Gas turbine engine and fuel nozzle thereof

Abstract

A gas turbine engine comprising a compressor section, a combustion section and a turbine section in a serial flow arrangement and shielded by a housing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; the multiple burner cups are arranged on the wall of the circular top in the circumferential direction; the fuel supply part is connected to the shell; and a fuel nozzle passing through the housing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two of the plurality of burner cups; wherein the fuel nozzle is fixed to the at least two burner cups.

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 other oxides including sulfur oxides (e.g., SO2 and SO3).

[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 diagram showing a flow chart along line III-III according to various aspects described herein. Figure 2 Schematic diagram of a portion of the combustion section.

[0009] Figure 4 is an illustration along line IV-IV according to various aspects described herein Figure 3 Cross-sectional view of a portion of the combustion section.

[0010] Figure 5is a partial cross-sectional view showing a portion of a combustion section according to various aspects described herein.

[0011] Figure 6 is an exploded perspective view showing a portion of a combustion section according to various aspects described herein.

[0012] Fig. 7A is a cross-sectional view of a portion of a tube showing a nozzle according to various aspects described herein.

[0013] Figure 7B is a schematic diagram showing a portion of a nozzle including an insulator according to various aspects described herein.

[0014] Figure 7C is a cross-sectional view of a portion of a tube showing a nozzle according to various aspects described herein.

[0015] Fig.7D is a cross-sectional view of a portion of a tube showing a nozzle according to various aspects described herein.

[0016] Fig. 7E is a cross-sectional view of a portion of a tube showing a nozzle according to various aspects described herein.

[0017] Figure 7F is a schematic diagram showing a portion of a nozzle including an insulator according to various aspects described herein.

[0018] Figure 7G is a schematic diagram showing a portion of a nozzle including an insulator according to various aspects described herein.

[0019] Figure 7H is a schematic diagram showing a portion of a nozzle including an insulator according to various aspects described herein.

[0020] Fig.7I is a schematic diagram showing a portion of a nozzle including an insulator according to various aspects described herein.

[0021] Figure 7J is a flow chart illustrating a method of assembling a nozzle according to various aspects described herein.

[0022] Figure 8 is an axial view showing a portion of a combustion section according to various aspects described herein.

[0023] Fig. 9 is an axial view showing a portion of a combustion section according to various aspects described herein.

[0024] Fig.10 is a partial axial view showing a portion of a combustion section according to various aspects described herein.

[0025] Fig.11 is a partial axial view showing a portion of a combustion section according to various aspects described herein.

[0026] Fig.12 is a partial axial view showing a portion of a combustion section according to various aspects described herein.

[0027] Fig.13 is a flow chart illustrating a method of assembling a turbine engine in accordance with various aspects described herein. DETAILED DESCRIPTION

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] Furthermore, as used herein, the term "radial" or "radially" refers 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] 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 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.

[0043] 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.

[0044] 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.

[0045] 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.

[0046] Figure 2 Depicts the Figure 1 FIG. 1 is a cross-sectional view of the combustion section 14 along the 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. The combustor 30 may have a can shape, can annular or annular arrangement depending on the type of engine in which the combustor 30 is located. In a non-limiting example, the combustor 30 may have a combined arrangement positioned with the casing 29 of the engine.

[0047] 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.

[0048] 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.

[0049] The burner 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 the outer surface 114 of the housing 29. The nozzle 38 fluidly couples the fuel supply 34 to the burner cup 31 and the combustion chamber 50. The fuel F may include any suitable fuel, including hydrocarbon fuels or hydrogen fuels in non-limiting examples. The burner cups 31 may be individually connected to the dome wall 46. For example, but not limited to, the burner cups 31 may be connected to the dome wall 46 in a circumferentially spaced configuration. The burner cups 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. The dome wall 46 may include an orifice 48 for each burner cup 31. Additionally or alternatively, each burner cup 31 may include a corresponding portion of the dome wall 46 having a corresponding orifice 48.

[0050] Figure 3A fuel nozzle 38 connected to the combustion chamber 50 is depicted. The fuel nozzle 38 may include a nozzle tube 70 and a distribution manifold 72. 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 distribution manifold 72. The distribution manifold 72 may include a plurality of manifold tubes (such as a first manifold tube 80, a second manifold tube 82, a third manifold tube 84, and additional manifold tubes), each of which may fluidly couple the nozzle tube 70 to a corresponding burner cup 31, such as a first burner cup 31a, a second burner cup 31b, and a third burner cup 31c, respectively. For example, but not limited to, the distribution manifold 72 and the manifold tubes 80-84 may fluidly couple a single nozzle tube 70 and a single outlet of the fuel supply 34 to a plurality of burner cups 31 and the combustion chamber 50. The manifold tubes 80-84 may include a nozzle tip 86 disposed at a distal end thereof. The nozzle tip 86 may include one or more openings 88 that allow the fuel F to exit the fuel nozzle 38 and enter the combustion chamber 50 .

