Gas turbine engine and fuel nozzle thereof

Abstract

A gas turbine engine includes a combustion section shielded by a housing having at least one through passage, the combustion section including: a domed wall and a liner, the domed wall and liner at least partially defining a combustion chamber; a fuel nozzle connected to the dome wall and having a nozzle tube; and a coupling which fixes the fuel nozzle to the housing and is at least partially disposed in the at least one through channel.

Description

Technical Field

[0001] The present subject matter generally relates to gas turbine engines having fuel nozzles. Background Art

[0002] The turbine engine is driven by a flow of combustion gases through the engine to rotate a plurality of turbine blades, which in turn rotate the compressor to provide compressed air to the combustor for combustion. The combustor may be disposed within the turbine engine and fluidly coupled to the turbine into which the combustion gases flow.

[0003] Historically, hydrocarbon fuels have been used in the combustors of turbine engines. Typically, air and fuel are supplied to a combustion chamber, the air is mixed with the fuel, and the fuel is then burned in the presence of air to produce hot gases. The hot gases are then supplied to a turbine where they are cooled and expanded to produce power. The byproducts of the combustion of the fuel typically include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively referred to as NO x ), carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and sulfur oxides (e.g., SO 2 and SO 3 ) other oxides.

[0004] To reduce environmentally harmful byproducts, other fuels, such as hydrogen, are being explored. Hydrogen or hydrogen mixed with another element has a higher flame temperature than traditional hydrocarbon fuels. That is, hydrogen or hydrogen mixed fuels generally have a wider flammable range and a faster burning speed than traditional hydrocarbon-based fuels. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] In the attached picture:

[0006] Figure 1 is a schematic cross-sectional view of a turbine engine having a compression section, a combustion section, and a turbine section according to various aspects described herein.

[0007] Figure 2 According to various aspects described herein, along line II-II Figure 1 Schematic diagram of the combustion section.

[0008] Figure 3 is a schematic diagram showing a portion of a fuel nozzle connected to a casing and a dome wall according to various aspects described herein.

[0009] Figure 4 yes Figure 3 Schematic cross-sectional view of a fuel nozzle.

[0010] Figure 5is a perspective view of a flange of a coupling of a fuel nozzle according to various aspects described herein.

[0011] Figure 6 and Figure 7 is a perspective view of a first axis of a coupling of a fuel nozzle according to various aspects described herein.

[0012] Figure 8 is a perspective view of a second axis of a coupling of a fuel nozzle according to various aspects described herein.

[0013] Fig. 9 is an enlarged cross-sectional view of a coupling of a fuel nozzle connected to a housing according to various aspects described herein.

[0014] Fig.10 is a schematic perspective view showing a portion of a fuel nozzle coupled to a housing and a dome wall according to various aspects described herein.

[0015] Fig.11 yes Fig.10 Schematic cross-sectional view of a fuel nozzle.

[0016] Fig.12 is a perspective view of a flange of a coupling of a fuel nozzle according to various aspects described herein.

[0017] Fig.13 is a perspective view of a second axis of a coupling of a fuel nozzle according to various aspects described herein.

[0018] Fig.14 is a perspective view of a third axis of a coupling of a fuel nozzle according to various aspects described herein.

[0019] Fig.15 is an enlarged cross-sectional view of a coupling of a fuel nozzle connected to a housing according to various aspects described herein.

[0020] Fig.16 is a flow chart illustrating a method of assembling a fuel nozzle assembly in a gas turbine engine according to various aspects described herein. DETAILED DESCRIPTION

[0021] The disclosed aspects described herein relate to combustors. For illustrative purposes, the present disclosure will be described with respect to a turbine engine. However, it will be understood that the disclosed aspects described herein are not limited thereto, and the combustors described herein may be implemented in engines including, but not limited to, turbojets, turboprops, turboshafts, and turbofans. The disclosed aspects discussed herein may have general applicability in non-aircraft engines having combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0022] As used herein, the word "exemplary" means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Furthermore, unless expressly stated otherwise, all embodiments described herein are to be considered exemplary.

[0023] As used herein, the terms “first,” “second,” and “third” 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 "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, front refers to a position closer to the engine inlet, while rear refers to a position closer to the engine exhaust.

[0025] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the direction of fluid flow. The terms "forward" or "front" mean in front of something, and "rearward" or "rear" mean behind something. For example, when used in relation to fluid flow, forward / front may mean upstream, and rearward / rear may mean downstream.

[0026] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that a fluid is able to establish a connection between designated areas.

[0027] Additionally, as used herein, the terms "radial" or "radially" refer to directions away from a common center. For example, in the overall context of a turbine engine, radial refers to directions along a ray extending between a central longitudinal axis of the engine and an outer periphery of the engine. In the context of a coupling of a fuel nozzle, radial may refer to directions along a ray extending between a centerline of the coupling or its axis and an outer periphery of the coupling.

[0028] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to help the reader understand the present disclosure and do not create limitations, particularly limitations on the position, orientation, or use of the disclosed aspects described herein. Connection references (e.g., attachment, coupling, connection, and engagement) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connection reference does not necessarily mean that two elements are directly connected and fixed relative to each other. The exemplary drawings are for illustration purposes only, and the dimensions, positions, orders, and relative sizes reflected in the attached drawings may vary.

[0029] Unless the context clearly dictates otherwise, the singular forms "a," "an," and "the" include plural references. Also, as used herein, the term "set" or "a group of" elements may include any number of elements, including only one.

[0030] The use of "and" and "or" should be interpreted broadly. For example, but not limited to, the use of "and" does not necessarily require all elements or features listed, and the use of "or" is inclusive unless such a construction is illogical.

[0031] Approximate language as used in the entire specification and claims herein is applied to modify any quantitative representation that can allow variation without causing its related basic function to change. Therefore, the value modified by one or more terms such as "approximately", "approximately", "substantially" and "substantially" is not limited to the specified precise value. In at least some cases, the approximate language may correspond to the accuracy of the instrument used to measure the value, or the accuracy of the method or machine used to construct or manufacture components and systems. In at least some cases, the approximate language may correspond to the accuracy of the instrument used to measure the value, or the accuracy of the method or machine used to construct or manufacture components and systems. For example, approximate language may refer to 1%, 2%, 4%, 5%, 10%, 15% or 20% of the end point of the range of a single value, a range of values ​​and a limited range of values. Here and throughout the specification and claims, range restrictions are combined and interchanged, and such ranges are identified and include all sub-ranges contained therein, unless otherwise indicated by context or language. For example, all ranges disclosed herein include endpoints, and the endpoints can be combined independently of each other.

[0032] As used herein, "close" is not limiting, but rather a descriptor used to locate parts described herein. In addition, the term "close" refers to being closer or closer to the referenced part than to the following part. For example, a first hole is close to a wall, and the first hole is upstream of a second hole, meaning that the first hole is closer to the wall than the first hole is to the second hole.

[0033] Figure 1 is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 may be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotationally couples the compressor section 12 and the turbine section 16 so that rotation of one affects rotation of the other, and defines an axis of rotation 20 of the turbine engine 10.

[0034] The compressor section 12 may include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 that are serially fluidly coupled to each other. The turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are serially fluidly coupled to each other. The drive shaft 18 may operably couple the LP compressor 22, the HP compressor 24, the HP turbine 26, and the LP turbine 28 together. Alternatively, the drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft may couple the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft, such that the rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft, such that the rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0035] The compressor section 12 may include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced fixed vanes. The compressor blades for one stage of the compressor section 12 may be mounted to a disk that is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the compressor section 12 may be mounted to a casing that may extend circumferentially around and shield one or more sections of the turbine engine 10. It should be understood that the representation of the compressor section 12 is merely schematic and there may be any number of blades, vanes, and stages. It is further contemplated that there may be any number of other components within the compressor section 12.

[0036] Similar to the compressor section 12, the turbine section 16 may include a plurality of axially spaced stages, with each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The turbine blades for one stage of the turbine section 16 may be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the turbine section 16 may be mounted to the housing in a circumferential manner. It is noted that there may be any number of blades, vanes, and turbine stages, as the illustrated turbine section 16 is merely a schematic representation. It is further contemplated that there may be any number of other components within the turbine section 16.

[0037] The combustion section 14 may be disposed in series between the compressor section 12 and the turbine section 16. The combustion section 14 may be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 may be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and fluidly coupled to the HP turbine 26 at a downstream end of the combustion section 14.

