of the dome 116 and extend radially inward. The alignment tabs 144 extend radially inward into the alignment slots 142 to reduce circumferential movement of the dome 116. The alignment tabs 144 can be secured to the dome 116 by a suitable fastening method, such as brazing, bonding, mechanical fasteners, or a combination thereof. Alternatively, the alignment tabs 144 can be positioned within the alignment slots 142 without additional fastening.

[0042] It should be understood that the inner bushing 102 may include a plurality of alignment tabs 144, and a plurality of alignment slots 142 may be arranged along the inner diameter 126 of the dome 116. In this configuration, the plurality of alignment tabs 144 extend radially outward from the inner bushing 102 into the plurality of alignment slots 142. It should also be understood that the dome 116 may include a plurality of alignment tabs 144, which are received by a plurality of alignment slots 142 defined in the inner bushing 102 or the outer bushing 104.

[0043] Now for reference Figure 4 The image provides a front and rear view of the burner dome assembly 150 with another dome 152. Specifically, although... Figure 1-3 Dome 116 is a single, integral structure, but Figure 4 The dome 152 includes a plurality of circumferentially arranged segments 154. Each of the plurality of segments 154 includes a fuel injector orifice 118, and some of the plurality of segments 154 include alignment grooves 142 for receiving alignment tabs 144 of the outer bushing 104. The plurality of segments 154 are joined together in a suitable manner, such as by brazing, fastening, bonding, or combination thereof. By forming the dome 152 as a plurality of segments 154, the manufacture of each individual segment 154 may be faster than the manufacture of the entire dome 152 at once, thereby reducing the overall manufacturing time of the burner dome assembly 150.

[0044] Now for reference Figure 5 The image provides a front and rear view of a burner dome assembly 200 with another dome 202. The burner dome assembly 200 includes an outer bushing 204 and an inner bushing 206, with the dome 202 extending between the outer bushing 204 and the inner bushing 206. The outer bushing 204 defines a plurality of alignment slots 208, and the dome 202 includes a plurality of alignment tabs 210 disposed in the plurality of alignment slots 208. The alignment tabs 210 extend outwardly into the alignment slots 208, securing the dome 202 to the outer bushing 204. Although... Figure 5 Although not shown, it should be understood that the inner sleeve 206 may define the alignment groove 208, and in this configuration, the alignment tab 210 may extend into the inner sleeve 206.

[0045] Further aspects are provided by the following topics:

[0046] A burner dome assembly includes: an outer bushing; an inner bushing located inside the outer bushing; a dome disposed on the inner bushing and the outer bushing; and a fairing connected to the inner bushing and the outer bushing; wherein the dome is disconnected from the fairing and defines an annular surface facing the fairing, the annular surface extending from the outer diameter of the dome to the inner diameter of the dome.

[0047] The burner dome assembly according to any of the foregoing clauses further includes an annular seal that secures the dome to the inner bushing and the outer bushing.

[0048] The burner dome assembly according to any of the foregoing clauses, wherein the dome further defines a front portion and a rear portion, the front portion including the annular surface, and the rear portion including an inner surface engaging the inner bushing, an outer surface engaging the outer bushing, and a second annular surface extending from the outer surface to the inner surface.

[0049] According to any of the preceding clauses, the size of the first annular surface is set relative to the second annular surface such that a first air pressure acting on the first annular surface is configured to be greater than a second air pressure acting on the second annular surface.

[0050] According to any of the foregoing clauses, the burner dome assembly wherein the second annular surface defines a second outer diameter and a second inner diameter, wherein the second outer diameter is smaller than the outer diameter and the second inner diameter is larger than the inner diameter.

[0051] The burner dome assembly according to any of the foregoing clauses, wherein the dome defines an alignment groove, and at least one of the outer bushing or the inner bushing includes an alignment tab disposed in the alignment groove.

[0052] The burner dome assembly according to any of the foregoing clauses, wherein at least one of the outer bushing or the inner bushing defines an alignment groove, and the dome includes an alignment tab disposed in the alignment groove.

[0053] The burner dome assembly according to any of the foregoing clauses, wherein the dome is spaced apart from the cowling.

[0054] The burner dome assembly according to any of the foregoing clauses, wherein the dome is configured to be pressurized and sealed to the inner bushing and the outer bushing.