[0051] In exemplary aspects, the combustor cup 31 includes or is fluidly coupled to a swirler 100. The swirler 100 may be disposed at or around the dome wall 46, and in some cases, may be at least partially disposed in the dome wall aperture 48. The swirler 100 may swirl incoming air 102 (such as compressed air from the compressor section 12) near the fuel F exiting the nozzle tip 86, which may promote a uniform mixture of air and fuel entering the combustor 30. In some configurations, the swirler 100 is fixed (e.g., rigidly, permanently) to the dome wall 46. For example, the swirler 100 may be rigidly fixed to the dome wall 46 via welding, brazing, fasteners, or a combination thereof.

[0052] In some examples, the swirler 100 is connected to and at least partially surrounds each manifold tube 80-84 and the nozzle tip 86. For example, the nozzle tip 86 may extend into and through the corresponding swirler 100. According to some configurations, the manifold tubes 80-84 are rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the swirler 100 so that the fuel nozzle 38 is rigidly fixed to the swirler 100 (e.g., the first, second, and third swirlers 100). For example, the manifold tubes 80-84 may each include a flange 90 (e.g., a mounting flange) at its distal end, the flange 90 being adapted to be fixed to the corresponding swirler 100. The flange 90 may include one or more flange apertures 92, and the one or more flange apertures 92 may receive fasteners 94 (e.g., bolts) to fasten the flange 90 to the swirler 100. Securing the flange 90 to the swirler 100, which may be rigidly secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the dome wall 46, may provide a configuration in which the nozzle tip 86, swirler 100, and dome wall aperture 48 are secured in a concentric position, which may provide a consistent flame distribution in the combustion chamber 50. In other designs, with a floating connection between the nozzle and the dome wall, the nozzle may move at least to some extent relative to the dome wall, which may provide an inconsistent flame distribution.

[0053] Some fuels, such as hydrogen, are particularly sensitive to interaction with the oxidant, so misalignment between the nozzle tip 86, swirler 100, and dome wall aperture 48 may have a significant and undesirable effect on flame distribution. Fixing the nozzle tip 86, swirler 100, and dome wall aperture 48 in proper alignment relative to one another (e.g., in a concentric configuration) may limit or eliminate such undesirable effects on flame distribution.

[0054] The fuel nozzle 38 may provide fuel F to multiple burner cups 31 via a single hole 110 in the housing 29. Other designs include one hole in the housing for each fuel cup (1 hole: 1 cup). This design may be suitable for some fuels (such as liquid fuels), but may be less feasible or unfeasible for other fuels (such as gaseous fuels with lower density (such as hydrogen)). Lower density fuels may require a larger volume of fuel to be provided to the combustion chamber. In other designs, simply increasing the size of each hole in a large number of holes (e.g., at least one hole per fuel cup) may weaken the housing. According to aspects of the current disclosure, the number of holes 110 in the housing 29 is reduced compared to such other designs (e.g., 1 hole: 2 or more cups), while the size of these holes 110 is increased, maintaining the strength of the housing 29. For example, the circumferential distance between adjacent holes 110 may be much greater than in a design where each cup has one hole. Some other designs may also include oversized housing holes to allow the nozzle 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 bore 110 may be just large enough to extend the inlet of the nozzle tube 70 into / through, and may not be large enough to pass the entire fuel nozzle 38 therethrough.

[0055] According to aspects of the present disclosure, the inner diameter of the nozzle tube 70 may be greater than the inner diameter of the manifold tubes 80-84. The proximal end of the nozzle tube 70 may be connected to the fuel supply 34. The distribution manifold 72 and the manifold tubes 80-84 may be connected at or around the distal end of the nozzle tube 70. The distribution manifold 72 may be disposed close to the first burner cup 31a and the first swirler 100, which may allow the first manifold tube 80 to be much shorter than the other manifold tubes 82, 84. For example, but not limited to, the length of the first manifold tube 80 may be 10% or less of the length of the other manifold tubes 82, 84, and the lengths of the other manifold tubes 82, 84 may be the same or similar, or may be different or different. In some configurations, the manifold tubes 80-84 may be connected to the nozzle tube 70 very close to each other, which may provide a mixing effect and cause the distribution manifold 72 to function as a mixing chamber at least to some extent.

[0056] According to some examples, the nozzle tube 70 may be disposed generally in the middle of the fuel nozzle 38 and may be generally circumferentially aligned with a middle one of the plurality of combustor cups 31 coupled with the fuel nozzle 38. The manifold tubes 82, 84 may extend from opposite sides of the distribution manifold 72 and generally in opposite circumferential directions.

[0057] Figure 4Depicted is a fuel nozzle 38 connected to the housing 29, the fuel supply 34, and the combustor cup 31 connected to the dome wall 46. In some examples, the dome wall 46 can be substantially annular and substantially perpendicular to at least some portions of the housing 29, but can also include other configurations. The nozzle tube 70 can include a generally L-shaped configuration. For example, a first section 120 of the nozzle tube 70 can extend generally radially inward from the housing 29 and the fuel supply 34, and a second section 122 of the nozzle tube 70 can extend generally axially from the first section 120 toward the dome wall 46. The first section 120 can be substantially perpendicular to the nozzle tip 86.