[0038] During operation of the turbine engine 10, ambient or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where the air is compressed, defining pressurized air. The pressurized air may then flow into the combustion section 14, where it is mixed with fuel and ignited, thereby generating combustion gases. The HP turbine 26 extracts some work from these combustion gases, which drives the HP compressor 24. The combustion gases are exhausted into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gases are ultimately exhausted from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and the combustion gases may together define a working airflow through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0039] Figure 2 Depicts the Figure 1 FIG. 1 is a cross-sectional view of the combustion section 14 of line II-II of FIG. The combustion section 14 may include a combustor 30 having an annular arrangement of combustor cups 31 disposed about the centerline or axis of rotation 20 of the turbine engine 10. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a can shape, a can annular, or an annular arrangement. In a non-limiting example, the combustor 30 may have a combined arrangement positioned with a shroud or casing 29 of the engine 10. The shroud or casing 29 may shield or cover at least a portion of the combustion section 14.

[0040] The combustor 30 may be at least partially defined by a combustor liner 40. In some examples, the combustor liner 40 may include an outer liner 41 and an inner liner 42 that are concentric with each other and arranged in an annular manner around the engine centerline or rotation axis 20. In some examples, the combustor liner 40 may have an annular structure around the combustor 30. In some examples, the combustor liner 40 may include multiple segments or portions that together form the combustor liner 40. In some examples, the combustor liner 40 may have an annular structure around the combustor 30. In some examples, the combustor liner 40 may include multiple segments or portions that together form the combustor liner 40. In some examples, the combustor liner 40 may include an outer liner 41 that is radially spaced apart from the inner liner 42. In some examples, the combustor liner 40 may include a single liner.

[0041] The dome assembly 44, together with the combustor liner 40, may at least partially define a combustion chamber 50 annularly arranged about the rotation axis 20. For example, the dome wall 46 of the dome assembly 44 may be substantially perpendicular to the rotation axis 20 and may cooperate with the outer liner 41, the inner liner 42, or both to at least partially define the combustion chamber 50. The compressed air passage 32 may be at least partially defined by the combustor liner 40 and the casing 29.

[0042] The combustor 30 may include or be connected to a fuel supply 34 (e.g., an external fuel manifold). The fuel supply 34 may be connected to an outer surface 62 of the housing 29, which may be a surface opposite the inner surface 60. The fuel nozzle 38 fluidly couples the fuel supply 34 to the combustor cup 31 and the combustion chamber 50. The fuel F may include any suitable fuel, including a hydrocarbon fuel or a hydrogen fuel in a non-limiting example. For example, the fuel nozzle 38 may be a hydrogen fuel nozzle, and the fuel nozzle assembly 48 may be a hydrogen fuel nozzle assembly. The combustor cup 31 may be individually connected to the dome wall 46. For example, but not limited to, the combustor cup 31 may be connected to the dome wall 46 in a circumferentially spaced configuration. The combustor cup 31 may be disposed at a radial distance from the axis of rotation 20 that is greater than the radial distance of the inner liner 42 and less than the radial distance of the outer liner 41.

[0043] Figure 3 Depicted Figure 1 8. The combustion section 14 of the combustion chamber 50 includes a portion of the combustion section 14, including a fuel nozzle 38 fixed to the combustion chamber 50 via a coupling 80. The fuel nozzle 38 may include a nozzle tube 70. The nozzle tube 70 may be fluidly coupled to the fuel supply 34. The nozzle tube 70 may provide the fuel F received by the fuel nozzle 38 (e.g., from the fuel supply 34) to the combustion chamber 50. The nozzle tube 70 may include a nozzle tip 72 disposed at its distal end. The nozzle tip 72 may include one or more openings that allow the fuel F to leave the fuel nozzle 38 and enter the combustion chamber 50. The fuel nozzle assembly 48 may include the fuel nozzle 38 and a coupling 80.

[0044] In exemplary aspects, the fuel nozzle 38 may include or be fluidly coupled to a swirler 74. The swirler 74 may be disposed at or around the dome wall 46, and in some cases, may extend into or through the dome wall 46. The swirler 74 may swirl incoming air (such as compressed air from the compressor section 12) near the fuel F exiting the nozzle tip 72, which may promote a uniform mixture of air and fuel entering the combustor 30. In some configurations, the swirler 74 may be fixed (e.g., rigidly, permanently) to the dome wall 46. For example, the swirler 74 may be rigidly fixed to the dome wall 46 via welding, brazing, fasteners, or a combination thereof.

[0045] In some examples, the swirler 74 may be connected to the nozzle tube 70 and the nozzle tip 72 and at least partially surround the nozzle tube 70 and the nozzle tip 72. For example, the nozzle tip 72 may extend into and through the swirler 74. According to some configurations, the nozzle tube 70 may be rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the swirler 74 so that the fuel nozzle 38 is rigidly fixed to the swirler 72, the dome wall 46, or both. The swirler 74 may be rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the dome wall 46, which may provide a configuration in which the nozzle tip 72 and the swirler 74 are fixed to the dome wall 46 in a concentric arrangement, which may provide a consistent flame distribution in the combustion chamber 50. In other designs, the nozzle may move at least to some extent relative to the dome wall through a floating connection between the nozzle and the dome wall, which may provide an inconsistent flame distribution.

[0046] Some fuels, such as hydrogen, are particularly sensitive to interaction with the oxidant, so misalignment between two or more of the nozzle tip 72, the swirler 74, or the dome wall 46 may have a significant and undesirable effect on the flame distribution. Fixing the nozzle tip 72, the swirler 74, and the dome wall 46 in proper alignment relative to one another (e.g., with the nozzle tip 72 and the swirler 74 in a concentric configuration) can limit or eliminate such undesirable effects on the flame distribution.

[0047] The fuel nozzle 38 can provide fuel F to the combustor cup 31 via a single hole 76 (e.g., a through passage) in the housing 29. Other designs include holes for fluid flow and multiple additional fastener holes for each nozzle. According to some aspects of the present disclosure, the number of holes 76 in the housing 29 is reduced compared to such other designs. Some other designs may also include oversized housing holes to allow the nozzles to be removed from the housing. According to the present design, the housing 29 may not include any such oversized housing holes. For example, the housing hole 76 may be just large enough to insert and rotate the second shaft 86, and may not be large enough to allow the entire fuel nozzle 38 to pass through (e.g., the flange 82 may not pass through the housing hole 76).

[0048] According to aspects of the present disclosure, the proximal end of nozzle tube 70 may be connected to coupling 80 , which may be connected to housing 29 , fuel supply 34 , or both. Nozzle tip 72 may be connected at or about the distal end of nozzle tube 70 .

[0049] In some examples, dome wall 46 may be substantially annular and substantially perpendicular to at least some portions of housing 29, although dome wall 46 may include other configurations as well. Nozzle tube 70 may include a generally L-shaped configuration. For example, a first section of nozzle tube 70 may extend generally radially inward from housing 29 and fuel supply 34, and a second section of nozzle tube 70 may extend generally axially from the first section toward dome wall 46. The first section may be substantially perpendicular to nozzle tip 72.

[0050] According to aspects of the present disclosure, the dome assembly 44 may include an extension 64 . The extension 64 may extend generally axially forward from the dome wall 46 and taper radially inward and may at least partially cover and surround the fuel nozzles 38 and the swirler 74 .

[0051] Figure 4A cross section of a fuel nozzle 38 connected to a housing 29 via a coupling 80 is depicted. According to some aspects, the coupling 80 may include a flange 82, a first shaft 84, a second shaft 86, and a nut 88. The flange 82 may be connected (e.g., rigidly fixed) to the proximal end of the nozzle tube 70. In the assembled configuration, the flange 82 may be adjacent to or in contact with the inner surface 60 of the housing 29. The first shaft 84 may engage with the flange 82 and extend beyond the outer surface 62 of the housing 29 through the housing hole 76, and fluidly couple the fuel nozzle 38, the coupling 80, or both to the fuel supply 34. The second shaft 86 may be disposed at least partially around the first shaft 84, extend through the housing hole 76, engage the flange 82, or a combination thereof. The nozzle tube 70 may be disposed at a first side 92 (e.g., inside) of the flange 82, and the nut 88 may be disposed at a second side 94 (e.g., outside) of the flange 82 opposite to the first side 92. The nut 88 can engage the second shaft 86 and contact the outer surface 62 of the housing 29 to apply a clamping force to the housing 29 between the nut 88 and the flange 82 to secure the nozzle 38 to the housing 29. For example, the nut 88 can be disposed opposite the flange 82 with a portion of the housing 29 therebetween.