[0055] The burner dome assembly according to any of the foregoing clauses, wherein both the inner liner and the outer liner are formed of ceramic matrix composite (CMC) material.

[0056] The burner dome assembly according to any of the foregoing clauses, wherein the shroud is formed of metal.

[0057] The burner dome assembly according to any of the foregoing clauses, wherein the fairing is connected to at least one of the outer bushing or the inner bushing via a pin joint.

[0058] The burner dome assembly according to any of the foregoing clauses, wherein the dome is integral.

[0059] The burner dome assembly according to any of the foregoing clauses, wherein the dome comprises a plurality of circumferentially arranged segments.

[0060] A gas turbine engine includes: a turbine comprising a fan section, a compressor section, a combustion section, and a turbine section in a series flow sequence; the combustion section including a combustor dome assembly; the combustor dome assembly including: an outer bushing; an inner bushing located inside the outer bushing; a dome disposed on the inner bushing and the outer bushing; and a fairing connected to the inner bushing and the outer bushing; wherein the dome is disconnected from the fairing and defines an annular surface facing the fairing, the annular surface extending from the outer diameter of the dome to the inner diameter of the dome.

[0061] According to any of the foregoing clauses, in a gas turbine engine, the combustor assembly further includes an annular seal that secures the dome to the inner bushing and the outer bushing.

[0062] According to any of the preceding clauses, in a gas turbine engine, the dome further defines a front portion and a rear portion, the front portion including the annular surface, and the rear portion including an inner surface engaging the inner bushing, an outer surface engaging the outer bushing, and a second annular surface extending from the outer surface to the inner surface.

[0063] In any of the preceding clauses, the gas turbine engine wherein the dome defines an alignment groove, and at least one of the outer bushing or the inner bushing includes an alignment tab disposed in the alignment groove.

[0064] In any of the preceding clauses, a gas turbine engine is provided, wherein at least one of the outer bushing or the inner bushing defines an alignment groove, and the dome includes an alignment tab disposed in the alignment groove.

[0065] In any of the preceding clauses of the gas turbine engine, the dome is configured to be pressurized and sealed to the inner bushing and the outer bushing.

[0066] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially indistinguishable from the literal language of the claims.

Claims

1. A burner dome assembly, characterized in that, include: Outer bushing; Inner liner, the inner liner being located inside the outer liner; A dome, wherein the dome is disposed on the inner bushing and the outer bushing; as well as A fairing, the fairing being connected to the inner bushing and the outer bushing; The dome is disconnected from the fairing and defines an annular surface facing the fairing, the annular surface extending from the outer diameter of the dome to the inner diameter of the dome.

2. The burner dome assembly according to claim 1, characterized in that, It further includes a ring seal that secures the dome to the inner bushing and the outer bushing.

3. The burner dome assembly according to claim 1, characterized in that, in, The dome further defines a front portion and a rear portion, the front portion including the annular surface, and the rear portion including an inner surface engaging the inner bushing, an outer surface engaging the outer bushing, and a second annular surface extending from the outer surface to the inner surface.

4. The burner dome assembly according to claim 3, characterized in that, in, The size of the first annular surface is set relative to the second annular surface such that a first air pressure acting on the first annular surface is configured to be greater than a second air pressure acting on the second annular surface.

5. The burner dome assembly according to claim 3, characterized in that, in, The second annular surface defines a second outer diameter and a second inner diameter, wherein the second outer diameter is smaller than the outer diameter and the second inner diameter is larger than the inner diameter.

6. The burner dome assembly according to claim 1, characterized in that, in, The dome defines an alignment groove, and at least one of the outer bushing or the inner bushing includes an alignment tab disposed in the alignment groove.

7. The burner dome assembly according to claim 1, characterized in that, in, At least one of the outer bushing or the inner bushing defines an alignment groove, and the dome includes an alignment tab disposed in the alignment groove.

8. The burner dome assembly according to claim 1, characterized in that, in, The dome is spaced apart from the fairing.

9. The burner dome assembly according to claim 1, characterized in that, in, The dome is configured to be pressurized and sealed to the inner and outer bushings.

10. The burner dome assembly according to claim 1, characterized in that, in, Both the inner and outer bushings are made of ceramic matrix composite (CMC) material.

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