[0058] According to aspects of the present disclosure, the nozzle tube 70 may include a nozzle tube flange 124 disposed at a proximal end of the first section 120. The nozzle tube flange 124 may be adapted to be rigidly secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the inner surface 112 of the housing 29 and the fuel supply 34. For example, but not limited to, the nozzle tube flange 124 may include one or more nozzle tube flange apertures 126 that may receive fasteners 128 (e.g., bolts) to fasten the nozzle tube flange 24 to the housing 29 and the fuel supply 34. For example, but not limited to, the nozzle tube flange 124 may include a cylindrical configuration and may directly abut / contact the inner surface 112 of the housing 29. In some configurations, the fuel nozzle 38 is attached (e.g., rigidly secured) to the housing 29 at the nozzle tube flange 124 and is not otherwise attached to the housing 29 (e.g., without including a separate / additional attachment component). The coupling 130 may include the nozzle tube flange 124, the fasteners 128, or both. A portion of the nozzle tube 70 may extend into and through the housing 29 to fluidly couple with the fuel supply 34 .

[0059] In some configurations, the fuel nozzle 38 may be bolted to the inner surface 112 of the casing 29 and to the plurality of combustor cups 31, which may help maintain the relative position (e.g., concentricity) of the nozzle tip 86, the swirler 100, and the dome wall 46, which may provide a consistent flame distribution. According to some examples, the fuel nozzle 38 may not be removable through the casing 29 and may not be configured as a line replaceable unit.

[0060] According to aspects of the present disclosure, the dome assembly 44 may include an extension 140 . The extension 140 may extend generally axially forward and taper radially inward, and may at least partially cover and surround the fuel nozzle 38 and the swirler 100 .

[0061] According to some configurations, the space 142 around the nozzle tube 70 and the manifold tubes 80-84 is at least somewhat closed and in a vacuum to restrict air movement around the tubes 70, 80-84. Restricting air movement may thermally insulate the tubes 70, 80-84 at least to some extent.

[0062] like Figure 5 As shown, the fuel nozzle 38 can be rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the inner surface 112 of the casing 29, such as via a coupling 130, and rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the plurality of combustor cups 31. The outer liner 41 can be disposed at a first radial distance from the axis of rotation 20. The inner liner 42 can be disposed at a second radial distance from the axis of rotation 20. The combustor cup 31 can be disposed at a third radial distance from the axis of rotation 20, the third radial distance being less than the first radial distance and greater than the second radial distance. Some or all of the manifold tubes 82, 84 can be disposed at a fourth radial distance, the fourth radial distance being less than the first radial distance and greater than the second radial distance. The casing 29 and the combustor liner 40 (including the outer liner 41 and the inner liner 42) can include an annular configuration.

[0063] In some configurations, one or more manifold tubes (such as the second manifold tube 82 and the third manifold tube 84) may include a curved configuration, a U-shaped configuration, or both. For example, the U-shaped configuration may open generally axially rearward.

[0064] According to some aspects of the present disclosure, such as Figure 6As generally shown in , the shape of the flange 90 can correspond to the shape of the mating surface 150 of the swirler 100. For example, the flange 90 can have a shape similar to a three-pointed star (e.g., having three tabs extending radially outward and circumferentially spaced from each other), and the swirler 100 can include a raised mating surface 150 having the same or similar shape (e.g., a three-pointed star). The mating surface 150 can include a mating aperture 152 that aligns with a corresponding flange aperture 92 of the flange 90. In some configurations, the mating aperture 152 is threaded to engage the fastener 94 and secure the flange 90 to the swirler 100. The aperture 152 may not be a through aperture. The swirler 100 can have a central aperture 154 that can be aligned with the center of the swirler 100 and can at least partially receive the manifold tubes 80-84, the nozzle tip 86 connected thereto, or a combination thereof. In some configurations, the nozzle tip 86 extends through the swirler 100 without extending beyond the swirler 100, such that the distal end of the nozzle tip 86 is aligned with the distal end of the swirler 100. The swirler 100 may include one or more air inlets 156 that may receive air 102 (such as compressed air from the compressor section 12). The swirler 100 may include a mounting surface 158 that may be connected (e.g., rigidly fixed / mounted) to the dome wall 46. For example, but not limited to, the mounting surface 158 may be a cylindrical surface that may be inserted into the dome wall aperture 48 and brazed or welded to the dome wall 46. The nozzle 38 and its manifold tubes 80-84 may be rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the combustor cup 31 and the dome wall 46 via the swirler 100.

[0065] According to some aspects of the current disclosure, such as Figures 7A-7I , the fuel nozzle 38, the nozzle tube 70, one or more manifold tubes 80-84, or a combination thereof may be thermally insulated, such as via an insulator 168. The tubes 70, 80-84 may include a double wall construction having an inner wall 160 and an outer wall 162 radially spaced outward from the inner wall 160 to define an inner space 164. The outer wall 162 may define an outer wall space 165. The inner wall 160 may be disposed in the outer wall space 165. The inner space 164 may include a portion of the outer wall space 165.