[0052] According to some aspects, the first shaft 84 includes a first fluid passage 100, the flange 82 includes a second fluid passage 102, and the nozzle tube 70 includes a third fluid passage 104. In an assembled configuration, the first fluid passage 100 can be fluidly coupled to the fuel supply 34 and to the second fluid passage 102. The second fluid passage 102 can be fluidly coupled to the third fluid passage 104 to provide fluid communication from the fuel supply 34 to the combustion chamber 50.

[0053] Figure 5 An example of a flange 82 is depicted. The flange 82 may include an inner portion 110 and an outer portion 112, the outer portion 112 may be spaced apart (e.g., radially) from the inner portion 110 by a channel 114. The flange 82 may be cylindrical, and the channel 114 may be annular. The channel 114 may include at least one threaded surface 116. The inner portion 110 may include an axial surface 120, which may face away from the nozzle tube 70 ( Figure 4 ), toward the housing 29 ( Figure 4 ), or both. The axial surface 120 may include one or more axially extending formations 122, such as one or more voids, one or more protrusions (e.g., teeth), or a combination thereof. The one or more formations 122 may be configured to engage a corresponding formation 124 of a first axial surface 126 of the first shaft 84 (see, e.g., Figure 4 For example, the formation 124 of the first shaft 84 may include complementary voids, protrusions (eg, teeth), or both, such that when the axial surface 120 of the flange 82 is aligned with the first shaft 84 ( Figure 4 ) of the first axial surface 126 ( Figure 4 ) are engaged, the formation 122 engages with the formation 124 and limits or prevents relative rotation between the flange 82 and the first shaft 84.

[0054] According to some aspects, the flange 82 may include a first sealing recess 140, a second sealing recess 142, or both. The inner portion 110 may include the first sealing recess 140. A first seal 144 may be at least partially disposed in the first sealing recess 140 to provide a fluid seal ( Figure 4 The second seal 146 may be at least partially disposed in the second seal recess 142 to provide a fluid seal between the flange 82 and the inner surface 60 of the housing 29 ( Figure 4 The diameter of the first seal 144 may be smaller than the diameter of the housing bore 76, and the diameter of the second seal 146 may be larger than the diameter of the housing bore 76 (see, e.g., Figure 4 For example, the second seal 146 can be configured to restrict the space within the housing 29 (such as the space 202 ( Figure 4 )) flows through the housing hole 76 to the space 200 (outside the housing 29) Figure 4 ). In some configurations, the second seal 146 can include a C-shaped seal. In some configurations, the second seal 146 can include a metallic seal, a non-metallic seal, or a combination of both.

[0055] Figure 6 and Figure 7 An example of a first shaft 84 is depicted. A first axial end 150 of the first shaft 84 may include a first axial surface 126, which may include a formation 124. The first axial end 150 may include one or more leakage channels 154 formed in a second axial surface 156 of the first shaft 84 facing away from the flange 82. The one or more leakage channels 154 may at least partially form a leakage path LP (see, e.g., Fig. 9 ), for flowing out of the first fluid channel 100 or the second fluid channel 102 ( Figure 5 ) and passes through flange 82( Figure 5 ) of the axial surface 120 ( Figure 5 ) and the first axial surface 126 of the first shaft 84 between the first seal 144 ( Figure 5) fluid. The second axial end 152 of the first shaft 84 may include one or more flat portions 158, such as for applying torque to the first shaft 84 or resisting the application of torque to the first shaft 84. The first axial end 150 may include a radial extension 160 having a diameter greater than other portions of the first axial end 150, the second axial end 152, or both. The radial extension 160 may define a second axial surface 156 and may provide a stepped configuration for the outer radial surface of the first shaft 84.

[0056] Figure 8 An example of a second shaft 86 is depicted. The second shaft 86 may include a threaded surface 170, which may be disposed at an outer radial surface of the second shaft 86. The threaded surface 170 may engage with the flange 82 ( Figure 5 ) of the thread surface 116( Figure 5 ) engagement. For example, when the threaded surface 170 of the second shaft 86 engages with the flange 82 ( Figure 5 ) when the threaded surface 116 of the second shaft 86 is engaged, the first axial end 172 of the second shaft 86 can be at least partially inserted into the groove 114 ( Figure 5 ). The second axial end 174 of the second shaft 86 may include one or more flat portions 176, such as for applying torque to the second shaft 86 or resisting the application of torque to the second shaft 86. The second shaft 86 may include an inner axial surface 180, and the inner axial surface 180 may include one or more leakage channels 182. The inner axial surface 180 may face the flange 82. The one or more leakage channels 182 may at least partially form a leakage path LP (see, e.g. Fig. 9 ), for flowing out of the first fluid channel 100 ( Figure 4 ) or the second fluid channel 102 ( Figure 4 ) and passes through the axial surface 120 of the flange 82 ( Figure 5 ) and the first shaft 84 ( Figure 6 ) of the first axial surface 126 ( Figure 6 ) between the first seal 144 ( Figure 5 In some configurations, the leakage channel 182 of the second shaft 86 may be connected to the first shaft 84 ( Figure 6 ) leakage channel 154 ( Figure 6 ) In other configurations, leakage channel 182 may cooperate with leakage channel 154 ( Figure 6 ) separately and in addition to or in place of the leakage channel 154. In the assembled configuration, the inner axial surface 180 of the second shaft 86 can be aligned with the second axial surface 156 ( Figure 7) adjacent, in contact, or both. The first axial end 172 of the second shaft 86 may include a larger inner diameter than the second axial end 174, which may provide a stepped configuration for the inner surface 210 (e.g., inner radial surface) of the second shaft 86, which may correspond to the first shaft 84 ( Figure 6 The inner axial surface 180 may extend radially between a larger inner diameter of the first axial end 172 and a smaller inner diameter of the second axial end 174 .

[0057] Fig. 9 An example of the coupling 80 is depicted in an assembled configuration with the housing 29. Assembling the fuel nozzle 38 and the coupling 80 with the housing 29 may include moving the flange 82 into proximity with the housing bore 76, which may include positioning the flange 82 adjacent to or in contact with the inner surface 60 of the housing 29. Additionally or alternatively, moving the flange 82 into proximity with the housing bore 76 may include moving the second seal 146 adjacent to or in contact with the inner surface 60. In some configurations, the flange 82 may be held adjacent to or in contact with the inner surface 60 via the connection of the nozzle tube 70 to the dome wall 46 (see, e.g., Figure 3 and Figure 4 For example, the nozzle tube 70 may be (eg, rigidly) secured to the dome wall 46 prior to completing assembly of the coupling 80 with the housing 29. Figure 4 ).

[0058] According to some aspects, the first shaft 84 can be connected to the flange 82, which can include at least partially inserting the first shaft 84 into the housing bore 76, engaging one or more formations 122 of the flange 82 with one or more formations 124 of the first shaft 84, positioning the first axial surface 126 of the first shaft 84 in contact with the axial surface 120 of the flange 82, aligning the first fluid passage 100 with the second fluid passage 102, positioning the first axial surface 126 in contact with the first seal 144, or a combination thereof.

[0059] In some examples, after the first shaft 84 is connected to the flange 82, the second shaft 86 can be connected to the flange 82. Connecting the second shaft 86 to the flange 82 can include engaging the threaded surface 170 of the second shaft 86 with the threaded surface 116 of the flange 82, which can include at least partially inserting the first axial end 172 of the second shaft 86 into the channel 114 of the flange 82 (e.g., screwing the second shaft 86 into the flange 82). Additionally or alternatively, connecting the second shaft 86 to the flange 82 can clamp at least a portion of the first shaft 84 between the axial surface 120 of the flange 82 and the inner axial surface 180 of the second shaft 86. Clamping the first shaft 84 between the flange 82 and the second shaft 86 can compress or deform the first seal 144 at least to some extent to provide a fluid seal between the flange 82 and the first shaft 84. According to some configurations, the first shaft 84 can be held in place, such as by applying a force or torque to the flat portion 158, while the second shaft 86 is connected to the flange 82, which can also hold the flange 82 in place, such as by engagement between the formations 122, 124. For example, holding the first shaft 84 in place can prevent rotational forces applied to the second shaft 86 (e.g., via the flat portion 176) from being transmitted to the flange 82 or the nozzle tube 70, thereby preventing the nozzle tube 70, the dome wall 46 ( Figure 4 ) or damage or misalignment of both. Due to the position of the flange 82 in the housing 29 (e.g., insufficient tool space, inaccessibility, etc.), directly retaining the flange 82 may not be feasible.