[0066] In some examples, nozzle tube 70 may include inner wall 160, outer wall 162, and insulator 168. Additionally or alternatively, at least one manifold tube 80-84 may include inner wall 160, outer wall 162, and insulator 168 disposed therebetween.

[0067] like Figure 7B-7HAs generally shown in , in some cases, the inner space 164 can be at least partially filled with an insulator 168, at least partially under a vacuum, or a combination thereof. The insulator 168 may include one or more insulating materials 172 that can thermally insulate one or more portions of the nozzle 38, such as air, a gas, a liquid, an aerogel, fiberglass, a honeycomb structure, or a combination thereof. The one or more insulating materials 172 may include a refractory material, such as a microporous material, a heat-absorbing microporous material, a quilted microporous material, a ceramic, an aerogel, or a combination thereof. In some configurations, sections of the insulator 168 may be in contact with the outer wall 162 and may not be in contact with the inner wall 160 (see, e.g., Fig.7D ), which may result in a portion of the inner space 164 being open between the insulator 168 and the inner wall 160. Additionally or alternatively, a section of the insulator 168 may be in contact with the inner wall 160 and may not be in contact with the outer wall 162 (see, e.g. Fig. 7E ), which may result in a portion of the inner space 164 being open between the insulator 168 and the outer wall 162. Additionally or alternatively, a section of the insulator 168 may be in contact with both the inner wall 160 and the outer wall 162 (see, e.g. Figure 7B , Figure 7C , Figure 7F-7I ), which may result in at least some portion of the inner space 164 being filled between the inner wall 160 and the outer wall 162.

[0068] According to some examples, the fuel nozzle 38 may include a fluid opening 170, and an insulator 168 may be provided to limit the flow of fluid from the fluid opening 170 in the inner space 164. For example, during operation of the turbine engine 10, hot air may flow into the fuel nozzle 38 through the fluid opening 170, and the insulator 168 may limit the flow of the hot air into the inner space 164, the flow within the inner space 164, or both. Limiting the flow of the hot air may limit the heating of the fuel flowing through the fuel nozzle 38 (e.g., within the inner wall 160), such as via reduced convection.

[0069] In some examples, the insulator 168 can include an insulating material 172 (e.g., a thermally insulating material) connected to the shell 174. For example, the shell 174 can include a metal. Additionally or alternatively, the shell 174 and the outer wall 162 can include a common material. The shell 174 can serve as a substrate for the insulating material 172. Additionally or alternatively, the insulating material 172 can be formed on the shell 174, applied to the shell 174, or adhered to the shell 174 (or a combination thereof). In some configurations, the shell 174 can be in contact with the outer wall 162, the inner wall 160, both, or neither.

[0070] In some examples, the tubes 70, 80-84 may include a thermal barrier coating (TBC) 166. For example, the inner wall 160 may include a TBC 166a, the outer wall 162 may include a TBC 166b, the outer shell 174 may include a TBC 166c, or a combination thereof. The TBCs 166a-c may be applied to, or disposed on, the inner surface, the outer surface, or both of the inner wall 160, the outer wall 162, and the outer shell 174.

[0071] According to some aspects, the fuel nozzle 38 (e.g., outer wall 162) may include an injection aperture 176 for receiving the insulating material 172 of the insulator 168. The injection aperture 176 may be fluidly coupled to the inner space 164. The fuel nozzle 38 may include a cap 178 that fluidly seals the injection aperture 176 (e.g., after injection).

[0072] In some examples, such as Fig.7I As generally shown in FIG. 1 , the insulator 168 can include a plurality of individual segments 168 a, 168 b. For example, the segments 168 a, 168 b can include one or more disks or other shapes spaced apart from one another in the interior space 164 .

[0073] refer to Figure 7J , the method 200 of assembling the fuel nozzle 38 may include providing an outer wall 162 that defines an outer wall space 165. The method 200 may include inserting the inner wall 160 into the outer wall space 165 (block 204), and inserting the insulator 168 into the outer wall space 165 (block 206). According to some examples, the insulator 168 may be inserted into the outer wall space 165 before the inner wall 160. In other examples, the inner wall 160 may be inserted into the outer wall space 165 before the insulator 168. For example, the inner wall 160 and the outer wall 162 may define an inner space 164, and the insulator 168 may be inserted into the inner space 164. Inserting the insulator 168 may include injecting an insulating material 172 of the insulator 168 into the inner space 164 between the inner wall 160 and the outer wall 162, such as via an injection orifice 176. Inserting the insulator 168 into the outer wall 162 may include inserting the insulating material 172 and the shell 174 into the outer wall space 165. Providing the outer wall 162 may include applying the thermal barrier coating 166b to the outer wall 162. The inner wall 160 may include the thermal barrier coating 166a.

[0074] One or more portions of the method 200 may be repeated or performed in parallel for other sections of the fuel nozzle 38 (eg, tubes 70 , 80 - 84 ).

[0075] The behavior of the fuel during combustion may vary with the temperature of the fuel, and some fuels may be more sensitive to temperature changes than other fuels. Thermally insulating the fuel nozzle 38 (such as the tubes 70, 80-84) can reduce temperature changes (e.g., increases) in the fuel in the fuel nozzle 38. For example, but not limited to, for some fuels, it may be desirable to maintain the fuel temperature significantly lower than the compressor discharge air. At least some of the air temperature in the turbine engine 10 may exceed 1000 degrees Fahrenheit, so thermally insulating the tubes 70, 80-84 can limit the fuel temperature raising effect of such hot air.

[0076] According to some aspects of the current disclosure, such as Figure 8 and Fig. 9 As generally shown in FIG. 1 , the combustion section 14 may include a plurality of nozzles 38 each fluidly coupled to a fuel supply 34 and a plurality of burner cups 31. For example, but not limitation, some configurations may include eighteen (18) burner cups 31 and six fuel nozzles 38, each connected to a respective three of the burner cups 31. However, the present disclosure is not limited to any particular number of burner cups 31 or nozzles 38. The number of housing holes 110 (e.g., holes through which fuel flows) may be equal to the number of nozzles 38, which may be half the number of burner cups 31 or less. In one example, the combustion section 14 may include a first fuel nozzle 38 fluidly coupled to the fuel supply 34 and at least two burner cups 31, and may include one, two, or at least two additional fuel nozzles 38, each fluidly coupled to the fuel supply 34 and at least two respective additional burner cups 31. The nozzles 38 may be coupled to the housing 29, the fuel supply 34, or both via couplings 130.

[0077] According to some aspects of the current disclosure, such as Figure 10-12 As generally shown in FIG. 1 , the fuel nozzle 38 may be connected to other numbers of burner cups 31 (e.g., burner cups 31a-31e), such as at least four burner cups 31. One non-limiting example may include a combustion section 14 having a total of 20 burner cups 31 and four fuel nozzles 38, each of which is fluidly coupled to five burner cups 31. The nozzle 38 may include an additional manifold tube, such as manifold tubes 182, 184, for each additional burner cup 31. For example, the manifold tubes 182, 184 may be connected to the ends of the manifold tubes 82, 84, respectively, and fluidly coupled to a corresponding additional swirler 100. The additional manifold tubes 182, 184 may include a smaller diameter than the nozzle tube 70 and the manifold tubes 80-84.

[0078] In another non-limiting example, the first fuel nozzle 38 is fluidly coupled and rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to a first group of combustor cups 31 including at least four combustor cups 31, the combustion section includes a first group of swirlers 100, the first group of swirlers 100 includes a swirler 100 for each combustor cup 31 in the first group of combustor cups 31; and the fuel nozzle 38 is rigidly fixed (e.g., bolted, brazed, welded, riveted, fastened, etc.) to each swirler 100 in the first group of swirlers 100.

[0079] like Fig.10 and Fig.11 As shown, in some configurations, the manifold tubes 82, 84, 182, 184 may include alternating U-shaped configurations that are substantially parallel to the dome wall 46. Fig.10 As shown, the manifold tubes 82, 84, 182, 184 may include substantially right angles with rounded corners. Additionally or alternatively, as shown Fig.11 As shown, the manifold tubes 82, 84, 182, 184 may include an oblique angle (e.g., an obtuse angle). Additionally or alternatively, in addition to various other configurations, such as Fig.12 As shown, the manifold tubes 82 , 84 , 182 , 184 may be linear.

[0080] refer to Fig.13 , the method 300 of assembling the gas turbine engine 10 may include coupling the nozzle tube 70 and the manifold tubes 80-84 to at least partially form the fuel nozzle 38 (block 302), securing (e.g., rigidly securing) the plurality of swirlers 100 to the dome wall 46 of the dome assembly 44 (block 304), securing (e.g., rigidly securing) the manifold tubes 80-84 of the fuel nozzle 38 to the plurality of swirlers 100 to form a subassembly (block 306), connecting the dome wall 46 of the subassembly to the combustor liner 40 (block 308); and securing (e.g., rigidly securing) the nozzle tube 70 of the fuel nozzle 38 of the subassembly to the inner surface 112 of the casing 29 (block 310). In some configurations, the manifold tubes 80-84 may be secured to the plurality of swirlers 100 (block 306) before securing the swirlers 100 to the dome wall 46 (block 304).

[0081] In some configurations, one or more portions of the fuel nozzle 38, the dome assembly 44, and the swirler 100 may be preassembled as a subassembly. For example, the swirler 100 may be secured to the dome wall 46 of the dome assembly 44 (e.g., brazed together with the dome wall 46), and the manifold tubes 80-86 of the fuel nozzle 38 may be secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the swirler 100 to form a subassembly. The subassembly may then be connected to other portions of the turbine engine 10. For example, the dome wall 46 may be connected to the combustor liner 40, and the nozzle tube 70 may be secured (e.g., bolted, brazed, welded, riveted, fastened, etc.) to the inner surface 112 of the casing 29.