[0060] According to some examples, after the second shaft 86 is connected to the flange 82, the nut 88 can be connected to the second shaft 86. Connecting the nut 88 to the second shaft 86 can include engaging the threaded inner surface 190 of the nut 88 with the threaded surface 170 of the second shaft 86 (e.g., the nut 88 can be screwed onto the second shaft 86). For example, in some cases, the flange 82 and the nut 88 can engage the same threaded surface 170 of the second shaft 86. The nut 88 can be screwed onto the second shaft 86 until the nut 88 contacts the outer surface 62 of the housing 29, reaches a threshold torque, or both. The torque can be applied via one or more flat portions 192 of the nut 88. Connecting the nut 88 to the second shaft 86 can include compressing or deforming the second seal 146 at least to some extent so as to provide a fluid seal between the flange 82 and the inner surface 60 of the housing 29. Additionally or alternatively, connecting the nut 88 to the second shaft 86 can clamp a portion of the housing 29 between the flange 82 and the nut 88, which can rigidly fix the nozzle 38 to the housing 29. When the nut 88 is connected to the second shaft 86, one or both of the first shaft 84 or the second shaft 86 can be held in place, such as by applying a force or torque to the flat portions 158, 176, so as to prevent the rotational force applied to the nut 88 from being transferred to the flange 82 or the nozzle tube 70, which can help prevent the nozzle tube 70, the dome wall 46 ( Figure 4 ) or both. The connection of the nut 88 to the second shaft 86 can complete the connection of the coupling 80 (and the fuel nozzle assembly 48) to the housing 29.

[0061] According to some aspects, the assembled coupling 80 can provide a leakage path LP. The leakage path LP can provide fluid communication from the interior of the coupling 80 to the space 200 outside the housing 29. For example, if a leak occurs in the coupling 80, it may be desirable to provide the leakage fluid to the space 200 outside the housing 29 rather than to the space 202 inside the housing 29. The outer surface 62 of the housing 29 can at least partially define the space 200. The inner surface 60 of the housing 29 can at least partially define the space 202. In some cases, leakage may occur between the flange 82 and the first shaft 84. Such leakage may include a portion of the fluid (e.g., fuel) that flows through the first fluid passage 100, flows radially outward between the axial surfaces 120, 126, and passes through the first seal 144, rather than flowing into the second fluid passage 102. The leakage fluid can then reach the inner surface 210 of the second shaft 86. The one or more leakage channels 154 of the first shaft 84 , the one or more leakage channels 182 of the second shaft 86 , or a combination thereof may reduce resistance to fluid flow between the first shaft 84 and the second shaft 86 to facilitate leakage fluid flow to the space 200 outside the housing 29 .

[0062] According to some examples, the first shaft 84 and the second shaft 86 may be arranged such that a radial gap 212 is arranged between an outer surface 214 (e.g., an outer radial surface) of the first shaft 84 and an inner surface 210 of the second shaft 86. The leakage fluid may flow into the radial gap 212 through one or more leakage channels 154, 182, and then flow into the space 200. For example, the leakage path LP may include a space between the axial surfaces 120, 126, a space between the outer surface 214 of the first shaft 84 and the inner surface 210 of the second shaft 86 at the first axial end 150, 172, a space between the second axial surface 156 of the first shaft 84 and the inner axial surface 180 of the second shaft 86, one or more leakage channels 154 of the first shaft 84, one or more leakage channels 182 of the second shaft 86, the radial gap 212, or a combination thereof. The resistance to fluid flow of the leakage path LP can be lower than the resistance to fluid flow between the threaded surface 116 of the flange 82 and the threaded surface 170 of the second shaft 86, so most or all of the leakage fluid can flow through the leakage path LP to the space 200 outside the housing 29 instead of flowing to the space 202 inside the housing. Although the leakage channels 154, 182 are shown in the axial surfaces of the shafts 84, 86, the radial surfaces 214, 210 of the shafts 84, 86 may additionally or alternatively include the leakage channels 154, 182.

[0063] According to some examples, the first shaft 84 and the second shaft 86 can be cylindrical, hollow, arranged in a concentric configuration, or a combination thereof. In some examples of the assembled nozzle 38, portions of the first shaft 84, the second shaft 86, and the nut 88 can overlap in a radial direction (e.g., relative to the centerline 80a of the coupling 80). Additionally or alternatively, in some examples of the assembled nozzle 38, portions of the first shaft 84, the second shaft 86, and the housing 29 can overlap in a radial direction. Additionally or alternatively, in some examples of the assembled nozzle 38, portions of the flange 82, the first seal 144, the second shaft 86, and the second seal 146 can overlap in a radial direction. In some configurations, the diameter of the housing bore 76 can be greater than the outer diameter of the second shaft 86, so that the second shaft 86 does not contact the housing 29 in the assembled configuration, so that the second shaft 86 can rotate in the housing bore 76 (e.g., when connected to the flange 82) without contacting the housing 29, or both.

[0064] In some examples, the nozzle tube 70 may be secured (e.g., brazed, welded, etc.) to the flange 82 prior to connecting the nozzle tube 70 to the dome wall 46, prior to connecting the first shaft 84 to the flange 82, or prior to both. Additionally or alternatively, the nozzle tube 70 may be secured (e.g., rigidly) to the dome wall 46 prior to connecting the first shaft 84 to the flange 82. In some cases, the flange 82 may not extend into the housing bore 76 to facilitate connection of the nozzle tube 70 to the dome wall 46, which may be substantially perpendicular to the centerline 80a of the coupling 80.

[0065] Fig.10 A fuel nozzle assembly 1048 is depicted that includes a fuel nozzle 1038 and a coupling 1080 connected to the combustion chamber 50. The fuel nozzle 1038 may include similar aspects as the fuel nozzle 38; therefore, like parts will be described with like numerals further increased by 1000, it being understood that the description of like parts of the fuel nozzle 38 may apply to the fuel nozzle 1038 unless otherwise stated.

[0066] The fuel nozzle 1038 may include a nozzle tube 1070. The nozzle tube 1070 may be fluidly coupled to the fuel supply 34. The nozzle tube 1070 may provide the fuel F received by the fuel nozzle 1038 (e.g., from the fuel supply 34) to the combustion chamber 50. The nozzle tube 1070 may include a nozzle tip 1072 disposed at its distal end. The nozzle tip 1072 may include one or more openings that allow the fuel F to exit the fuel nozzle 1038 and enter the combustion chamber 50. The fuel nozzle 1038 may include or be connected to a swirler 1074, which may be connected (e.g., rigidly fixed) to the dome wall 46.

[0067] According to aspects of the present disclosure, the proximal end of nozzle tube 1070 may be connected to coupling 1080, which may be connected to housing 29, fuel supply 34, or both.

[0068] Fig.11A cross section of a fuel nozzle 1038 connected to a housing 29 via a coupling 1080 is depicted. According to some aspects, the coupling 1080 may include a flange 1082, a first shaft 1084, a second shaft 1086, a nut 1088, and a third shaft 1090. The flange 1082 may be connected (e.g., rigidly fixed) to the proximal end of the nozzle tube 1070. In an assembled configuration, the flange 1082 may be adjacent to or in contact with the inner surface 60 of the housing 29. The first shaft 1084 may engage with the flange 1082, and in some configurations, may include one or more portions (e.g., formation 1122) extending beyond the outer surface 62 of the housing 29 through the housing hole 76. The second shaft 1086 may be disposed at least partially around the flange 1082, the first shaft 1084, or both, extend through the housing hole 76, engage the flange 1082, or a combination thereof. The third shaft 1090 may be disposed at least partially around the flange 1082, the first shaft 1084, the second shaft 1086, or a combination thereof. The third shaft 1090 may extend through the housing bore 76, engage the flange 1082, or a combination thereof. The nozzle tube 1070 may be disposed at a first side 1092 (e.g., an inner side) of the flange 1082, and the nut 1088 may be disposed at a second side 1094 (e.g., an outer side) of the flange 1082 opposite the first side 1092. The nut 1088 may engage the third shaft 1090 and contact the outer surface 62 of the housing 29 to apply a clamping force to the housing 29 between the nut 1088 and the flange 1082, thereby securing the fuel nozzle 1038 to the housing 29 (e.g., rigidly). For example, the nut 1088 may be disposed opposite the flange 1082, with a portion of the housing 29 located therebetween.

[0069] According to some aspects, first shaft 1084 includes first fluid passage 1100, flange 1082 includes second fluid passage 1102, and nozzle tube 1070 includes third fluid passage 1104. In an assembled configuration, first fluid passage 1100 may be fluidly coupled to fuel supply 34 and to second fluid passage 1102. Second fluid passage 1102 may be fluidly coupled to third fluid passage 1104 to provide fluid communication from fuel supply 34 to combustion chamber 50.

[0070] According to some aspects, the first shaft 1084 can be constructed in the same or similar manner as the first shaft 84 (see, e.g., Figure 6 and Figure 7). For example, the first shaft 1084 can include: a first axial end 1150 including a first axial surface 1124 having a formation 1124; a second axial surface 1156; one or more leakage channels 1154 formed in the second axial surface 1156; and a second axial end 1152 including one or more flat portions 1158. The first axial end 1150 can include a radial extension 1160 having a larger diameter than other portions of the first axial end 1150, the second axial end 1152, or both. The radial extension 1160 can define the second axial surface 1156 and can provide a stepped configuration for the outer radial surface of the first shaft 1084.

[0071] Fig.12 An example of flange 1082 is depicted. Flange 1082 may include flange 82 ( Figure 5 ) and may additionally include a second threaded surface 1118. For example, flange 1082 may include an inner portion 1110, an outer portion 1112, a channel 1114, a first threaded surface 1116 disposed in channel 1114, and a flange 1082 that may face away from nozzle tube 1070 ( Fig.11 ), one or more axially extending formations 1122, a first sealing recess 1140, a second sealing recess 1142, a first seal 1144 that can be at least partially disposed in the first sealing recess 1140, a second seal 1146 that can be at least partially disposed in the second sealing recess 1142, or a combination thereof. The second threaded surface 1118 can face radially outwardly toward the first threaded surface 1116. For example, the threaded surfaces 1116, 1118 can be disposed at opposite radial sides of the channel 1114.

[0072] Fig.13 An example of a second shaft 1086 is depicted. The second shaft 1086 may include a threaded surface 1170, which may be disposed at an inner radial surface of the second shaft 1086. The threaded surface 1170 may engage the first threaded surface 1116 of the flange 1082 (see, e.g., Fig.15). The first axial end 1172 of the second shaft 1086 can be at least partially inserted into the channel 1114, such as when the threaded surface 1170 of the second shaft 1086 engages the first threaded surface 1116 of the flange 1082. The second axial end 1174 of the second shaft 1086 can include one or more flat portions 1176, such as for applying torque to the second shaft 1086 or resisting the application of torque to the second shaft 1086. The second shaft 1086 can include an inner axial surface 1180, and the inner axial surface 1180 can include one or more leakage channels 1182. The inner axial surface 1180 can face the flange 1082. The one or more leakage channels 1182 can at least partially form a leakage path LP for the fluid that flows out of the first fluid channel 1100 ( Fig.11 ) or the second fluid channel 1102 ( Fig.11 ) and on flange 1082( Fig.12 ) of the axial surface 1120 ( Fig.12 ) and the first axial surface 1126 ( Fig.12 ) through the first seal 1144 ( Fig.12 )(See e.g. Fig.15 In some configurations, the leakage channel 1182 of the second shaft 1086 may be coupled to the leakage channel 1154 of the first shaft 1084 ( Fig.11 ) In other configurations, leakage channel 1182 may cooperate with leakage channel 1154 ( Fig.11 ) separately and in addition to or in place of leakage channel 1154. In the assembled configuration ( Fig.11 ), the inner axial surface 1180 of the second shaft 1086 can be adjacent to, in contact with, or both of the second axial surface 1156 of the first shaft 1084. The first axial end 1172 of the second shaft 1086 can include a larger inner diameter than the second axial end 1174, which can provide a stepped configuration for the inner surface 1210 of the second shaft 1086, which can correspond to the stepped configuration of the first shaft 1084. The inner axial surface 1180 can extend radially between the larger inner diameter of the first axial end 1172 and the smaller inner diameter of the second axial end 1174.

[0073] Fig.14An example of a third shaft 1090 is depicted. The third shaft 1090 may include a threaded surface 1230, which may be disposed at an outer radial surface of the third shaft 1090. The threaded surface 1230 may extend from a first axial end 1232 of the third shaft 1090 toward a second axial end 1234 of the third shaft 1090. The second axial end 1234 may include one or more flat portions 1236, such as for applying torque to the third shaft 1090 or resisting the application of torque to the third shaft 1090. For example, the third shaft 1090 may be cylindrical, hollow, or both.

[0074] Fig.15 An example of a coupling 1080 of a fuel nozzle 1038 in an assembled configuration with a housing 29 is depicted. Assembling the fuel nozzle 1038 and coupling 1080 with the housing 29 may include moving the flange 1082 proximate to the housing bore 76, which may include positioning the flange 1082 adjacent to or in contact with the inner surface 60 of the housing 29. Additionally or alternatively, moving the flange 1082 proximate to the housing bore 76 may include moving the second seal 1146 adjacent to or in contact with the inner surface 60. In some configurations, the flange 1082 may be held adjacent to or in contact with the inner surface 60 via the connection of the nozzle tube 1070 to the dome wall 46 ( Fig.10 and Fig.11 For example, the nozzle tube 1070 may be secured to the dome wall 46 ( Fig.10 and Fig.11 ), which can facilitate the assembly of the connecting piece 1080 and the shell 29.

[0075] According to some aspects, the first shaft 1084 can be connected to the flange 1082, which can include at least partially inserting the first shaft 1084 into the housing bore 76, engaging one or more formations 1122 of the flange 1082 with one or more formations 1124 of the first shaft 1084, setting the first axial surface 1126 of the first shaft 1084 in contact with the axial surface 1120 of the flange 1082, aligning the first fluid channel 1100 with the second fluid channel 1102, setting the first axial surface 1126 in contact with the first seal 1144, or a combination thereof.

[0076] In some examples, after the first shaft 1084 is connected to the flange 1082, the second shaft 1086 can be connected to the flange 1082. Connecting the second shaft 1086 to the flange 1082 can include engaging the threaded surface 1170 of the second shaft 1086 with the threaded surface 1116 of the flange 1082, which can include at least partially inserting the first axial end 1172 of the second shaft 1086 into the channel 1114 of the flange 1082 (e.g., screwing the second shaft 1086 into the flange 1082). Additionally or alternatively, connecting the second shaft 1086 to the flange 1082 can clamp at least a portion of the first shaft 1084 between the axial surface 1120 of the flange 1082 and the inner axial surface 1180 of the second shaft 1086. Clamping the first shaft 1084 between the flange 1082 and the second shaft 1086 can compress or deform the first seal 1144 at least to some extent to provide a fluid seal between the flange 1082 and the first shaft 1084. According to some configurations, the first shaft 1084 can be held in place, such as by applying a force or torque to the flat portion 1158, while the second shaft 1086 is connected to the flange 1082, which can also hold the flange 1082 in place, such as by engagement between the formations 1122, 1124. For example, holding the first shaft 1084 in place can prevent rotational forces or torque applied to the second shaft 1086 (e.g., via the flat portion 1176) from being transmitted to the flange 1082 or the nozzle tube 1070, thereby preventing the nozzle tube 1070, the dome wall 46 ( Fig.11 ) or damage or misalignment of both.

[0077] According to some examples, after the second shaft 1086 is connected to the flange 1082, the third shaft 1090 can be connected to the flange 1082. Connecting the third shaft 1090 to the flange 1082 may include engaging the threaded surface 1230 of the third shaft 1090 with the threaded surface 1118 of the flange 1082, which may include at least partially inserting the first axial end 1232 of the third shaft 1090 into the channel 1114 of the flange 1082 (e.g., screwing the third shaft 1090 into the flange 1082). According to some configurations, the first shaft 1084 and the second shaft 1086 can be held in place, such as via applying a force or torque to the flat portions 1158, 1176, while the third shaft 1090 is connected to the flange 1082, which may also hold the flange 1082 in place, such as via engagement between the formations 1122, 1124. For example, holding the first shaft 1084 in place can prevent rotational forces or torque applied to the third shaft 1090 (e.g., via the flat portion 1236) from being transmitted to the flange 1082 or the nozzle tube 1070, thereby preventing the nozzle tube 1070, the dome wall 46 ( Fig.11 ) or damage or misalignment of both.