[0082] The term "nozzle" is used in various ways in the context of gas turbine engines. In this application, "nozzle" refers to a component having a portion for fluidly coupling to a fuel supply and having multiple portions for fluidly coupling with a corresponding combustor cup 31. The distal end of the nozzle 38 may have a nozzle tip 86, but is not referred to as a nozzle itself.

[0083] Rigidly securing two elements together includes securing the elements so that they do not move relative to each other. Non-rigidly securing two elements together includes connecting the two elements so that the two elements can move relative to each other at least to a certain extent. For example, a first element can be secured to a second element so that the first element can rotate relative to the second element (e.g., rotatably secured), but the first element is not rigidly secured to the second element.

[0084] In addition to those shown in the above-mentioned figures, the present disclosure also contemplates many other possible aspects and configurations. The examples of the fuel nozzles disclosed herein can be coupled to multiple burner cups, fixed to the dome wall, fixed to the shell, include one or more insulating tubes, or a combination thereof. The aspects disclosed herein can reduce the number of shell holes 110 and fix the relative positions of the fuel nozzles 38, the swirler 100, and the dome wall 46. Additionally or alternatively, the aspects disclosed herein can help maintain the fuel temperature. The technical effect is that the strength of the shell 29 is improved and a consistent flame distribution is provided.

[0085] Further aspects are provided by the subject matter of the following clauses:

[0086] A gas turbine engine comprises: a combustion section, which is shielded by a casing, and the combustion section includes: an annular combustion chamber, which is defined by at least a dome wall and an annular liner; a plurality of burner cups, which are circumferentially arranged on the dome wall; a fuel supply, which is connected to the casing; and a fuel nozzle, which passes through the casing and has a nozzle pipe and a distribution manifold, which fluidly connects the nozzle pipe to at least two burner cups of the plurality of burner cups; wherein the fuel nozzle is fixed to the at least two burner cups.

[0087] 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 at least two combustor cups.

[0088] A gas turbine engine according to any preceding clause, wherein the plurality of combustor cups include a first combustor cup and a second combustor cup; wherein the first combustor cup includes a first swirler fixed to the dome wall; wherein the second combustor cup includes a second swirler fixed to the dome wall; and wherein the fuel nozzles are fixed to the first swirler and the second swirler.

[0089] A gas turbine engine as claimed in any preceding clause, wherein the fuel nozzle is fixed to an inner surface of the casing.

[0090] A gas turbine engine as described in any preceding clause, wherein the distribution manifold comprises (i) a first manifold tube fluidly coupled to the nozzle tube and the first swirler, and (ii) a second manifold tube fluidly coupled to the nozzle tube and the second swirler.

[0091] A gas turbine engine as in any preceding clause, wherein the first manifold tube comprises a first mounting flange rigidly mounted to the first swirler; and wherein the second manifold tube comprises a second mounting flange rigidly mounted to the second swirler.

[0092] A gas turbine engine as claimed in any preceding clause, wherein the nozzle pipe comprises a nozzle pipe mounting flange adapted for connection to an inner surface of a casing of the combustion section.

[0093] A gas turbine engine as claimed in any preceding clause, wherein the first swirler comprises a first swirler mating surface; and wherein a shape of the first swirler mating surface corresponds to a shape of the first mounting flange.

[0094] A gas turbine engine according to the preceding clause, wherein the diameter of the nozzle tube is greater than the diameter of the first manifold tube.

[0095] The gas turbine engine according to the preceding clause, wherein the first manifold tube comprises a double wall construction and insulation.

[0096] A gas turbine engine according to the preceding clause, wherein the plurality of combustor cups include a first combustor cup, a second combustor cup and a third combustor cup; wherein the combustion section further includes a first swirler connected to the first combustor cup, a second swirler connected to the second combustor cup, and a third swirler connected to the third combustor cup; and wherein the fuel nozzle is fixed to the first swirler, the second swirler and the third swirler.

[0097] A gas turbine engine according to the preceding clause, wherein the plurality of burner cups comprises a first group of burner cups, the first group of burner cups comprising at least four burner cups; wherein the combustion section further comprises a first group of swirlers, the first group of swirlers comprising a swirler for each burner cup in the first group of burner cups; and wherein the fuel nozzle is fixed to each swirler in the first group of swirlers.

[0098] The gas turbine engine according to the preceding clause, further comprising an additional fuel nozzle fluidly coupled to the fuel supply and to at least two additional combustor cups of the plurality of combustor cups.

[0099] The gas turbine engine according to the preceding clause, further comprising at least two additional fuel nozzles, each additional fuel nozzle being fluidly coupled to the fuel supply and to at least two respective additional combustor cups of the plurality of combustor cups.

[0100] A gas turbine engine according to the preceding clause, wherein the casing comprises a plurality of casing holes, the fuel supply being connected to the plurality of casing holes, and wherein a total number of casing holes in the plurality of casing holes is less than a total number of combustor cups in the plurality of combustor cups.

[0101] The gas turbine engine according to the preceding clause, wherein said fuel nozzle is configured for use with hydrogen.