[0078] According to some examples, after the third shaft 1090 is connected to the flange 1082, the nut 1088 can be connected to the third shaft 1090. Connecting the nut 1088 to the third shaft 1090 can include engaging the threaded inner surface 1190 of the nut 1088 with the threaded surface 1230 of the third shaft 1090 (e.g., the nut 1088 can be screwed onto the third shaft 1090). The nut 1088 can be screwed onto the third shaft 1090 until the nut 1088 contacts the outer surface 62 of the housing 29, a threshold torque is reached, or both. The torque can be applied to the nut 1088 via one or more flat portions 1192 of the nut 1088. Connecting the nut 1088 to the third shaft 1090 can include compressing or deforming the second seal 1146 at least to some extent to provide a fluid seal between the flange 1082 and the inner surface 60 of the housing 29. Additionally or alternatively, connecting the nut 1088 to the third shaft 1090 can clamp a portion of the housing 29 between the flange 1082 and the nut 1088, which can rigidly secure the nozzle 38 to the housing 29. When the nut 1088 is connected to the third shaft 1090, one or a combination of the first shaft 1084, the second shaft 1086, or the third shaft 1090 can be held in place, such as by applying a force or torque to the flat portions 1158, 1176, 1236, which can prevent the rotational force applied to the nut 1088 from being transmitted to the flange 1082 or the nozzle tube 1070, which can help prevent the nozzle tube 1070, the dome wall 46 ( Fig.11 ) or both. The connection of the nut 1088 to the third shaft 1090 can complete the connection of the coupling 1080 (and the fuel nozzle assembly 1048) to the housing 29.

[0079] According to some aspects, the assembled coupling 1080 can provide a leakage path LP. The leakage path LP can provide fluid communication from the interior of the coupling 1080 to the space 200 outside the housing 29. For example, if a leak occurs in the coupling 1080, it may be desirable to provide the leakage fluid to the space 200 outside the housing 29 rather than to the space 202 inside the housing 29. In some cases, leakage may occur between the flange 1082 and the first shaft 1084. Such leakage may include a portion of the fluid F (e.g., fuel) that flows through the first fluid passage 1100, flows radially outward between the axial surfaces 1120, 1126, and passes through the first seal 1144 instead of flowing into the second fluid passage 1102. The leakage fluid can then reach the inner surface 1210 of the second shaft 1086. One or more leakage channels 1154 of the first shaft 1084, one or more leakage channels 1182 of the second shaft 1086, or a combination thereof may reduce resistance to fluid flow between the first shaft 1084 and the second shaft 1086 so as to promote leakage fluid to flow toward the space 200 outside the housing 29 (as opposed to toward the space 202).

[0080] According to some examples, the first shaft 1084 and the second shaft 1086 may be arranged such that a radial gap 1212 is arranged between an outer surface 1214 of the first shaft 1084 and an inner surface 1210 of the second shaft 1086. The leakage fluid may flow into the radial gap 1212 through one or more leakage channels 1154, 1182, and then flow into the space 200. For example, the leakage path LP may include a space between the axial surfaces 1120, 1126, a space between the outer surface 1214 of the first shaft 1084 and the inner surface 1210 of the second shaft 1086 at the first axial end 1150, 1172, a space between the second axial surface 1156 of the first shaft 1084 and the inner axial surface 1180 of the second shaft 1086, one or more leakage channels 1154 of the first shaft 1084, one or more leakage channels 1182 of the second shaft 1086, the radial gap 1212, or a combination thereof. The resistance to fluid flow in the leakage path LP can be lower than the resistance to fluid flow between the flange 1082 and the threaded surfaces 1116, 1170 of the second shaft 1086 and the third shaft 1090, so most or all of the leakage fluid can flow through the leakage path LP to the space 200 outside the shell 29 instead of the space 202 inside the shell.

[0081] According to some examples, the first shaft 1084 and the second shaft 1086 can be hollow, cylindrical, arranged in a concentric configuration, or a combination thereof. In some examples of the assembled fuel nozzle 1038, portions of the first shaft 1084, the second shaft 1086, the nut 1088, and the third shaft 1090 can overlap in a radial direction (e.g., relative to the centerline 1080a of the coupling 1080). Additionally or alternatively, in some examples of the assembled fuel nozzle 1038, portions of the first shaft 1084, the second shaft 1086, the third shaft 1090, and the housing 29 can overlap in a radial direction. Additionally or alternatively, in some examples of the assembled fuel nozzle 1038, portions of the flange 1082, the first seal 1144, the second shaft 1086, the third shaft 1090, and the second seal 1146 can overlap in a radial direction. In some constructions, the diameter of the housing bore 76 can be larger than the outer diameter of the third shaft 1090 so that the third shaft 1090 does not contact the housing 29 in the assembled construction, so that the third shaft 1190 can rotate in the housing bore 76 (for example, when connected to the flange 1082) without contacting the housing 29, or both.

[0082] In some examples, the nozzle tube 1070 is connected to the dome wall 46 ( Figure 2 ) before connecting, before connecting the first shaft 1084 to the flange 1082, or before both.

[0083] refer to Fig.16 , generally showing the assembly of the gas turbine engine 10 according to Figure 2-15 The method 2000 of an embodiment of a fuel nozzle assembly 48 , 1048 , which may include a fuel nozzle 38 , 1038 and a coupling 80 , 1080 , and a gas turbine engine 10 , which may include a dome wall 46 and a casing 29 . The method 2000 may include coupling the nozzle tube 70, 1070 to the dome wall 46 (frame 2002), inserting the first shaft 84, 1084 into the bore 76 of the housing 29 (frame 2004), engaging the first shaft 84, 1084 with the flange 82, 1082 (frame 2006), inserting the second shaft 86, 1086 into the bore 76 of the housing 29 (frame 2008), engaging the second shaft 86, 1086 with the flange 82, 1082 (frame 2010), engaging the nut 88, 1088 with the second shaft 88, 1086 or the third shaft 1090 (frame 2012), applying torque to the nut 88, 1088 to secure the fuel nozzle assembly 48, 1048 to the housing 29 (frame 2014), or a combination thereof. The method 2000 may include limiting the rotation of the first shaft 84, 1084 when engaging the second shaft 86, 1086 with the flange 82, 1082 (block 2020), and limiting the rotation of the second shaft 86, 1086 when engaging the nut 88, 1088, applying torque to the nut 88, 1088, or both (block 2022). Limiting the rotation of the first shaft 84, 1084 may include applying a force or torque to a portion of the first shaft 84, 1084 disposed outside the housing 29. Engaging the second shaft 86, 1086 with the flange 82, 1082 may include applying a second force or torque to a portion of the second shaft 86, 1086 disposed outside the housing 29. Limiting the rotation of the second shaft 86, 1086 may include applying a third force or torque to a portion of the second shaft 86, 1086 disposed outside the housing 29. The nut 88, 1088 may be disposed outside the housing 29.

[0084] Engaging the first shaft 84, 1084 with the flange 82, 1082 may include inserting the teeth 122, 1122, 124, 1124 of one of the first shaft 84, 1084 or the flange 82, 1082 in the axial direction into the recesses 122, 1122, 124, 1124 of the other of the first shaft 84, 1084 and the flange 82, 1082. Connecting the nozzle tube 70, 1070 to the dome wall 46 may include rigidly securing the nozzle tube 70, 1070 to the dome wall 46 before engaging the nut 88, 1088 with the second shaft 86, 1086 or the third shaft 1090. Connecting the nozzle tube 70 to the dome wall 46 may include rigidly securing the nozzle tube 70, 1070 to the dome wall 46 before inserting the first shaft 84, 1084 into the hole 76. The method 2000 may include engaging (e.g., threading) the third shaft 1090 with the flange 1082 (block 2030). The nut 1088 may engage the third shaft 1090. Threading the third shaft 1090 with the flange 1082 may include deforming the seal 1146 disposed between the flange 1082 and the inner surface 60 of the housing 29.