[0102] The gas turbine engine according to the preceding clause, wherein said at least two combustor cups include three or more combustor cups.

[0103] The gas turbine engine according to the preceding clause, wherein said at least two combustor cups comprises five combustor cups.

[0104] An aircraft comprising a gas turbine engine according to the preceding clause.

[0105] A fuel nozzle for a combustion section of a gas turbine engine, the fuel nozzle comprising: a nozzle tube; a first manifold tube, the first manifold tube being fluidly coupled to the nozzle tube; a second manifold tube, the second manifold tube being fluidly coupled to the nozzle tube; a first swirler, the first swirler being fixed to the first manifold tube and connected to a dome wall of the combustion section; and a second swirler, the second swirler being fixed to the second manifold tube and connected to the dome wall.

[0106] The fuel nozzle of the preceding clause, wherein the first manifold tube includes a first mounting flange rigidly mounted to the first swirler, and the second manifold tube includes a second mounting flange rigidly mounted to the second swirler.

[0107] A fuel nozzle according to the preceding clause, wherein the nozzle tube includes a nozzle tube mounting flange adapted for connection to an inner surface of a casing of the combustion section.

[0108] A fuel nozzle as recited in the preceding clause, wherein the first swirler comprises a first swirler mating surface; and wherein a shape of the first swirler mating surface corresponds to a shape of the first mounting flange.

[0109] A fuel nozzle according to the preceding clause, wherein the first swirler and the second swirler are rigidly fixed to the dome wall.

[0110] A fuel nozzle according to the preceding clause, further comprising a third manifold tube fluidly coupled to the nozzle tube and a third swirler.

[0111] The fuel nozzle according to the preceding clause, further comprising a plurality of additional manifold tubes at least indirectly fluidly coupled to the nozzle tube and rigidly fixed to respective additional swirlers.

[0112] A fuel nozzle as recited in the preceding clause, wherein the first and second manifold tubes comprise a double wall construction and an insulator.

[0113] A gas turbine engine comprising a fuel nozzle according to any preceding clause.

[0114] A method of assembling a gas turbine engine according to any of the preceding clauses, the method comprising: securing a plurality of swirlers to a dome wall of a dome assembly; securing a manifold tube of the fuel nozzle to the plurality of swirlers to form a subassembly; connecting the dome wall of the subassembly to a combustor liner; and securing a nozzle tube of the fuel nozzle of the subassembly to an inner surface of a casing.

[0115] A method of assembling a gas turbine engine, the method comprising: securing a plurality of swirlers to a dome wall of a dome assembly; securing a manifold tube of a fuel nozzle to the plurality of swirlers to form a subassembly; connecting the dome wall of the subassembly to a combustor liner; and securing a nozzle tube of the fuel nozzle of the subassembly to an inner surface of a casing.

[0116] A gas turbine engine comprises: a compressor section, a combustion section and a turbine section in a serial flow arrangement, the combustion section comprising: a combustion chamber defined by at least one dome wall and a liner; a plurality of combustor cups arranged on the dome wall; and a fuel nozzle fluidly coupled to one or more of the plurality of combustor cups; wherein the fuel nozzle comprises a thermal insulator.

[0117] A gas turbine engine as claimed in any preceding clause, wherein the fuel nozzle comprises a double wall construction having an outer wall and an inner wall defining an inner space.

[0118] A gas turbine engine according to any preceding clause, wherein the thermal insulator is disposed in the inner space.

[0119] A gas turbine engine as described in any preceding clause, wherein the thermal insulation comprises aerogel, fiberglass, or both.

[0120] A gas turbine engine as described in any preceding clause, wherein the fuel nozzle includes a thermal barrier coating disposed on the outer wall, the inner wall, or both the inner wall and the outer wall.

[0121] A gas turbine engine according to any preceding clause, wherein the thermal insulator is in contact with the outer wall.

[0122] A gas turbine engine as claimed in any preceding clause, wherein the thermal insulator is in contact with the inner wall.

[0123] A gas turbine engine according to any preceding clause, wherein the thermal insulator is in contact with the inner wall and the outer wall.

[0124] A gas turbine engine as claimed in any preceding clause, wherein the thermal insulator comprises thermally insulating material connected to the outer casing.

[0125] A gas turbine engine as described in any preceding clause, wherein the casing comprises metal.

[0126] A gas turbine engine as claimed in any preceding clause, wherein the outer wall and the casing comprise a common material.

[0127] A gas turbine engine as described in any preceding clause, wherein the casing comprises a thermal barrier coating.

[0128] A gas turbine engine as described in any preceding clause, wherein the inner wall, the outer wall and the outer casing comprise a thermal barrier coating.

[0129] A gas turbine engine as claimed in any preceding clause, wherein the fuel nozzle comprises a fluid opening and the thermal insulator is arranged to restrict the flow of fluid from the fluid opening in the inner space.

[0130] A gas turbine engine as claimed in any preceding clause, wherein the thermal insulator comprises a honeycomb structure.