[0085] Connecting the fuel nozzle 38, 1038 to the housing via a threaded shaft and nut, as opposed to multiple individual bolts inserted into separate holes, can reduce or eliminate stress concentrators from the connection between the fuel nozzle 38, 1038 and the housing 29, and provide a more uniform clamping force between the fuel nozzle 38, 1036 and the housing 29. In some cases, this configuration can provide a more uniform force to the first seal 144, 1144, which can provide an improved fluid seal. Additionally or alternatively, such a configuration can reduce the minimum strength of one or more portions of the housing 29, such as compared to other designs that can have increased strength to withstand concentrated forces (e.g., from multiple individual bolts).

[0086] In some examples, in an assembled configuration, the flat portion 158, 176, 192, 1158, 1176, 1192, 1236 can be disposed outside of the housing 29, such as in the space 200. The nut 88, 1088 can be disposed entirely outside of the housing 29. The first shaft 84, 1084 can extend axially beyond the second shaft 86, 1086 (e.g., in a direction away from the housing 29) such that the flat portion 158, 1158 is not covered by the second shaft 86, 1086. In an example with a third shaft 1090, the second shaft 1086 can extend axially beyond the third shaft 1090 such that the flat portion 1176 is not covered by the third shaft 1090. For example, the first shaft 84, 1084 can be longer than the second shaft 86, 1086, and the second shaft 86, 1086 can be longer than the third shaft 1090. The first shaft 84 , 1084 , the second shaft 86 , 1086 , and the third shaft 1090 may extend axially beyond the nut 88 , 1088 such that the flat portion 158 , 176 , 1158 , 1176 , 1236 is not covered by the nut.

[0087] The flange 82, 1082 may be disposed completely within the interior of the housing 29. The shaft 84, 86, 1084, 1086, 1090 may be disposed partially outside of the housing 29, partially within the bore 76 of the housing 29, partially within the interior of the housing 29, or a combination thereof.

[0088] According to some aspects, providing an intentional leak path for the fuel nozzle 38, 1038 can reduce or eliminate the flow of fluid leaking from the fuel nozzle 38, 1038 into the space 202 inside the housing 29, and instead cause the leaking fluid to flow into the space 200 outside the housing 29. The space 200 outside the housing 29 can be better configured to detect, mitigate, compensate for leaking fluid, or a combination thereof, compared to the space 202 inside the housing 29. For example, but not limited to, the space 200 can include one or more leak detectors.

[0089] Although the first shaft 84, 1084 is shown as a separate component, the first shaft 84, 1084 can be integrated into another component or system, such as an adapter or the fuel supply 34 (e.g., a fuel manifold). Additionally or alternatively, the first shaft 84, 1084 can include one or more additional components, such as a check valve, a valve housing, or both, among others.

[0090] In some configurations, one or more portions of the fuel nozzle 38, 1038, the dome wall 46, and the swirler 74, 1074 may be preassembled as a subassembly. For example, the swirler 74, 1074 may be secured to the dome wall 46 (e.g., brazed together with the dome wall 46), and the nozzle tube 70, 1070 or its nozzle tip 72, 1072 may be secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the swirler 74, 1074 to form a subassembly. The subassembly may then be connected to other portions of the engine 10. For example, the dome wall 46 may be connected to the combustor liner 40, and the nozzle 38 may be secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the inner surface 60 of the casing 29.

[0091] The term "nozzle" is used in various ways in the context of gas turbine engines. In this application, a "nozzle" refers to a component having a portion for fluidly coupling to a fuel supply and having at least a portion for fluidly coupling with a combustor cup 31. The distal end of a fuel nozzle 38, 1038 or nozzle tube 70, 1070 may have a nozzle tip 72, 1072, but is not referred to herein as a nozzle per se.

[0092] In addition to those shown in the above-mentioned figures, the present disclosure also contemplates many other possible aspects and configurations. The aspects disclosed herein can reduce the number of casing holes 76, provide a more uniform clamping force between the fuel nozzle 38, 1038 and the casing 29, fix the relative positions of the fuel nozzle 38, 1038, the casing 29 and the dome wall 46, and reduce or eliminate the presence of leaking fluid in the casing 29. The technical effect is that the strength of the casing 29 is improved, stress concentrators (e.g., bolts) can be eliminated, a consistent flame distribution is provided, and fluid leakage from the fuel nozzle 38 in the casing 29 is reduced or eliminated.

[0093] Further aspects are provided by the subject matter of the following clauses:

[0094] A gas turbine engine comprises: a combustion section, which is shielded by a casing having at least one through passage, the combustion section comprising: a dome wall and a liner, the dome wall and the liner at least partially defining a combustion chamber; a fuel nozzle, the fuel nozzle being connected to the dome wall and having a nozzle tube; and a coupling, the coupling fixing the fuel nozzle to the inner surface of the casing and being at least partially disposed in the at least one through passage; wherein the coupling comprises a flange disposed at the inner surface of the casing, a first shaft engaged with the flange, and a second shaft at least partially disposed around the first shaft and engaged with the flange.

[0095] A gas turbine engine according to any preceding clause, wherein the fuel nozzle is rigidly fixed to the inner surface of the casing and to the dome wall by the coupling.

[0096] A gas turbine engine as in any preceding clause, wherein the first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled to the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled to the second fluid passage.

[0097] A gas turbine engine as claimed in any preceding clause, wherein the first shaft and the second shaft extend into the through passage.

[0098] A gas turbine engine as claimed in any preceding clause, wherein the coupling comprises a nut disposed at an outer surface of the casing and engaged with the second shaft.

[0099] A gas turbine engine as claimed in any preceding clause, wherein the flange engages a threaded surface of the second shaft.

[0100] A gas turbine engine as claimed in any preceding clause, wherein an axial surface of the first shaft comprises a formation which engages with a corresponding formation of an axial surface of the flange.

[0101] A gas turbine engine as in any preceding clause, wherein the first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled to the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled to the second fluid passage.

[0102] A gas turbine engine as described in any preceding clause, wherein the first shaft, the second shaft and the flange at least partially define a leakage path that provides fluid communication from an interior of the coupling to a space exterior of the casing.

[0103] The gas turbine engine of any preceding clause, wherein the leakage path comprises a leakage channel of the first shaft, a leakage channel of the second shaft, or both; and wherein the leakage path comprises a radial gap between the first shaft and the second shaft.

[0104] A gas turbine engine according to any preceding clause, wherein the coupling comprises a first seal disposed in a first sealing recess of the flange and a second seal disposed in a second sealing recess of the flange; wherein the flange comprises a channel radially disposed between the first sealing recess and the second sealing recess; and wherein a portion of the second shaft is disposed in the channel.

[0105] A gas turbine engine according to any preceding clause, wherein the coupling comprises a nut disposed at an outer surface of the casing; wherein the coupling comprises a third shaft disposed at least partially around the second shaft; and wherein the third shaft engages with the flange and the nut.

[0106] A gas turbine engine according to any preceding clause, wherein the third shaft includes a threaded surface engaged with the flange and the nut; wherein the second shaft includes a second shaft threaded surface engaged with the flange; and wherein portions of the second shaft and the third shaft are disposed in a channel of the flange.

[0107] A gas turbine engine as described in any preceding clause, wherein the first shaft, the second shaft, the third shaft and the nut include a flat portion disposed outside the casing.

[0108] A fuel nozzle assembly for a gas turbine engine, the fuel nozzle assembly comprising: a first shaft, the first shaft comprising a first fluid passage; a flange, the flange being connected to the first shaft and comprising a second fluid passage fluidically coupled to the first fluid passage; a nozzle pipe, the nozzle pipe being connected to the flange and comprising a third fluid passage fluidically coupled to the second fluid passage, the nozzle pipe being disposed at a first side of the flange; a second shaft, the second shaft being connected to the flange, the first shaft being at least partially disposed in the second shaft; and a nut, the nut being disposed at a second side of the flange, the second side being opposite to the first side.

[0109] The fuel nozzle assembly of any preceding clause, wherein the flange, the first shaft, and the second shaft at least partially define a leak path.

[0110] A fuel nozzle assembly according to any preceding clause, wherein the leakage path comprises: a radial gap between the first shaft and the second shaft; and a leakage channel in an axial surface of at least one of the first shaft or the second shaft.

[0111] A fuel nozzle assembly as defined in any preceding clause, wherein one of the flange or the first shaft includes an axially extending tooth disposed in a recess in the other of the flange and the first shaft.

[0112] A fuel nozzle assembly as defined in any preceding clause, wherein the first shaft extends axially beyond the second shaft such that a flat portion of the first shaft is not covered by the second shaft.

[0113] A fuel nozzle assembly according to any preceding clause, further comprising a third shaft disposed at least partially around the second shaft; wherein the first shaft is at least partially disposed in the third shaft; and wherein the second shaft and the third shaft are threadedly engaged with the flange.

[0114] A fuel nozzle assembly according to any preceding clause, wherein the flange includes a channel having a first threaded surface and a second threaded surface disposed at opposite sides of the channel; wherein the second shaft engages the first threaded surface; and wherein the third shaft engages the second threaded surface.

[0115] A method for assembling a fuel nozzle assembly in a gas turbine engine including a dome wall and a casing, the fuel nozzle assembly including a flange, a first shaft, a second shaft, a nozzle tube and a nut, the method comprising: connecting the nozzle tube to the dome wall; inserting the first shaft into a hole in the casing; engaging the first shaft with the flange; inserting the second shaft into the hole in the casing; engaging the second shaft with the flange; engaging the nut with the second shaft or a third shaft of the fuel nozzle assembly; and applying torque to the nut to secure the fuel nozzle assembly to the casing.

[0116] The method of any preceding clause, further comprising limiting rotation of the first shaft when engaging the second shaft with the flange; and limiting rotation of the second shaft when engaging the nut, applying torque to the nut, or both.

[0117] A method according to any preceding clause, wherein limiting the rotation of the first shaft comprises applying a force or torque to a portion of the first shaft disposed outside of the housing;

[0118] Wherein engaging the second shaft with the flange comprises applying a second force or torque to a portion of the second shaft disposed outside the housing; wherein limiting the rotation of the second shaft comprises applying a third force or torque to the portion of the second shaft disposed outside the housing; and wherein the nut is disposed outside the housing.

[0119] A method as in any preceding clause, wherein engaging the first shaft with the flange comprises inserting teeth of one of the first shaft or the flange into recesses of the other of the first shaft or the flange in an axial direction.

[0120] A method as in any preceding clause, wherein connecting the nozzle tube to the dome wall comprises rigidly securing the nozzle tube to the dome wall prior to engaging the nut with the second shaft or the third shaft.

[0121] A method as in any preceding clause, wherein connecting the nozzle tube to the dome wall comprises rigidly securing the nozzle tube to the dome wall prior to inserting the first shaft into the bore.

[0122] A method as in any preceding clause, further comprising threadedly engaging the third shaft with the flange; wherein the nut engages the third shaft.

[0123] A method as in any preceding clause, wherein threadedly engaging the third shaft with the flange comprises deforming a seal disposed between the flange and an inner surface of the housing.

[0124] A hydrogen fuel nozzle assembly for a gas turbine engine, the hydrogen fuel nozzle assembly comprising: a first shaft, the first shaft comprising a first fluid passage; a flange, the flange being connected to the first shaft and comprising a second fluid passage fluidically coupled to the first fluid passage; a nozzle tube, the nozzle tube being connected to the flange and comprising a third fluid passage fluidically coupled to the second fluid passage; a second shaft, the second shaft being connected to the flange, the first shaft being at least partially disposed in the second shaft; and a nut, the nut being connected to the second shaft.

[0125] A fuel nozzle assembly according to any preceding clause, wherein the nut is disposed on the exterior of the housing and the flange is disposed on the interior of the housing.

[0126] A method for assembling a fuel nozzle assembly according to any of the preceding clauses in a gas turbine engine comprising a dome wall and a casing, the method comprising: connecting the nozzle tube to the dome wall; inserting the first shaft into a hole in the casing; engaging the first shaft with the flange; inserting the second shaft into the hole in the casing; engaging the second shaft with the flange; engaging the nut with the second shaft or a third shaft; and applying torque to the nut to secure the fuel nozzle assembly to the casing.

[0127] The method of any preceding clause, further comprising limiting rotation of the first shaft when engaging the second shaft with the flange; and limiting rotation of the second shaft when engaging the nut, applying torque to the nut, or both.

[0128] A method according to any preceding clause, wherein limiting the rotation of the first shaft includes applying a force or torque to a portion of the first shaft disposed outside the housing; wherein engaging the second shaft with the flange includes applying a second force or torque to a portion of the second shaft disposed outside the housing; wherein limiting the rotation of the second shaft includes applying a third force or torque to the portion of the second shaft disposed outside the housing; and wherein the nut is disposed outside the housing.

[0129] A method as in any preceding clause, wherein engaging the first shaft with the flange comprises inserting teeth of one of the first shaft or the flange into recesses of the other of the first shaft or the flange in an axial direction.

[0130] A method as in any preceding clause, wherein connecting the nozzle tube to the dome wall comprises rigidly securing the nozzle tube to the dome wall prior to engaging the nut with the second shaft or the third shaft.

[0131] A method as in any preceding clause, wherein connecting the nozzle tube to the dome wall comprises rigidly securing the nozzle tube to the dome wall prior to inserting the first shaft into the bore.

[0132] A method as in any preceding clause, further comprising threadedly engaging the third shaft with the flange; wherein the nut engages the third shaft.

[0133] A method as in any preceding clause, wherein threadedly engaging the third shaft with the flange comprises deforming a seal disposed between the flange and an inner surface of the housing.

[0134] Although described with respect to turbine engines, it should be understood that the combustor described herein can be used in any engine having a combustor. It should be understood that the application of aspects of the present disclosure discussed herein is also applicable to engines having propeller sections or fan and supercharger sections, as well as turbojets and turbine engines.

[0135] To the extent not yet described, the different features and structures of the various embodiments may be used in combination or in place of one another as desired. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown as such, but is done so for the sake of brevity of description. Thus, the various features of the different embodiments may be mixed and matched as desired to form new embodiments, whether or not the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by the present disclosure.

[0136] This written description uses examples to describe the aspects of the disclosure described herein, including the best mode, and also to enable any person skilled in the art to practice aspects of the disclosure, including making and using any device or system and performing any combined methods. The patentable scope of the various aspects of the disclosure is defined by the claims, and may include other examples that occur to one skilled in the art. These other examples are intended to fall within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims.

Claims

1. A gas turbine engine, characterized in that: include: A combustion section, which is shielded by a housing having at least one through-going passage, and which comprises: a dome wall and a liner, said dome wall and said liner at least partially defining a combustion chamber; a fuel nozzle connected to the dome wall and having a nozzle tube; and a coupling member securing the fuel nozzle to an inner surface of the housing and at least partially disposed in the at least one through passage; The coupling member includes a flange disposed at the inner surface of the housing, a first shaft engaged with the flange, and a second shaft at least partially disposed around the first shaft and engaged with the flange.

2. The gas turbine engine according to claim 1, characterized in that in, The fuel nozzle is rigidly secured to the inner surface of the housing by the coupling and is rigidly secured to the dome wall.

3. The gas turbine engine according to claim 1, characterized in that in, The first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled to the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled to the second fluid passage.

4. The gas turbine engine according to claim 1, characterized in that in, The first shaft and the second shaft extend into the through passage.

5. The gas turbine engine according to claim 1, characterized in that in, The coupling includes a nut disposed at an outer surface of the housing and engaged with the second shaft.

6. The gas turbine engine according to claim 5, characterized in that in, The flange engages a threaded surface of the second shaft.

7. The gas turbine engine according to claim 6, characterized in that in, The axial surface of the first shaft includes a formation that engages a corresponding formation on the axial surface of the flange.

8. The gas turbine engine according to claim 6, characterized in that in, The first shaft includes a first fluid passage, the flange includes a second fluid passage fluidly coupled to the first fluid passage, and the nozzle tube includes a third fluid passage fluidly coupled to the second fluid passage.

9. The gas turbine engine according to claim 6, characterized in that in, The first shaft, the second shaft, and the flange at least partially define a leak path that provides fluid communication from an interior of the coupling to a space exterior to the housing.

10. The gas turbine engine according to claim 9, characterized in that in, The leakage path includes a leakage channel of the first shaft, a leakage channel of the second shaft, or both; and Wherein the leakage path includes a radial gap between the first shaft and the second shaft.

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