[0131] A gas turbine engine as claimed in any preceding clause, wherein the thermal insulation comprises a plurality of separate sections.

[0132] A gas turbine engine as claimed in any preceding clause, wherein said plurality of individual sections comprises one or more disks.

[0133] A gas turbine engine according to any preceding clause, wherein the fuel nozzle comprises an injection orifice for receiving material of the thermal insulation, the injection orifice being fluidly coupled to the inner space.

[0134] A gas turbine engine as claimed in any preceding clause, wherein the fuel nozzle comprises a cap fluidly sealing the injection orifice.

[0135] A gas turbine engine as claimed in any preceding clause, wherein the fuel nozzle comprises a nozzle tube and a distribution manifold, the distribution manifold comprising a plurality of manifold tubes.

[0136] A gas turbine engine as claimed in any preceding clause, wherein said nozzle pipe comprises said outer wall and said inner wall.

[0137] The gas turbine engine of any preceding clause, wherein at least one manifold tube of the plurality of manifold tubes comprises a manifold tube outer wall, a manifold tube inner wall, and a manifold insulator disposed between the manifold tube outer wall and the manifold tube inner wall.

[0138] A gas turbine engine as described in any preceding clause, wherein the fuel nozzle is rigidly secured to at least one combustor cup of the plurality of combustor cups.

[0139] A method of assembling a fuel nozzle for a gas turbine engine, the method comprising: providing an outer wall defining an outer wall space; inserting an insulator into the outer wall space; inserting an inner wall into the outer wall space; and connecting at least one of the outer wall or the inner wall to a flange.

[0140] A method as in any preceding clause, wherein the insulation is inserted into the outer wall space before the inner wall.

[0141] A method as in any preceding clause, wherein the inner wall is inserted into the outer wall space before the insulator; wherein the inner wall and the outer wall define an inner space; and wherein the thermal insulator is inserted into the inner space.

[0142] A method as in any preceding clause, wherein inserting the insulator comprises injecting insulating material of the insulator into an inner space between the outer wall and the inner wall.

[0143] A method as in any preceding clause, wherein injecting the insulating material of the insulator comprises injecting the insulating material into an injection orifice of the fuel nozzle.

[0144] A method as in any preceding clause, wherein the insulator comprises an insulating material disposed on a housing, and inserting the insulator into the outer wall comprises inserting the insulating material and the housing into the outer wall.

[0145] A method as in any preceding clause, wherein providing the outer wall comprises applying a thermal barrier coating to the outer wall space.

[0146] A method as in any preceding clause, wherein the inner wall comprises a second thermal barrier coating.

[0147] Although described with respect to a turbine engine, it should be understood that the combustors described herein may be used with any engine having a combustor.

[0148] It should be understood that application of aspects of the present disclosure discussed herein also applies to engines having a propeller section or a fan and supercharger section, as well as turbojets and turbine engines.

[0149] 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.

[0150] 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, the combustion section being shielded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of burner cups circumferentially arranged on the dome wall; a fuel supply coupled to the housing; and a fuel nozzle extending through the housing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two of the plurality of combustor cups; Wherein the fuel nozzle is secured to the at least two burner cups.

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 and to the at least two burner cups.

3. The gas turbine engine according to claim 1, characterized in that in, The plurality of burner cups include a first burner cup and a second burner cup; wherein said first burner cup comprises a first swirler secured to said dome wall; wherein said second burner cup comprises a second swirler secured to said dome wall; and The fuel nozzle is fixed to the first swirler and the second swirler.

4. The gas turbine engine according to claim 3, characterized in that in, The fuel nozzle is fixed to an inner surface of the housing.

5. The gas turbine engine according to claim 3, characterized in that in, The distribution manifold includes (i) a first manifold tube fluidly coupled to the nozzle tube and the first swirler, and (ii) a second manifold tube fluidly coupled to the nozzle tube and the second swirler.

6. The gas turbine engine according to claim 5, characterized in that in, The nozzle tube has a diameter greater than a diameter of the first manifold tube.

7. The gas turbine engine according to claim 5, characterized in that in, The first manifold tube includes a double wall construction and an insulator.

8. The gas turbine engine according to claim 1, characterized in that in, The plurality of burner cups include a first burner cup, a second burner cup, and a third burner cup; wherein the combustion section further comprises a first swirler connected to the first burner cup, a second swirler connected to the second burner cup, and a third swirler connected to the third burner cup; and The fuel nozzle is fixed to the first swirler, the second swirler, and the third swirler.

9. The gas turbine engine according to claim 1, characterized in that in, The plurality of burner cups includes a first group of burner cups, the first group of burner cups including at least four burner cups; wherein the combustion section further comprises a first set of swirlers, the first set of swirlers comprising a swirler for each burner cup in the first set of burner cups; and The fuel nozzle is fixed to each swirler in the first group of swirlers.

10. The gas turbine engine according to any one of claims 1 to 9, characterized in that: Further included is an additional fuel nozzle fluidly coupled to the fuel supply and to at least two additional burner cups of the plurality of burner cups.

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